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CONTROL DEWAR AND VLPC BAYONET CAN PLATFORM CONNECTION
DESIGN AND ANALYSIS
DO Engineering Note 382311S-EN-467 July 29 1997
Andrew Kuwazaki PPD-ETT DO Upgrade Group
Approved By
-
TABLE OF CONTENTS
Page
LIST OF TABLES AND FIGURE iii
ABSTRACf v
i
INTRODUcnON 1
APPENDIX A PLATFORM DESIGN CALCULATIONS AI-A6
AND LOAD ESTIMATE
APPENDIX B CONTOUR STRESS PLOTS BI-BI5
APPENDIX C BOLT PATTERNS CI-C6
INITIAL CONDITIONS 2
METHOD OF ANALYSIS 3
CANTILEVER BEAM ANALYSIS 7
CANTILEVER BEAM RESULTS 10
PLATFORM CONNECTION DESIGN 11
RECOMMENDATIONS 16
BOLT PATTERN DESIGN 17
WELD SPECIFICATIONS 20
WELD RECOMMENDATIONS 23
BIBLIOGRAPHY 24
ii
LIST OF TABLES AND FIGURES
Page
Figure 1 Cantilever Beam 1 0x2x 1 with 1 0000 in-Ib 7
Moment
Figure 2 Cantilever Beam 10x2x I with Extension and Lumped 7
Mass Applied
Figure 3 Assembly of Plate Connection at Nodes 1 and 288 18
Figure 4 Reinforcement Material 19
Figure 5 Assembly of Bracket Connection at Nodes 26 and 313 22
Figure I-B
Figure 2-B
Figure 3-B
Figure 4-B
Figure 5-B
Figure 6-B
Figure 7-B
Figure 8-B
Figure 9-B
Cantilever Beam Stresses with Lumped Mass and I-B
Extensions (Mz shy 10000 in-lb)
Cantilever Beam Stresses without Lumped Mass 2-B
and Partial Boom Excluded
Cantilever Beam Stresses without Entire Volume 3-B
on Lumped Mass Side
Cantilever Beam Stresses without Lumped Mass 4-B
and Extensions
Node Connection 288 Lumped Mass and Boom 5-B
Node Connection 288 Lumped Mass and Partial 6-B
Boom Excluded
Node Connection 288 Lumped Mass Partial 7-B
Boom and Fastener Tension Excluded
Node Connection 1 Lumped Mass and Boom 8-B
Node Connection 1 Lumped Mass and Partial 9-B
Boom Excluded
Figure 10-B Node Connection 1 Lumped Mass Partial IO-B
Boom and Fastener Tension Excluded
- Figure II-B Node Connection 313 Stresses with Lumped 11-B
ill
------------ -----~----
Mass and Boom
Figure 12-B Node Connection 313 Stress with Lumped 12-B
Mass and Partial Boom Excluded
Figure 13-B Node Connection 313 Stresses with Fastener 13-B
Tension Lumped Mass and Partial Boom
Figure 14-B Node Connection 26 Stresses with Lumped 14-B
Mass and Partial Boom Excluded
Figure 15-B Node Connection 26 Stresses with Fastener 15-B
Tension Lumped Mass and Partial Boom Excluded
Table 1 Moment Results for all Cantilever Beam 9
Lumped Mass Models
Table 2 Comparison of Moments Results for all 13
Lumped Mass Models
iv
ABSTRACT
The four connections for the control dewar and VLPC bayonet can platform are
designed using finite element analysis to carry all dead weight and live loads Based on
the loads applied to the platform two 1 inch thick plates and two 34 inch thick brackets
made of ASTM A572middotGrade 42 are required The 1 inch thick plate requires a 3S inch
thick intermediate steel material between the Sx4x14 boom and the plate for load
reinforcement as well as weld area reinforcement Both the plates and the brackets
require 34 inch steel bolt connections
v
INTRODUCTION
The new solenoid which just arrived from Japan will be tested while the detector
is positioned outside the collision hall to assure that the solenoid operates correctly before
it is rolled back into the collision hall In order for these tests to begin the proper
cryogenics must be made available The components needed to operate the solenoid are a
control dewar vacuum pump and controllers All of these components along with a
VLPC bayonet can have been designated to sit on a platform which will be mounted onto
the cryobridge The cryobridge is essentially a rectangular column that houses cryogenic
piping and runs around the perimeter of the detector The focus of this report is the
platform connections
First the load estimates due to the above components are considered Second
the platform dimensional outline and the loads as applied to the platform structure are
presented Third the reaction forces and moments generated by a fmite element analysis
are presented for all four connection points Once these three steps are complete the
platform connection design begins
The platform connection designs start by frrst explaining the initial conditions
governing the design Second the design analysis method is presented Third the
tgtlatform connection design is presented And fmally the recommendations for the
connections the bolt patterns and the weld calculations are presented
2
INITIAL CONDITONS
The platfonn design begins with a load analysis which is based on the
components mounted on the platfonn as seen in Appendix A This section of the
analysis specifies the platfonn dimensions and the type of structural material chosen
Page A3 is the dimensional outline of the platfonn structure consisting of 2x 4x 316
and 4x 8x 114 rectangular tubing After these types of tubing were chosen the loads
were distributed as seen on page A4 This model is then entered into the computer and a
fmite element analysis (PEA) is perfonned A fmite element analysis is an approximate
method for calculating the behavior of the real structure Points A B C and D on the
model are considered the connection points of the platfonn The results from the FEA are
shown on page AS where the reaction forces and moments are drawn at all four
connection points In order to maintain continuity with the FEA model the connection
points will no longer be labeled A B C D but will rather be designated as nodes 1 26
313 and 288 due to the meshing process generated by the computer Page A6 shows the
assigned nodes in a simple wireframe sketch and presents the reaction forces and
moments in table fonn at the top of the page
I Appendix A authored by Russell Rucinski Mechanical Engineer
3
METHOD OF ANALYSIS
The analysis required for the four connections involves analyzing the forces acting
on the connections as well as the moments acting on those connections Therefore the
correct analysis must include both reactions SORC I-DEAS 3-D modeling has been
chosen to perform the fmite element analysis However a limitation arises in that this
software does not allow for a direct application of a moment onto a solid part Since I am
modeling all four connections as solid parts I must devise a method that allows me to
completely and correctly model my connections I experimented with numerous elements
and meshing techniques in order to fmd the best analysis method I also consulted with
SORe After trying various techniques I found a method that yielded acceptable
solutions This method will be called the lumped mass model The lumped mass model
allows for a moment to be applied to solid and the creation of this lumped mass model is
outlined in How to Create Moments on a Solid The outline is written in SORe 1shy
OEAS commands and is presented on the following page
Lumped Mass Model
The lumped mass model begins by creating a structure which is also referred to as
a solid part The structure is then meshed where the meshing process involves
subdividing the structure into nodes and finite elements in order to perform fmite element
analysis A fmite element is a discrete entity used to subdivide the geometry of the
structure and each element is a simple shape such as rectangle or a triangle The number
of fmite elements created is determined by the shape and size of the elements This in
tum determines the number and location of the nodes In a fmite element model nodes
are the points where the elements are connected The nodes are what is needed to
continue the development of the lumped mass model
The moment application process begins by choosing a node on the surface of the
structure near the location where the moment is to be applied The selected node is then
copied at some distance away from the structures surface The distance chosen is
irrelevant since the lumped mass model translates the forces directly to the surface and
4
does not require a moment arm length This new node is designated as the lumped mass
and allows for six degrees of freedom(OOF)
5
Constraint Elements
Now that the lumped mass is created it must be constrained to the surface of the
structure Constraining the lumped mass to the structure allows the moment which is
applied to the lumped mass to translate to the structure The leading candidate for
constraint is a constraint element A constraint element connects a single node to a set of
nodes and transmits all translational and rotational forces from the single node to the set
of nodes chosen Thus the constraint element originates from the lumped mass and
connects to the elements on the surface of structure thereby translating the moment
acting on the lumped mass to the elements on the surface of the structure However in
order to transmit the moment from the elements on the surface of the structure to the
elements making up the entire structure the elements on the surface must have six
degrees of freedom as well
Thin Shell Coating
Thin shell coating has been chosen to transmit the moment from the elements on
the surface of the structure to the elements making up the entire structure The thin shell
coating perfonned on the surface of the structure is done for two reasons First it is used
to change the elements on the specified surface from three DOF elements to six DOF
elements This allows for the transmission of the moment from the lumped mass through
the constraint elements to the elements on the surface where the elements on the surface
can now accept rotational degrees of freedom as well as translational degrees of freedom
Second the thin shell coating method provides for the transmission of the moment
throughout the entire structure Since the structure already consists of elements that are
similar in size and shape any force or moment applied to one element will automatically
transmit that same force or moment to adjoining elements Thus by creating a thin shell
coating on the surface of the structure I am allowing the surface elements to receive force
and moment reactions which are in tum transmitted to all the elements in the structure
However there is one precaution that must be mentioned
6
Precaution
The constraint elements used to constrain the lumped mass to the elements on the
surface of the structure create a dissimilar mesh between This occurs because the
geometry of the elements on the surface of the structure are different fonn the geometry
of the constraint elements According to I-DEAS Creating Elements with Special
TechniQues the precaution for joining dissimilar meshes is that the results for any
elements near [this] mesh interface should be suspect In order to avoid suspect results
for elements near the mesh interface these elements are not selected for display during
post processing
7
CANTILEVER BEAM ANALYSIS
In order to validate the lumped mass method results I created several cantilever
beam models First I modeled a cantilever beam as seen below in Fig 1 The cantilever
beam is 10 x 2 x I and is made of steel The left end of the beam is held rigid while a
10000 in-lb moment is applied to the other end acting in the z-direction The resulting
bending stress should be a maximum at 15 ksi based on static calculations where the
moment is the force multiplied by the distance and the bending stress is the moment
multiplied by the distance from the neutral axis to the outer most fiber divided by the
moment of inertia COb - ~c) The results from the ftnite element analysis (FEA) are
15 ksi which agrees with the calculated bending stress of 15 ksi
M
Fig 1 Cantilever Beam 1 0x2x 1 Fig 2 Cantilever Beam lOx2xl with 1 0000 in-lb Moment Applied with Extension and Lumped
Mass Applied
The second cantilever beam model Fig 2 begins with the same dimensions used
in Fig 1 but now there is an additional beam section which extends off the end of the
cantilever beam The additional material allows me to (1) avoid suspect results near the
mesh interface and (2) post process the original cantilever beam section Now I can
constrain the lumped mass where the 10000 in-lb moment in the z-direction is applied
to the surface of the additional material Thus when I post process my model to
determine the maximum stress I can chose to post process only a portion of the extended
8
material This allows me to avoid the suspect results completely while still incorporating
the effects of the moment applied to the lumped mass
The results from the lumped mass method as applied to the cantilever beam are
shown in Table 1 The first maximum Von Mises stress for the cantilever beam 15 ksi
is the theoretical stress which all the models should predict I used this theoretical stress
as comparison for all the cantilever beam models tested
I post processed the second model of the cantilever beam which includes the
extended beam section and the lumped mass interface Figure I-B in Appendix B shows
that this maximum Von Mises stress is 29 ksi a stress that is 9333 higher than the
theoretical stress This result is precaution mentioned early stating that the results for
any elements near a mesh interface should be suspect II And as cautioned the high
stresses occur at the mesh interface
For the third model I post processed only a portion of the extended beam section
and excluded the lumped mass interface as seen in Fig 2-B The maximum Von Mises
stress dropped to 24 ksi With this post processing method I have been able to minimize
the suspect results near the mesh interface and the maximum Von Mises stress is now
only 60 higher than the theoretical stress However the true shape of the cantilever
beam must be analyzed as closely as possible Thus I post processed a fourth model
The fourth model eliminates the entire extended beam section on the side of the
applied moment as seen in Fig 3-B The result is a maximum Von Mises stress of 176
ksi This maximum Von Mises stress is only 1733 higher than the theoretical
maximum stress of 15 ksi
I used a fifth model to determine whether or not the extended beam section on the
opposite side of the lumped mass affects the results Figure 4-B shows the maximum
Von Mises stress for the fifth post processed model which post processes only the
original cantilever beam The stress remained the same at a maximum at 176 ksi
TABLE 1 Moment Resuhs for all Cantilever Beam Lumped Mass Models
PART CONDITION MAX VON MISES STRESS (ksi)
DIFFERENCE FROM THEORETICAL
Cantilever Beam 1 0 000 in-Ib moment applied to end of beam 15 0 With lumped Mass and Extensions 29 9333 Without lumped Mass 24 6000 Without Elements on lumped Mass Side 176 1733 Without lumped Mass and Extensions 176 1733
0
10
CANTILEVER BEAM RESULTS
From the cantilever beam models I found that the lumped mass model produces a
stress that is conservatively higher than that of the theoretical stress value Therefore this
method will only increase the factor of safety in my design Thus I will proceed with the
method of adding material to the original design then applying a lumped mass to the
additional material and fmally post processing only the original shape of the platform
connections
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
I
I I
j i D (- TYP (__________________l~==_L_________________l Ii) I
i ~
I
middot I
I
bullI I middotbullbull bull
iI I
t-------------fr-----------middot---shy I
middotmiddot middot
middot I
bull I -A shy I
I middot IL_ -fI
~-----------------i t-
I bull
DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
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CVLf( BON~ Z ~T 500] 14
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o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
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286
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dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
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RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
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dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
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RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
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STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
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257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
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RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
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t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
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F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
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S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
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a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
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109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
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B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
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VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
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01
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24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
-
TABLE OF CONTENTS
Page
LIST OF TABLES AND FIGURE iii
ABSTRACf v
i
INTRODUcnON 1
APPENDIX A PLATFORM DESIGN CALCULATIONS AI-A6
AND LOAD ESTIMATE
APPENDIX B CONTOUR STRESS PLOTS BI-BI5
APPENDIX C BOLT PATTERNS CI-C6
INITIAL CONDITIONS 2
METHOD OF ANALYSIS 3
CANTILEVER BEAM ANALYSIS 7
CANTILEVER BEAM RESULTS 10
PLATFORM CONNECTION DESIGN 11
RECOMMENDATIONS 16
BOLT PATTERN DESIGN 17
WELD SPECIFICATIONS 20
WELD RECOMMENDATIONS 23
BIBLIOGRAPHY 24
ii
LIST OF TABLES AND FIGURES
Page
Figure 1 Cantilever Beam 1 0x2x 1 with 1 0000 in-Ib 7
Moment
Figure 2 Cantilever Beam 10x2x I with Extension and Lumped 7
Mass Applied
Figure 3 Assembly of Plate Connection at Nodes 1 and 288 18
Figure 4 Reinforcement Material 19
Figure 5 Assembly of Bracket Connection at Nodes 26 and 313 22
Figure I-B
Figure 2-B
Figure 3-B
Figure 4-B
Figure 5-B
Figure 6-B
Figure 7-B
Figure 8-B
Figure 9-B
Cantilever Beam Stresses with Lumped Mass and I-B
Extensions (Mz shy 10000 in-lb)
Cantilever Beam Stresses without Lumped Mass 2-B
and Partial Boom Excluded
Cantilever Beam Stresses without Entire Volume 3-B
on Lumped Mass Side
Cantilever Beam Stresses without Lumped Mass 4-B
and Extensions
Node Connection 288 Lumped Mass and Boom 5-B
Node Connection 288 Lumped Mass and Partial 6-B
Boom Excluded
Node Connection 288 Lumped Mass Partial 7-B
Boom and Fastener Tension Excluded
Node Connection 1 Lumped Mass and Boom 8-B
Node Connection 1 Lumped Mass and Partial 9-B
Boom Excluded
Figure 10-B Node Connection 1 Lumped Mass Partial IO-B
Boom and Fastener Tension Excluded
- Figure II-B Node Connection 313 Stresses with Lumped 11-B
ill
------------ -----~----
Mass and Boom
Figure 12-B Node Connection 313 Stress with Lumped 12-B
Mass and Partial Boom Excluded
Figure 13-B Node Connection 313 Stresses with Fastener 13-B
Tension Lumped Mass and Partial Boom
Figure 14-B Node Connection 26 Stresses with Lumped 14-B
Mass and Partial Boom Excluded
Figure 15-B Node Connection 26 Stresses with Fastener 15-B
Tension Lumped Mass and Partial Boom Excluded
Table 1 Moment Results for all Cantilever Beam 9
Lumped Mass Models
Table 2 Comparison of Moments Results for all 13
Lumped Mass Models
iv
ABSTRACT
The four connections for the control dewar and VLPC bayonet can platform are
designed using finite element analysis to carry all dead weight and live loads Based on
the loads applied to the platform two 1 inch thick plates and two 34 inch thick brackets
made of ASTM A572middotGrade 42 are required The 1 inch thick plate requires a 3S inch
thick intermediate steel material between the Sx4x14 boom and the plate for load
reinforcement as well as weld area reinforcement Both the plates and the brackets
require 34 inch steel bolt connections
v
INTRODUCTION
The new solenoid which just arrived from Japan will be tested while the detector
is positioned outside the collision hall to assure that the solenoid operates correctly before
it is rolled back into the collision hall In order for these tests to begin the proper
cryogenics must be made available The components needed to operate the solenoid are a
control dewar vacuum pump and controllers All of these components along with a
VLPC bayonet can have been designated to sit on a platform which will be mounted onto
the cryobridge The cryobridge is essentially a rectangular column that houses cryogenic
piping and runs around the perimeter of the detector The focus of this report is the
platform connections
First the load estimates due to the above components are considered Second
the platform dimensional outline and the loads as applied to the platform structure are
presented Third the reaction forces and moments generated by a fmite element analysis
are presented for all four connection points Once these three steps are complete the
platform connection design begins
The platform connection designs start by frrst explaining the initial conditions
governing the design Second the design analysis method is presented Third the
tgtlatform connection design is presented And fmally the recommendations for the
connections the bolt patterns and the weld calculations are presented
2
INITIAL CONDITONS
The platfonn design begins with a load analysis which is based on the
components mounted on the platfonn as seen in Appendix A This section of the
analysis specifies the platfonn dimensions and the type of structural material chosen
Page A3 is the dimensional outline of the platfonn structure consisting of 2x 4x 316
and 4x 8x 114 rectangular tubing After these types of tubing were chosen the loads
were distributed as seen on page A4 This model is then entered into the computer and a
fmite element analysis (PEA) is perfonned A fmite element analysis is an approximate
method for calculating the behavior of the real structure Points A B C and D on the
model are considered the connection points of the platfonn The results from the FEA are
shown on page AS where the reaction forces and moments are drawn at all four
connection points In order to maintain continuity with the FEA model the connection
points will no longer be labeled A B C D but will rather be designated as nodes 1 26
313 and 288 due to the meshing process generated by the computer Page A6 shows the
assigned nodes in a simple wireframe sketch and presents the reaction forces and
moments in table fonn at the top of the page
I Appendix A authored by Russell Rucinski Mechanical Engineer
3
METHOD OF ANALYSIS
The analysis required for the four connections involves analyzing the forces acting
on the connections as well as the moments acting on those connections Therefore the
correct analysis must include both reactions SORC I-DEAS 3-D modeling has been
chosen to perform the fmite element analysis However a limitation arises in that this
software does not allow for a direct application of a moment onto a solid part Since I am
modeling all four connections as solid parts I must devise a method that allows me to
completely and correctly model my connections I experimented with numerous elements
and meshing techniques in order to fmd the best analysis method I also consulted with
SORe After trying various techniques I found a method that yielded acceptable
solutions This method will be called the lumped mass model The lumped mass model
allows for a moment to be applied to solid and the creation of this lumped mass model is
outlined in How to Create Moments on a Solid The outline is written in SORe 1shy
OEAS commands and is presented on the following page
Lumped Mass Model
The lumped mass model begins by creating a structure which is also referred to as
a solid part The structure is then meshed where the meshing process involves
subdividing the structure into nodes and finite elements in order to perform fmite element
analysis A fmite element is a discrete entity used to subdivide the geometry of the
structure and each element is a simple shape such as rectangle or a triangle The number
of fmite elements created is determined by the shape and size of the elements This in
tum determines the number and location of the nodes In a fmite element model nodes
are the points where the elements are connected The nodes are what is needed to
continue the development of the lumped mass model
The moment application process begins by choosing a node on the surface of the
structure near the location where the moment is to be applied The selected node is then
copied at some distance away from the structures surface The distance chosen is
irrelevant since the lumped mass model translates the forces directly to the surface and
4
does not require a moment arm length This new node is designated as the lumped mass
and allows for six degrees of freedom(OOF)
5
Constraint Elements
Now that the lumped mass is created it must be constrained to the surface of the
structure Constraining the lumped mass to the structure allows the moment which is
applied to the lumped mass to translate to the structure The leading candidate for
constraint is a constraint element A constraint element connects a single node to a set of
nodes and transmits all translational and rotational forces from the single node to the set
of nodes chosen Thus the constraint element originates from the lumped mass and
connects to the elements on the surface of structure thereby translating the moment
acting on the lumped mass to the elements on the surface of the structure However in
order to transmit the moment from the elements on the surface of the structure to the
elements making up the entire structure the elements on the surface must have six
degrees of freedom as well
Thin Shell Coating
Thin shell coating has been chosen to transmit the moment from the elements on
the surface of the structure to the elements making up the entire structure The thin shell
coating perfonned on the surface of the structure is done for two reasons First it is used
to change the elements on the specified surface from three DOF elements to six DOF
elements This allows for the transmission of the moment from the lumped mass through
the constraint elements to the elements on the surface where the elements on the surface
can now accept rotational degrees of freedom as well as translational degrees of freedom
Second the thin shell coating method provides for the transmission of the moment
throughout the entire structure Since the structure already consists of elements that are
similar in size and shape any force or moment applied to one element will automatically
transmit that same force or moment to adjoining elements Thus by creating a thin shell
coating on the surface of the structure I am allowing the surface elements to receive force
and moment reactions which are in tum transmitted to all the elements in the structure
However there is one precaution that must be mentioned
6
Precaution
The constraint elements used to constrain the lumped mass to the elements on the
surface of the structure create a dissimilar mesh between This occurs because the
geometry of the elements on the surface of the structure are different fonn the geometry
of the constraint elements According to I-DEAS Creating Elements with Special
TechniQues the precaution for joining dissimilar meshes is that the results for any
elements near [this] mesh interface should be suspect In order to avoid suspect results
for elements near the mesh interface these elements are not selected for display during
post processing
7
CANTILEVER BEAM ANALYSIS
In order to validate the lumped mass method results I created several cantilever
beam models First I modeled a cantilever beam as seen below in Fig 1 The cantilever
beam is 10 x 2 x I and is made of steel The left end of the beam is held rigid while a
10000 in-lb moment is applied to the other end acting in the z-direction The resulting
bending stress should be a maximum at 15 ksi based on static calculations where the
moment is the force multiplied by the distance and the bending stress is the moment
multiplied by the distance from the neutral axis to the outer most fiber divided by the
moment of inertia COb - ~c) The results from the ftnite element analysis (FEA) are
15 ksi which agrees with the calculated bending stress of 15 ksi
M
Fig 1 Cantilever Beam 1 0x2x 1 Fig 2 Cantilever Beam lOx2xl with 1 0000 in-lb Moment Applied with Extension and Lumped
Mass Applied
The second cantilever beam model Fig 2 begins with the same dimensions used
in Fig 1 but now there is an additional beam section which extends off the end of the
cantilever beam The additional material allows me to (1) avoid suspect results near the
mesh interface and (2) post process the original cantilever beam section Now I can
constrain the lumped mass where the 10000 in-lb moment in the z-direction is applied
to the surface of the additional material Thus when I post process my model to
determine the maximum stress I can chose to post process only a portion of the extended
8
material This allows me to avoid the suspect results completely while still incorporating
the effects of the moment applied to the lumped mass
The results from the lumped mass method as applied to the cantilever beam are
shown in Table 1 The first maximum Von Mises stress for the cantilever beam 15 ksi
is the theoretical stress which all the models should predict I used this theoretical stress
as comparison for all the cantilever beam models tested
I post processed the second model of the cantilever beam which includes the
extended beam section and the lumped mass interface Figure I-B in Appendix B shows
that this maximum Von Mises stress is 29 ksi a stress that is 9333 higher than the
theoretical stress This result is precaution mentioned early stating that the results for
any elements near a mesh interface should be suspect II And as cautioned the high
stresses occur at the mesh interface
For the third model I post processed only a portion of the extended beam section
and excluded the lumped mass interface as seen in Fig 2-B The maximum Von Mises
stress dropped to 24 ksi With this post processing method I have been able to minimize
the suspect results near the mesh interface and the maximum Von Mises stress is now
only 60 higher than the theoretical stress However the true shape of the cantilever
beam must be analyzed as closely as possible Thus I post processed a fourth model
The fourth model eliminates the entire extended beam section on the side of the
applied moment as seen in Fig 3-B The result is a maximum Von Mises stress of 176
ksi This maximum Von Mises stress is only 1733 higher than the theoretical
maximum stress of 15 ksi
I used a fifth model to determine whether or not the extended beam section on the
opposite side of the lumped mass affects the results Figure 4-B shows the maximum
Von Mises stress for the fifth post processed model which post processes only the
original cantilever beam The stress remained the same at a maximum at 176 ksi
TABLE 1 Moment Resuhs for all Cantilever Beam Lumped Mass Models
PART CONDITION MAX VON MISES STRESS (ksi)
DIFFERENCE FROM THEORETICAL
Cantilever Beam 1 0 000 in-Ib moment applied to end of beam 15 0 With lumped Mass and Extensions 29 9333 Without lumped Mass 24 6000 Without Elements on lumped Mass Side 176 1733 Without lumped Mass and Extensions 176 1733
0
10
CANTILEVER BEAM RESULTS
From the cantilever beam models I found that the lumped mass model produces a
stress that is conservatively higher than that of the theoretical stress value Therefore this
method will only increase the factor of safety in my design Thus I will proceed with the
method of adding material to the original design then applying a lumped mass to the
additional material and fmally post processing only the original shape of the platform
connections
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
I
I I
j i D (- TYP (__________________l~==_L_________________l Ii) I
i ~
I
middot I
I
bullI I middotbullbull bull
iI I
t-------------fr-----------middot---shy I
middotmiddot middot
middot I
bull I -A shy I
I middot IL_ -fI
~-----------------i t-
I bull
DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
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VAtshy vUSC - 631+lshy20 ~ bullis Pt 30
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CVLf( BON~ Z ~T 500] 14
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p~~a8~3 J Amiddot2ENGINEERING NOTE
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o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
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APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
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Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
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I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
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286
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AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
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dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
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Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
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RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
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l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
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t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
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RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
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t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
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F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
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Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
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Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
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l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
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BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
LIST OF TABLES AND FIGURES
Page
Figure 1 Cantilever Beam 1 0x2x 1 with 1 0000 in-Ib 7
Moment
Figure 2 Cantilever Beam 10x2x I with Extension and Lumped 7
Mass Applied
Figure 3 Assembly of Plate Connection at Nodes 1 and 288 18
Figure 4 Reinforcement Material 19
Figure 5 Assembly of Bracket Connection at Nodes 26 and 313 22
Figure I-B
Figure 2-B
Figure 3-B
Figure 4-B
Figure 5-B
Figure 6-B
Figure 7-B
Figure 8-B
Figure 9-B
Cantilever Beam Stresses with Lumped Mass and I-B
Extensions (Mz shy 10000 in-lb)
Cantilever Beam Stresses without Lumped Mass 2-B
and Partial Boom Excluded
Cantilever Beam Stresses without Entire Volume 3-B
on Lumped Mass Side
Cantilever Beam Stresses without Lumped Mass 4-B
and Extensions
Node Connection 288 Lumped Mass and Boom 5-B
Node Connection 288 Lumped Mass and Partial 6-B
Boom Excluded
Node Connection 288 Lumped Mass Partial 7-B
Boom and Fastener Tension Excluded
Node Connection 1 Lumped Mass and Boom 8-B
Node Connection 1 Lumped Mass and Partial 9-B
Boom Excluded
Figure 10-B Node Connection 1 Lumped Mass Partial IO-B
Boom and Fastener Tension Excluded
- Figure II-B Node Connection 313 Stresses with Lumped 11-B
ill
------------ -----~----
Mass and Boom
Figure 12-B Node Connection 313 Stress with Lumped 12-B
Mass and Partial Boom Excluded
Figure 13-B Node Connection 313 Stresses with Fastener 13-B
Tension Lumped Mass and Partial Boom
Figure 14-B Node Connection 26 Stresses with Lumped 14-B
Mass and Partial Boom Excluded
Figure 15-B Node Connection 26 Stresses with Fastener 15-B
Tension Lumped Mass and Partial Boom Excluded
Table 1 Moment Results for all Cantilever Beam 9
Lumped Mass Models
Table 2 Comparison of Moments Results for all 13
Lumped Mass Models
iv
ABSTRACT
The four connections for the control dewar and VLPC bayonet can platform are
designed using finite element analysis to carry all dead weight and live loads Based on
the loads applied to the platform two 1 inch thick plates and two 34 inch thick brackets
made of ASTM A572middotGrade 42 are required The 1 inch thick plate requires a 3S inch
thick intermediate steel material between the Sx4x14 boom and the plate for load
reinforcement as well as weld area reinforcement Both the plates and the brackets
require 34 inch steel bolt connections
v
INTRODUCTION
The new solenoid which just arrived from Japan will be tested while the detector
is positioned outside the collision hall to assure that the solenoid operates correctly before
it is rolled back into the collision hall In order for these tests to begin the proper
cryogenics must be made available The components needed to operate the solenoid are a
control dewar vacuum pump and controllers All of these components along with a
VLPC bayonet can have been designated to sit on a platform which will be mounted onto
the cryobridge The cryobridge is essentially a rectangular column that houses cryogenic
piping and runs around the perimeter of the detector The focus of this report is the
platform connections
First the load estimates due to the above components are considered Second
the platform dimensional outline and the loads as applied to the platform structure are
presented Third the reaction forces and moments generated by a fmite element analysis
are presented for all four connection points Once these three steps are complete the
platform connection design begins
The platform connection designs start by frrst explaining the initial conditions
governing the design Second the design analysis method is presented Third the
tgtlatform connection design is presented And fmally the recommendations for the
connections the bolt patterns and the weld calculations are presented
2
INITIAL CONDITONS
The platfonn design begins with a load analysis which is based on the
components mounted on the platfonn as seen in Appendix A This section of the
analysis specifies the platfonn dimensions and the type of structural material chosen
Page A3 is the dimensional outline of the platfonn structure consisting of 2x 4x 316
and 4x 8x 114 rectangular tubing After these types of tubing were chosen the loads
were distributed as seen on page A4 This model is then entered into the computer and a
fmite element analysis (PEA) is perfonned A fmite element analysis is an approximate
method for calculating the behavior of the real structure Points A B C and D on the
model are considered the connection points of the platfonn The results from the FEA are
shown on page AS where the reaction forces and moments are drawn at all four
connection points In order to maintain continuity with the FEA model the connection
points will no longer be labeled A B C D but will rather be designated as nodes 1 26
313 and 288 due to the meshing process generated by the computer Page A6 shows the
assigned nodes in a simple wireframe sketch and presents the reaction forces and
moments in table fonn at the top of the page
I Appendix A authored by Russell Rucinski Mechanical Engineer
3
METHOD OF ANALYSIS
The analysis required for the four connections involves analyzing the forces acting
on the connections as well as the moments acting on those connections Therefore the
correct analysis must include both reactions SORC I-DEAS 3-D modeling has been
chosen to perform the fmite element analysis However a limitation arises in that this
software does not allow for a direct application of a moment onto a solid part Since I am
modeling all four connections as solid parts I must devise a method that allows me to
completely and correctly model my connections I experimented with numerous elements
and meshing techniques in order to fmd the best analysis method I also consulted with
SORe After trying various techniques I found a method that yielded acceptable
solutions This method will be called the lumped mass model The lumped mass model
allows for a moment to be applied to solid and the creation of this lumped mass model is
outlined in How to Create Moments on a Solid The outline is written in SORe 1shy
OEAS commands and is presented on the following page
Lumped Mass Model
The lumped mass model begins by creating a structure which is also referred to as
a solid part The structure is then meshed where the meshing process involves
subdividing the structure into nodes and finite elements in order to perform fmite element
analysis A fmite element is a discrete entity used to subdivide the geometry of the
structure and each element is a simple shape such as rectangle or a triangle The number
of fmite elements created is determined by the shape and size of the elements This in
tum determines the number and location of the nodes In a fmite element model nodes
are the points where the elements are connected The nodes are what is needed to
continue the development of the lumped mass model
The moment application process begins by choosing a node on the surface of the
structure near the location where the moment is to be applied The selected node is then
copied at some distance away from the structures surface The distance chosen is
irrelevant since the lumped mass model translates the forces directly to the surface and
4
does not require a moment arm length This new node is designated as the lumped mass
and allows for six degrees of freedom(OOF)
5
Constraint Elements
Now that the lumped mass is created it must be constrained to the surface of the
structure Constraining the lumped mass to the structure allows the moment which is
applied to the lumped mass to translate to the structure The leading candidate for
constraint is a constraint element A constraint element connects a single node to a set of
nodes and transmits all translational and rotational forces from the single node to the set
of nodes chosen Thus the constraint element originates from the lumped mass and
connects to the elements on the surface of structure thereby translating the moment
acting on the lumped mass to the elements on the surface of the structure However in
order to transmit the moment from the elements on the surface of the structure to the
elements making up the entire structure the elements on the surface must have six
degrees of freedom as well
Thin Shell Coating
Thin shell coating has been chosen to transmit the moment from the elements on
the surface of the structure to the elements making up the entire structure The thin shell
coating perfonned on the surface of the structure is done for two reasons First it is used
to change the elements on the specified surface from three DOF elements to six DOF
elements This allows for the transmission of the moment from the lumped mass through
the constraint elements to the elements on the surface where the elements on the surface
can now accept rotational degrees of freedom as well as translational degrees of freedom
Second the thin shell coating method provides for the transmission of the moment
throughout the entire structure Since the structure already consists of elements that are
similar in size and shape any force or moment applied to one element will automatically
transmit that same force or moment to adjoining elements Thus by creating a thin shell
coating on the surface of the structure I am allowing the surface elements to receive force
and moment reactions which are in tum transmitted to all the elements in the structure
However there is one precaution that must be mentioned
6
Precaution
The constraint elements used to constrain the lumped mass to the elements on the
surface of the structure create a dissimilar mesh between This occurs because the
geometry of the elements on the surface of the structure are different fonn the geometry
of the constraint elements According to I-DEAS Creating Elements with Special
TechniQues the precaution for joining dissimilar meshes is that the results for any
elements near [this] mesh interface should be suspect In order to avoid suspect results
for elements near the mesh interface these elements are not selected for display during
post processing
7
CANTILEVER BEAM ANALYSIS
In order to validate the lumped mass method results I created several cantilever
beam models First I modeled a cantilever beam as seen below in Fig 1 The cantilever
beam is 10 x 2 x I and is made of steel The left end of the beam is held rigid while a
10000 in-lb moment is applied to the other end acting in the z-direction The resulting
bending stress should be a maximum at 15 ksi based on static calculations where the
moment is the force multiplied by the distance and the bending stress is the moment
multiplied by the distance from the neutral axis to the outer most fiber divided by the
moment of inertia COb - ~c) The results from the ftnite element analysis (FEA) are
15 ksi which agrees with the calculated bending stress of 15 ksi
M
Fig 1 Cantilever Beam 1 0x2x 1 Fig 2 Cantilever Beam lOx2xl with 1 0000 in-lb Moment Applied with Extension and Lumped
Mass Applied
The second cantilever beam model Fig 2 begins with the same dimensions used
in Fig 1 but now there is an additional beam section which extends off the end of the
cantilever beam The additional material allows me to (1) avoid suspect results near the
mesh interface and (2) post process the original cantilever beam section Now I can
constrain the lumped mass where the 10000 in-lb moment in the z-direction is applied
to the surface of the additional material Thus when I post process my model to
determine the maximum stress I can chose to post process only a portion of the extended
8
material This allows me to avoid the suspect results completely while still incorporating
the effects of the moment applied to the lumped mass
The results from the lumped mass method as applied to the cantilever beam are
shown in Table 1 The first maximum Von Mises stress for the cantilever beam 15 ksi
is the theoretical stress which all the models should predict I used this theoretical stress
as comparison for all the cantilever beam models tested
I post processed the second model of the cantilever beam which includes the
extended beam section and the lumped mass interface Figure I-B in Appendix B shows
that this maximum Von Mises stress is 29 ksi a stress that is 9333 higher than the
theoretical stress This result is precaution mentioned early stating that the results for
any elements near a mesh interface should be suspect II And as cautioned the high
stresses occur at the mesh interface
For the third model I post processed only a portion of the extended beam section
and excluded the lumped mass interface as seen in Fig 2-B The maximum Von Mises
stress dropped to 24 ksi With this post processing method I have been able to minimize
the suspect results near the mesh interface and the maximum Von Mises stress is now
only 60 higher than the theoretical stress However the true shape of the cantilever
beam must be analyzed as closely as possible Thus I post processed a fourth model
The fourth model eliminates the entire extended beam section on the side of the
applied moment as seen in Fig 3-B The result is a maximum Von Mises stress of 176
ksi This maximum Von Mises stress is only 1733 higher than the theoretical
maximum stress of 15 ksi
I used a fifth model to determine whether or not the extended beam section on the
opposite side of the lumped mass affects the results Figure 4-B shows the maximum
Von Mises stress for the fifth post processed model which post processes only the
original cantilever beam The stress remained the same at a maximum at 176 ksi
TABLE 1 Moment Resuhs for all Cantilever Beam Lumped Mass Models
PART CONDITION MAX VON MISES STRESS (ksi)
DIFFERENCE FROM THEORETICAL
Cantilever Beam 1 0 000 in-Ib moment applied to end of beam 15 0 With lumped Mass and Extensions 29 9333 Without lumped Mass 24 6000 Without Elements on lumped Mass Side 176 1733 Without lumped Mass and Extensions 176 1733
0
10
CANTILEVER BEAM RESULTS
From the cantilever beam models I found that the lumped mass model produces a
stress that is conservatively higher than that of the theoretical stress value Therefore this
method will only increase the factor of safety in my design Thus I will proceed with the
method of adding material to the original design then applying a lumped mass to the
additional material and fmally post processing only the original shape of the platform
connections
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
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i ~
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bull
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bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
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20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
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ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
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LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
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Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
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dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
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dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
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l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
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jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
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dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
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dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
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F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
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dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
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B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
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VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
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01
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24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
Mass and Boom
Figure 12-B Node Connection 313 Stress with Lumped 12-B
Mass and Partial Boom Excluded
Figure 13-B Node Connection 313 Stresses with Fastener 13-B
Tension Lumped Mass and Partial Boom
Figure 14-B Node Connection 26 Stresses with Lumped 14-B
Mass and Partial Boom Excluded
Figure 15-B Node Connection 26 Stresses with Fastener 15-B
Tension Lumped Mass and Partial Boom Excluded
Table 1 Moment Results for all Cantilever Beam 9
Lumped Mass Models
Table 2 Comparison of Moments Results for all 13
Lumped Mass Models
iv
ABSTRACT
The four connections for the control dewar and VLPC bayonet can platform are
designed using finite element analysis to carry all dead weight and live loads Based on
the loads applied to the platform two 1 inch thick plates and two 34 inch thick brackets
made of ASTM A572middotGrade 42 are required The 1 inch thick plate requires a 3S inch
thick intermediate steel material between the Sx4x14 boom and the plate for load
reinforcement as well as weld area reinforcement Both the plates and the brackets
require 34 inch steel bolt connections
v
INTRODUCTION
The new solenoid which just arrived from Japan will be tested while the detector
is positioned outside the collision hall to assure that the solenoid operates correctly before
it is rolled back into the collision hall In order for these tests to begin the proper
cryogenics must be made available The components needed to operate the solenoid are a
control dewar vacuum pump and controllers All of these components along with a
VLPC bayonet can have been designated to sit on a platform which will be mounted onto
the cryobridge The cryobridge is essentially a rectangular column that houses cryogenic
piping and runs around the perimeter of the detector The focus of this report is the
platform connections
First the load estimates due to the above components are considered Second
the platform dimensional outline and the loads as applied to the platform structure are
presented Third the reaction forces and moments generated by a fmite element analysis
are presented for all four connection points Once these three steps are complete the
platform connection design begins
The platform connection designs start by frrst explaining the initial conditions
governing the design Second the design analysis method is presented Third the
tgtlatform connection design is presented And fmally the recommendations for the
connections the bolt patterns and the weld calculations are presented
2
INITIAL CONDITONS
The platfonn design begins with a load analysis which is based on the
components mounted on the platfonn as seen in Appendix A This section of the
analysis specifies the platfonn dimensions and the type of structural material chosen
Page A3 is the dimensional outline of the platfonn structure consisting of 2x 4x 316
and 4x 8x 114 rectangular tubing After these types of tubing were chosen the loads
were distributed as seen on page A4 This model is then entered into the computer and a
fmite element analysis (PEA) is perfonned A fmite element analysis is an approximate
method for calculating the behavior of the real structure Points A B C and D on the
model are considered the connection points of the platfonn The results from the FEA are
shown on page AS where the reaction forces and moments are drawn at all four
connection points In order to maintain continuity with the FEA model the connection
points will no longer be labeled A B C D but will rather be designated as nodes 1 26
313 and 288 due to the meshing process generated by the computer Page A6 shows the
assigned nodes in a simple wireframe sketch and presents the reaction forces and
moments in table fonn at the top of the page
I Appendix A authored by Russell Rucinski Mechanical Engineer
3
METHOD OF ANALYSIS
The analysis required for the four connections involves analyzing the forces acting
on the connections as well as the moments acting on those connections Therefore the
correct analysis must include both reactions SORC I-DEAS 3-D modeling has been
chosen to perform the fmite element analysis However a limitation arises in that this
software does not allow for a direct application of a moment onto a solid part Since I am
modeling all four connections as solid parts I must devise a method that allows me to
completely and correctly model my connections I experimented with numerous elements
and meshing techniques in order to fmd the best analysis method I also consulted with
SORe After trying various techniques I found a method that yielded acceptable
solutions This method will be called the lumped mass model The lumped mass model
allows for a moment to be applied to solid and the creation of this lumped mass model is
outlined in How to Create Moments on a Solid The outline is written in SORe 1shy
OEAS commands and is presented on the following page
Lumped Mass Model
The lumped mass model begins by creating a structure which is also referred to as
a solid part The structure is then meshed where the meshing process involves
subdividing the structure into nodes and finite elements in order to perform fmite element
analysis A fmite element is a discrete entity used to subdivide the geometry of the
structure and each element is a simple shape such as rectangle or a triangle The number
of fmite elements created is determined by the shape and size of the elements This in
tum determines the number and location of the nodes In a fmite element model nodes
are the points where the elements are connected The nodes are what is needed to
continue the development of the lumped mass model
The moment application process begins by choosing a node on the surface of the
structure near the location where the moment is to be applied The selected node is then
copied at some distance away from the structures surface The distance chosen is
irrelevant since the lumped mass model translates the forces directly to the surface and
4
does not require a moment arm length This new node is designated as the lumped mass
and allows for six degrees of freedom(OOF)
5
Constraint Elements
Now that the lumped mass is created it must be constrained to the surface of the
structure Constraining the lumped mass to the structure allows the moment which is
applied to the lumped mass to translate to the structure The leading candidate for
constraint is a constraint element A constraint element connects a single node to a set of
nodes and transmits all translational and rotational forces from the single node to the set
of nodes chosen Thus the constraint element originates from the lumped mass and
connects to the elements on the surface of structure thereby translating the moment
acting on the lumped mass to the elements on the surface of the structure However in
order to transmit the moment from the elements on the surface of the structure to the
elements making up the entire structure the elements on the surface must have six
degrees of freedom as well
Thin Shell Coating
Thin shell coating has been chosen to transmit the moment from the elements on
the surface of the structure to the elements making up the entire structure The thin shell
coating perfonned on the surface of the structure is done for two reasons First it is used
to change the elements on the specified surface from three DOF elements to six DOF
elements This allows for the transmission of the moment from the lumped mass through
the constraint elements to the elements on the surface where the elements on the surface
can now accept rotational degrees of freedom as well as translational degrees of freedom
Second the thin shell coating method provides for the transmission of the moment
throughout the entire structure Since the structure already consists of elements that are
similar in size and shape any force or moment applied to one element will automatically
transmit that same force or moment to adjoining elements Thus by creating a thin shell
coating on the surface of the structure I am allowing the surface elements to receive force
and moment reactions which are in tum transmitted to all the elements in the structure
However there is one precaution that must be mentioned
6
Precaution
The constraint elements used to constrain the lumped mass to the elements on the
surface of the structure create a dissimilar mesh between This occurs because the
geometry of the elements on the surface of the structure are different fonn the geometry
of the constraint elements According to I-DEAS Creating Elements with Special
TechniQues the precaution for joining dissimilar meshes is that the results for any
elements near [this] mesh interface should be suspect In order to avoid suspect results
for elements near the mesh interface these elements are not selected for display during
post processing
7
CANTILEVER BEAM ANALYSIS
In order to validate the lumped mass method results I created several cantilever
beam models First I modeled a cantilever beam as seen below in Fig 1 The cantilever
beam is 10 x 2 x I and is made of steel The left end of the beam is held rigid while a
10000 in-lb moment is applied to the other end acting in the z-direction The resulting
bending stress should be a maximum at 15 ksi based on static calculations where the
moment is the force multiplied by the distance and the bending stress is the moment
multiplied by the distance from the neutral axis to the outer most fiber divided by the
moment of inertia COb - ~c) The results from the ftnite element analysis (FEA) are
15 ksi which agrees with the calculated bending stress of 15 ksi
M
Fig 1 Cantilever Beam 1 0x2x 1 Fig 2 Cantilever Beam lOx2xl with 1 0000 in-lb Moment Applied with Extension and Lumped
Mass Applied
The second cantilever beam model Fig 2 begins with the same dimensions used
in Fig 1 but now there is an additional beam section which extends off the end of the
cantilever beam The additional material allows me to (1) avoid suspect results near the
mesh interface and (2) post process the original cantilever beam section Now I can
constrain the lumped mass where the 10000 in-lb moment in the z-direction is applied
to the surface of the additional material Thus when I post process my model to
determine the maximum stress I can chose to post process only a portion of the extended
8
material This allows me to avoid the suspect results completely while still incorporating
the effects of the moment applied to the lumped mass
The results from the lumped mass method as applied to the cantilever beam are
shown in Table 1 The first maximum Von Mises stress for the cantilever beam 15 ksi
is the theoretical stress which all the models should predict I used this theoretical stress
as comparison for all the cantilever beam models tested
I post processed the second model of the cantilever beam which includes the
extended beam section and the lumped mass interface Figure I-B in Appendix B shows
that this maximum Von Mises stress is 29 ksi a stress that is 9333 higher than the
theoretical stress This result is precaution mentioned early stating that the results for
any elements near a mesh interface should be suspect II And as cautioned the high
stresses occur at the mesh interface
For the third model I post processed only a portion of the extended beam section
and excluded the lumped mass interface as seen in Fig 2-B The maximum Von Mises
stress dropped to 24 ksi With this post processing method I have been able to minimize
the suspect results near the mesh interface and the maximum Von Mises stress is now
only 60 higher than the theoretical stress However the true shape of the cantilever
beam must be analyzed as closely as possible Thus I post processed a fourth model
The fourth model eliminates the entire extended beam section on the side of the
applied moment as seen in Fig 3-B The result is a maximum Von Mises stress of 176
ksi This maximum Von Mises stress is only 1733 higher than the theoretical
maximum stress of 15 ksi
I used a fifth model to determine whether or not the extended beam section on the
opposite side of the lumped mass affects the results Figure 4-B shows the maximum
Von Mises stress for the fifth post processed model which post processes only the
original cantilever beam The stress remained the same at a maximum at 176 ksi
TABLE 1 Moment Resuhs for all Cantilever Beam Lumped Mass Models
PART CONDITION MAX VON MISES STRESS (ksi)
DIFFERENCE FROM THEORETICAL
Cantilever Beam 1 0 000 in-Ib moment applied to end of beam 15 0 With lumped Mass and Extensions 29 9333 Without lumped Mass 24 6000 Without Elements on lumped Mass Side 176 1733 Without lumped Mass and Extensions 176 1733
0
10
CANTILEVER BEAM RESULTS
From the cantilever beam models I found that the lumped mass model produces a
stress that is conservatively higher than that of the theoretical stress value Therefore this
method will only increase the factor of safety in my design Thus I will proceed with the
method of adding material to the original design then applying a lumped mass to the
additional material and fmally post processing only the original shape of the platform
connections
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
I
I I
j i D (- TYP (__________________l~==_L_________________l Ii) I
i ~
I
middot I
I
bullI I middotbullbull bull
iI I
t-------------fr-----------middot---shy I
middotmiddot middot
middot I
bull I -A shy I
I middot IL_ -fI
~-----------------i t-
I bull
DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
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CVLf( BON~ Z ~T 500] 14
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p~~a8~3 J Amiddot2ENGINEERING NOTE
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o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
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APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
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Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
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I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
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286
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AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
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dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
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Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
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RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
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l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
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dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
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t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
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F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
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Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
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Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
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NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
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BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
ABSTRACT
The four connections for the control dewar and VLPC bayonet can platform are
designed using finite element analysis to carry all dead weight and live loads Based on
the loads applied to the platform two 1 inch thick plates and two 34 inch thick brackets
made of ASTM A572middotGrade 42 are required The 1 inch thick plate requires a 3S inch
thick intermediate steel material between the Sx4x14 boom and the plate for load
reinforcement as well as weld area reinforcement Both the plates and the brackets
require 34 inch steel bolt connections
v
INTRODUCTION
The new solenoid which just arrived from Japan will be tested while the detector
is positioned outside the collision hall to assure that the solenoid operates correctly before
it is rolled back into the collision hall In order for these tests to begin the proper
cryogenics must be made available The components needed to operate the solenoid are a
control dewar vacuum pump and controllers All of these components along with a
VLPC bayonet can have been designated to sit on a platform which will be mounted onto
the cryobridge The cryobridge is essentially a rectangular column that houses cryogenic
piping and runs around the perimeter of the detector The focus of this report is the
platform connections
First the load estimates due to the above components are considered Second
the platform dimensional outline and the loads as applied to the platform structure are
presented Third the reaction forces and moments generated by a fmite element analysis
are presented for all four connection points Once these three steps are complete the
platform connection design begins
The platform connection designs start by frrst explaining the initial conditions
governing the design Second the design analysis method is presented Third the
tgtlatform connection design is presented And fmally the recommendations for the
connections the bolt patterns and the weld calculations are presented
2
INITIAL CONDITONS
The platfonn design begins with a load analysis which is based on the
components mounted on the platfonn as seen in Appendix A This section of the
analysis specifies the platfonn dimensions and the type of structural material chosen
Page A3 is the dimensional outline of the platfonn structure consisting of 2x 4x 316
and 4x 8x 114 rectangular tubing After these types of tubing were chosen the loads
were distributed as seen on page A4 This model is then entered into the computer and a
fmite element analysis (PEA) is perfonned A fmite element analysis is an approximate
method for calculating the behavior of the real structure Points A B C and D on the
model are considered the connection points of the platfonn The results from the FEA are
shown on page AS where the reaction forces and moments are drawn at all four
connection points In order to maintain continuity with the FEA model the connection
points will no longer be labeled A B C D but will rather be designated as nodes 1 26
313 and 288 due to the meshing process generated by the computer Page A6 shows the
assigned nodes in a simple wireframe sketch and presents the reaction forces and
moments in table fonn at the top of the page
I Appendix A authored by Russell Rucinski Mechanical Engineer
3
METHOD OF ANALYSIS
The analysis required for the four connections involves analyzing the forces acting
on the connections as well as the moments acting on those connections Therefore the
correct analysis must include both reactions SORC I-DEAS 3-D modeling has been
chosen to perform the fmite element analysis However a limitation arises in that this
software does not allow for a direct application of a moment onto a solid part Since I am
modeling all four connections as solid parts I must devise a method that allows me to
completely and correctly model my connections I experimented with numerous elements
and meshing techniques in order to fmd the best analysis method I also consulted with
SORe After trying various techniques I found a method that yielded acceptable
solutions This method will be called the lumped mass model The lumped mass model
allows for a moment to be applied to solid and the creation of this lumped mass model is
outlined in How to Create Moments on a Solid The outline is written in SORe 1shy
OEAS commands and is presented on the following page
Lumped Mass Model
The lumped mass model begins by creating a structure which is also referred to as
a solid part The structure is then meshed where the meshing process involves
subdividing the structure into nodes and finite elements in order to perform fmite element
analysis A fmite element is a discrete entity used to subdivide the geometry of the
structure and each element is a simple shape such as rectangle or a triangle The number
of fmite elements created is determined by the shape and size of the elements This in
tum determines the number and location of the nodes In a fmite element model nodes
are the points where the elements are connected The nodes are what is needed to
continue the development of the lumped mass model
The moment application process begins by choosing a node on the surface of the
structure near the location where the moment is to be applied The selected node is then
copied at some distance away from the structures surface The distance chosen is
irrelevant since the lumped mass model translates the forces directly to the surface and
4
does not require a moment arm length This new node is designated as the lumped mass
and allows for six degrees of freedom(OOF)
5
Constraint Elements
Now that the lumped mass is created it must be constrained to the surface of the
structure Constraining the lumped mass to the structure allows the moment which is
applied to the lumped mass to translate to the structure The leading candidate for
constraint is a constraint element A constraint element connects a single node to a set of
nodes and transmits all translational and rotational forces from the single node to the set
of nodes chosen Thus the constraint element originates from the lumped mass and
connects to the elements on the surface of structure thereby translating the moment
acting on the lumped mass to the elements on the surface of the structure However in
order to transmit the moment from the elements on the surface of the structure to the
elements making up the entire structure the elements on the surface must have six
degrees of freedom as well
Thin Shell Coating
Thin shell coating has been chosen to transmit the moment from the elements on
the surface of the structure to the elements making up the entire structure The thin shell
coating perfonned on the surface of the structure is done for two reasons First it is used
to change the elements on the specified surface from three DOF elements to six DOF
elements This allows for the transmission of the moment from the lumped mass through
the constraint elements to the elements on the surface where the elements on the surface
can now accept rotational degrees of freedom as well as translational degrees of freedom
Second the thin shell coating method provides for the transmission of the moment
throughout the entire structure Since the structure already consists of elements that are
similar in size and shape any force or moment applied to one element will automatically
transmit that same force or moment to adjoining elements Thus by creating a thin shell
coating on the surface of the structure I am allowing the surface elements to receive force
and moment reactions which are in tum transmitted to all the elements in the structure
However there is one precaution that must be mentioned
6
Precaution
The constraint elements used to constrain the lumped mass to the elements on the
surface of the structure create a dissimilar mesh between This occurs because the
geometry of the elements on the surface of the structure are different fonn the geometry
of the constraint elements According to I-DEAS Creating Elements with Special
TechniQues the precaution for joining dissimilar meshes is that the results for any
elements near [this] mesh interface should be suspect In order to avoid suspect results
for elements near the mesh interface these elements are not selected for display during
post processing
7
CANTILEVER BEAM ANALYSIS
In order to validate the lumped mass method results I created several cantilever
beam models First I modeled a cantilever beam as seen below in Fig 1 The cantilever
beam is 10 x 2 x I and is made of steel The left end of the beam is held rigid while a
10000 in-lb moment is applied to the other end acting in the z-direction The resulting
bending stress should be a maximum at 15 ksi based on static calculations where the
moment is the force multiplied by the distance and the bending stress is the moment
multiplied by the distance from the neutral axis to the outer most fiber divided by the
moment of inertia COb - ~c) The results from the ftnite element analysis (FEA) are
15 ksi which agrees with the calculated bending stress of 15 ksi
M
Fig 1 Cantilever Beam 1 0x2x 1 Fig 2 Cantilever Beam lOx2xl with 1 0000 in-lb Moment Applied with Extension and Lumped
Mass Applied
The second cantilever beam model Fig 2 begins with the same dimensions used
in Fig 1 but now there is an additional beam section which extends off the end of the
cantilever beam The additional material allows me to (1) avoid suspect results near the
mesh interface and (2) post process the original cantilever beam section Now I can
constrain the lumped mass where the 10000 in-lb moment in the z-direction is applied
to the surface of the additional material Thus when I post process my model to
determine the maximum stress I can chose to post process only a portion of the extended
8
material This allows me to avoid the suspect results completely while still incorporating
the effects of the moment applied to the lumped mass
The results from the lumped mass method as applied to the cantilever beam are
shown in Table 1 The first maximum Von Mises stress for the cantilever beam 15 ksi
is the theoretical stress which all the models should predict I used this theoretical stress
as comparison for all the cantilever beam models tested
I post processed the second model of the cantilever beam which includes the
extended beam section and the lumped mass interface Figure I-B in Appendix B shows
that this maximum Von Mises stress is 29 ksi a stress that is 9333 higher than the
theoretical stress This result is precaution mentioned early stating that the results for
any elements near a mesh interface should be suspect II And as cautioned the high
stresses occur at the mesh interface
For the third model I post processed only a portion of the extended beam section
and excluded the lumped mass interface as seen in Fig 2-B The maximum Von Mises
stress dropped to 24 ksi With this post processing method I have been able to minimize
the suspect results near the mesh interface and the maximum Von Mises stress is now
only 60 higher than the theoretical stress However the true shape of the cantilever
beam must be analyzed as closely as possible Thus I post processed a fourth model
The fourth model eliminates the entire extended beam section on the side of the
applied moment as seen in Fig 3-B The result is a maximum Von Mises stress of 176
ksi This maximum Von Mises stress is only 1733 higher than the theoretical
maximum stress of 15 ksi
I used a fifth model to determine whether or not the extended beam section on the
opposite side of the lumped mass affects the results Figure 4-B shows the maximum
Von Mises stress for the fifth post processed model which post processes only the
original cantilever beam The stress remained the same at a maximum at 176 ksi
TABLE 1 Moment Resuhs for all Cantilever Beam Lumped Mass Models
PART CONDITION MAX VON MISES STRESS (ksi)
DIFFERENCE FROM THEORETICAL
Cantilever Beam 1 0 000 in-Ib moment applied to end of beam 15 0 With lumped Mass and Extensions 29 9333 Without lumped Mass 24 6000 Without Elements on lumped Mass Side 176 1733 Without lumped Mass and Extensions 176 1733
0
10
CANTILEVER BEAM RESULTS
From the cantilever beam models I found that the lumped mass model produces a
stress that is conservatively higher than that of the theoretical stress value Therefore this
method will only increase the factor of safety in my design Thus I will proceed with the
method of adding material to the original design then applying a lumped mass to the
additional material and fmally post processing only the original shape of the platform
connections
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
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I 224 TYP ~ 250
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LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
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20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
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200 TYP
~
8 00 TYP --l
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320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
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ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
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Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
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dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
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jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
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240E+03
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RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
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3S2E+03
176E+03
226E-Ol
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176E+04
15BE+04
141E+04
123E+04
l06E+04
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3S2E+03
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226E-Ol
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RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
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STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
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257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
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QJ
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RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
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dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
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dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
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60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
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a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
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109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
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B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
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951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
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24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
INTRODUCTION
The new solenoid which just arrived from Japan will be tested while the detector
is positioned outside the collision hall to assure that the solenoid operates correctly before
it is rolled back into the collision hall In order for these tests to begin the proper
cryogenics must be made available The components needed to operate the solenoid are a
control dewar vacuum pump and controllers All of these components along with a
VLPC bayonet can have been designated to sit on a platform which will be mounted onto
the cryobridge The cryobridge is essentially a rectangular column that houses cryogenic
piping and runs around the perimeter of the detector The focus of this report is the
platform connections
First the load estimates due to the above components are considered Second
the platform dimensional outline and the loads as applied to the platform structure are
presented Third the reaction forces and moments generated by a fmite element analysis
are presented for all four connection points Once these three steps are complete the
platform connection design begins
The platform connection designs start by frrst explaining the initial conditions
governing the design Second the design analysis method is presented Third the
tgtlatform connection design is presented And fmally the recommendations for the
connections the bolt patterns and the weld calculations are presented
2
INITIAL CONDITONS
The platfonn design begins with a load analysis which is based on the
components mounted on the platfonn as seen in Appendix A This section of the
analysis specifies the platfonn dimensions and the type of structural material chosen
Page A3 is the dimensional outline of the platfonn structure consisting of 2x 4x 316
and 4x 8x 114 rectangular tubing After these types of tubing were chosen the loads
were distributed as seen on page A4 This model is then entered into the computer and a
fmite element analysis (PEA) is perfonned A fmite element analysis is an approximate
method for calculating the behavior of the real structure Points A B C and D on the
model are considered the connection points of the platfonn The results from the FEA are
shown on page AS where the reaction forces and moments are drawn at all four
connection points In order to maintain continuity with the FEA model the connection
points will no longer be labeled A B C D but will rather be designated as nodes 1 26
313 and 288 due to the meshing process generated by the computer Page A6 shows the
assigned nodes in a simple wireframe sketch and presents the reaction forces and
moments in table fonn at the top of the page
I Appendix A authored by Russell Rucinski Mechanical Engineer
3
METHOD OF ANALYSIS
The analysis required for the four connections involves analyzing the forces acting
on the connections as well as the moments acting on those connections Therefore the
correct analysis must include both reactions SORC I-DEAS 3-D modeling has been
chosen to perform the fmite element analysis However a limitation arises in that this
software does not allow for a direct application of a moment onto a solid part Since I am
modeling all four connections as solid parts I must devise a method that allows me to
completely and correctly model my connections I experimented with numerous elements
and meshing techniques in order to fmd the best analysis method I also consulted with
SORe After trying various techniques I found a method that yielded acceptable
solutions This method will be called the lumped mass model The lumped mass model
allows for a moment to be applied to solid and the creation of this lumped mass model is
outlined in How to Create Moments on a Solid The outline is written in SORe 1shy
OEAS commands and is presented on the following page
Lumped Mass Model
The lumped mass model begins by creating a structure which is also referred to as
a solid part The structure is then meshed where the meshing process involves
subdividing the structure into nodes and finite elements in order to perform fmite element
analysis A fmite element is a discrete entity used to subdivide the geometry of the
structure and each element is a simple shape such as rectangle or a triangle The number
of fmite elements created is determined by the shape and size of the elements This in
tum determines the number and location of the nodes In a fmite element model nodes
are the points where the elements are connected The nodes are what is needed to
continue the development of the lumped mass model
The moment application process begins by choosing a node on the surface of the
structure near the location where the moment is to be applied The selected node is then
copied at some distance away from the structures surface The distance chosen is
irrelevant since the lumped mass model translates the forces directly to the surface and
4
does not require a moment arm length This new node is designated as the lumped mass
and allows for six degrees of freedom(OOF)
5
Constraint Elements
Now that the lumped mass is created it must be constrained to the surface of the
structure Constraining the lumped mass to the structure allows the moment which is
applied to the lumped mass to translate to the structure The leading candidate for
constraint is a constraint element A constraint element connects a single node to a set of
nodes and transmits all translational and rotational forces from the single node to the set
of nodes chosen Thus the constraint element originates from the lumped mass and
connects to the elements on the surface of structure thereby translating the moment
acting on the lumped mass to the elements on the surface of the structure However in
order to transmit the moment from the elements on the surface of the structure to the
elements making up the entire structure the elements on the surface must have six
degrees of freedom as well
Thin Shell Coating
Thin shell coating has been chosen to transmit the moment from the elements on
the surface of the structure to the elements making up the entire structure The thin shell
coating perfonned on the surface of the structure is done for two reasons First it is used
to change the elements on the specified surface from three DOF elements to six DOF
elements This allows for the transmission of the moment from the lumped mass through
the constraint elements to the elements on the surface where the elements on the surface
can now accept rotational degrees of freedom as well as translational degrees of freedom
Second the thin shell coating method provides for the transmission of the moment
throughout the entire structure Since the structure already consists of elements that are
similar in size and shape any force or moment applied to one element will automatically
transmit that same force or moment to adjoining elements Thus by creating a thin shell
coating on the surface of the structure I am allowing the surface elements to receive force
and moment reactions which are in tum transmitted to all the elements in the structure
However there is one precaution that must be mentioned
6
Precaution
The constraint elements used to constrain the lumped mass to the elements on the
surface of the structure create a dissimilar mesh between This occurs because the
geometry of the elements on the surface of the structure are different fonn the geometry
of the constraint elements According to I-DEAS Creating Elements with Special
TechniQues the precaution for joining dissimilar meshes is that the results for any
elements near [this] mesh interface should be suspect In order to avoid suspect results
for elements near the mesh interface these elements are not selected for display during
post processing
7
CANTILEVER BEAM ANALYSIS
In order to validate the lumped mass method results I created several cantilever
beam models First I modeled a cantilever beam as seen below in Fig 1 The cantilever
beam is 10 x 2 x I and is made of steel The left end of the beam is held rigid while a
10000 in-lb moment is applied to the other end acting in the z-direction The resulting
bending stress should be a maximum at 15 ksi based on static calculations where the
moment is the force multiplied by the distance and the bending stress is the moment
multiplied by the distance from the neutral axis to the outer most fiber divided by the
moment of inertia COb - ~c) The results from the ftnite element analysis (FEA) are
15 ksi which agrees with the calculated bending stress of 15 ksi
M
Fig 1 Cantilever Beam 1 0x2x 1 Fig 2 Cantilever Beam lOx2xl with 1 0000 in-lb Moment Applied with Extension and Lumped
Mass Applied
The second cantilever beam model Fig 2 begins with the same dimensions used
in Fig 1 but now there is an additional beam section which extends off the end of the
cantilever beam The additional material allows me to (1) avoid suspect results near the
mesh interface and (2) post process the original cantilever beam section Now I can
constrain the lumped mass where the 10000 in-lb moment in the z-direction is applied
to the surface of the additional material Thus when I post process my model to
determine the maximum stress I can chose to post process only a portion of the extended
8
material This allows me to avoid the suspect results completely while still incorporating
the effects of the moment applied to the lumped mass
The results from the lumped mass method as applied to the cantilever beam are
shown in Table 1 The first maximum Von Mises stress for the cantilever beam 15 ksi
is the theoretical stress which all the models should predict I used this theoretical stress
as comparison for all the cantilever beam models tested
I post processed the second model of the cantilever beam which includes the
extended beam section and the lumped mass interface Figure I-B in Appendix B shows
that this maximum Von Mises stress is 29 ksi a stress that is 9333 higher than the
theoretical stress This result is precaution mentioned early stating that the results for
any elements near a mesh interface should be suspect II And as cautioned the high
stresses occur at the mesh interface
For the third model I post processed only a portion of the extended beam section
and excluded the lumped mass interface as seen in Fig 2-B The maximum Von Mises
stress dropped to 24 ksi With this post processing method I have been able to minimize
the suspect results near the mesh interface and the maximum Von Mises stress is now
only 60 higher than the theoretical stress However the true shape of the cantilever
beam must be analyzed as closely as possible Thus I post processed a fourth model
The fourth model eliminates the entire extended beam section on the side of the
applied moment as seen in Fig 3-B The result is a maximum Von Mises stress of 176
ksi This maximum Von Mises stress is only 1733 higher than the theoretical
maximum stress of 15 ksi
I used a fifth model to determine whether or not the extended beam section on the
opposite side of the lumped mass affects the results Figure 4-B shows the maximum
Von Mises stress for the fifth post processed model which post processes only the
original cantilever beam The stress remained the same at a maximum at 176 ksi
TABLE 1 Moment Resuhs for all Cantilever Beam Lumped Mass Models
PART CONDITION MAX VON MISES STRESS (ksi)
DIFFERENCE FROM THEORETICAL
Cantilever Beam 1 0 000 in-Ib moment applied to end of beam 15 0 With lumped Mass and Extensions 29 9333 Without lumped Mass 24 6000 Without Elements on lumped Mass Side 176 1733 Without lumped Mass and Extensions 176 1733
0
10
CANTILEVER BEAM RESULTS
From the cantilever beam models I found that the lumped mass model produces a
stress that is conservatively higher than that of the theoretical stress value Therefore this
method will only increase the factor of safety in my design Thus I will proceed with the
method of adding material to the original design then applying a lumped mass to the
additional material and fmally post processing only the original shape of the platform
connections
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
I
I I
j i D (- TYP (__________________l~==_L_________________l Ii) I
i ~
I
middot I
I
bullI I middotbullbull bull
iI I
t-------------fr-----------middot---shy I
middotmiddot middot
middot I
bull I -A shy I
I middot IL_ -fI
~-----------------i t-
I bull
DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
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VAtshy vUSC - 631+lshy20 ~ bullis Pt 30
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(Zo)L ~ )~ Z + (75 + 11 (Ugt 30)(106
=- ~ 2 + 3 Cj t i IAIgt 8gt2S tA)
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- AoO u-TIJt~ IJJ TIlft~ 9PE~)~ 1IP eELOW- b ~ S 10
CVLf( BON~ Z ~T 500] 14
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p~~a8~3 J Amiddot2ENGINEERING NOTE
PLA 4=Q 2vt DeS I 6rJ cA -c~
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o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
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125
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APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
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1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
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I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
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tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
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CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
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Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
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dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
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l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
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jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
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dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
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F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
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Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
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dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
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24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
2
INITIAL CONDITONS
The platfonn design begins with a load analysis which is based on the
components mounted on the platfonn as seen in Appendix A This section of the
analysis specifies the platfonn dimensions and the type of structural material chosen
Page A3 is the dimensional outline of the platfonn structure consisting of 2x 4x 316
and 4x 8x 114 rectangular tubing After these types of tubing were chosen the loads
were distributed as seen on page A4 This model is then entered into the computer and a
fmite element analysis (PEA) is perfonned A fmite element analysis is an approximate
method for calculating the behavior of the real structure Points A B C and D on the
model are considered the connection points of the platfonn The results from the FEA are
shown on page AS where the reaction forces and moments are drawn at all four
connection points In order to maintain continuity with the FEA model the connection
points will no longer be labeled A B C D but will rather be designated as nodes 1 26
313 and 288 due to the meshing process generated by the computer Page A6 shows the
assigned nodes in a simple wireframe sketch and presents the reaction forces and
moments in table fonn at the top of the page
I Appendix A authored by Russell Rucinski Mechanical Engineer
3
METHOD OF ANALYSIS
The analysis required for the four connections involves analyzing the forces acting
on the connections as well as the moments acting on those connections Therefore the
correct analysis must include both reactions SORC I-DEAS 3-D modeling has been
chosen to perform the fmite element analysis However a limitation arises in that this
software does not allow for a direct application of a moment onto a solid part Since I am
modeling all four connections as solid parts I must devise a method that allows me to
completely and correctly model my connections I experimented with numerous elements
and meshing techniques in order to fmd the best analysis method I also consulted with
SORe After trying various techniques I found a method that yielded acceptable
solutions This method will be called the lumped mass model The lumped mass model
allows for a moment to be applied to solid and the creation of this lumped mass model is
outlined in How to Create Moments on a Solid The outline is written in SORe 1shy
OEAS commands and is presented on the following page
Lumped Mass Model
The lumped mass model begins by creating a structure which is also referred to as
a solid part The structure is then meshed where the meshing process involves
subdividing the structure into nodes and finite elements in order to perform fmite element
analysis A fmite element is a discrete entity used to subdivide the geometry of the
structure and each element is a simple shape such as rectangle or a triangle The number
of fmite elements created is determined by the shape and size of the elements This in
tum determines the number and location of the nodes In a fmite element model nodes
are the points where the elements are connected The nodes are what is needed to
continue the development of the lumped mass model
The moment application process begins by choosing a node on the surface of the
structure near the location where the moment is to be applied The selected node is then
copied at some distance away from the structures surface The distance chosen is
irrelevant since the lumped mass model translates the forces directly to the surface and
4
does not require a moment arm length This new node is designated as the lumped mass
and allows for six degrees of freedom(OOF)
5
Constraint Elements
Now that the lumped mass is created it must be constrained to the surface of the
structure Constraining the lumped mass to the structure allows the moment which is
applied to the lumped mass to translate to the structure The leading candidate for
constraint is a constraint element A constraint element connects a single node to a set of
nodes and transmits all translational and rotational forces from the single node to the set
of nodes chosen Thus the constraint element originates from the lumped mass and
connects to the elements on the surface of structure thereby translating the moment
acting on the lumped mass to the elements on the surface of the structure However in
order to transmit the moment from the elements on the surface of the structure to the
elements making up the entire structure the elements on the surface must have six
degrees of freedom as well
Thin Shell Coating
Thin shell coating has been chosen to transmit the moment from the elements on
the surface of the structure to the elements making up the entire structure The thin shell
coating perfonned on the surface of the structure is done for two reasons First it is used
to change the elements on the specified surface from three DOF elements to six DOF
elements This allows for the transmission of the moment from the lumped mass through
the constraint elements to the elements on the surface where the elements on the surface
can now accept rotational degrees of freedom as well as translational degrees of freedom
Second the thin shell coating method provides for the transmission of the moment
throughout the entire structure Since the structure already consists of elements that are
similar in size and shape any force or moment applied to one element will automatically
transmit that same force or moment to adjoining elements Thus by creating a thin shell
coating on the surface of the structure I am allowing the surface elements to receive force
and moment reactions which are in tum transmitted to all the elements in the structure
However there is one precaution that must be mentioned
6
Precaution
The constraint elements used to constrain the lumped mass to the elements on the
surface of the structure create a dissimilar mesh between This occurs because the
geometry of the elements on the surface of the structure are different fonn the geometry
of the constraint elements According to I-DEAS Creating Elements with Special
TechniQues the precaution for joining dissimilar meshes is that the results for any
elements near [this] mesh interface should be suspect In order to avoid suspect results
for elements near the mesh interface these elements are not selected for display during
post processing
7
CANTILEVER BEAM ANALYSIS
In order to validate the lumped mass method results I created several cantilever
beam models First I modeled a cantilever beam as seen below in Fig 1 The cantilever
beam is 10 x 2 x I and is made of steel The left end of the beam is held rigid while a
10000 in-lb moment is applied to the other end acting in the z-direction The resulting
bending stress should be a maximum at 15 ksi based on static calculations where the
moment is the force multiplied by the distance and the bending stress is the moment
multiplied by the distance from the neutral axis to the outer most fiber divided by the
moment of inertia COb - ~c) The results from the ftnite element analysis (FEA) are
15 ksi which agrees with the calculated bending stress of 15 ksi
M
Fig 1 Cantilever Beam 1 0x2x 1 Fig 2 Cantilever Beam lOx2xl with 1 0000 in-lb Moment Applied with Extension and Lumped
Mass Applied
The second cantilever beam model Fig 2 begins with the same dimensions used
in Fig 1 but now there is an additional beam section which extends off the end of the
cantilever beam The additional material allows me to (1) avoid suspect results near the
mesh interface and (2) post process the original cantilever beam section Now I can
constrain the lumped mass where the 10000 in-lb moment in the z-direction is applied
to the surface of the additional material Thus when I post process my model to
determine the maximum stress I can chose to post process only a portion of the extended
8
material This allows me to avoid the suspect results completely while still incorporating
the effects of the moment applied to the lumped mass
The results from the lumped mass method as applied to the cantilever beam are
shown in Table 1 The first maximum Von Mises stress for the cantilever beam 15 ksi
is the theoretical stress which all the models should predict I used this theoretical stress
as comparison for all the cantilever beam models tested
I post processed the second model of the cantilever beam which includes the
extended beam section and the lumped mass interface Figure I-B in Appendix B shows
that this maximum Von Mises stress is 29 ksi a stress that is 9333 higher than the
theoretical stress This result is precaution mentioned early stating that the results for
any elements near a mesh interface should be suspect II And as cautioned the high
stresses occur at the mesh interface
For the third model I post processed only a portion of the extended beam section
and excluded the lumped mass interface as seen in Fig 2-B The maximum Von Mises
stress dropped to 24 ksi With this post processing method I have been able to minimize
the suspect results near the mesh interface and the maximum Von Mises stress is now
only 60 higher than the theoretical stress However the true shape of the cantilever
beam must be analyzed as closely as possible Thus I post processed a fourth model
The fourth model eliminates the entire extended beam section on the side of the
applied moment as seen in Fig 3-B The result is a maximum Von Mises stress of 176
ksi This maximum Von Mises stress is only 1733 higher than the theoretical
maximum stress of 15 ksi
I used a fifth model to determine whether or not the extended beam section on the
opposite side of the lumped mass affects the results Figure 4-B shows the maximum
Von Mises stress for the fifth post processed model which post processes only the
original cantilever beam The stress remained the same at a maximum at 176 ksi
TABLE 1 Moment Resuhs for all Cantilever Beam Lumped Mass Models
PART CONDITION MAX VON MISES STRESS (ksi)
DIFFERENCE FROM THEORETICAL
Cantilever Beam 1 0 000 in-Ib moment applied to end of beam 15 0 With lumped Mass and Extensions 29 9333 Without lumped Mass 24 6000 Without Elements on lumped Mass Side 176 1733 Without lumped Mass and Extensions 176 1733
0
10
CANTILEVER BEAM RESULTS
From the cantilever beam models I found that the lumped mass model produces a
stress that is conservatively higher than that of the theoretical stress value Therefore this
method will only increase the factor of safety in my design Thus I will proceed with the
method of adding material to the original design then applying a lumped mass to the
additional material and fmally post processing only the original shape of the platform
connections
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
I
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i ~
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middot I
I
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iI I
t-------------fr-----------middot---shy I
middotmiddot middot
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~-----------------i t-
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DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
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VAtshy vUSC - 631+lshy20 ~ bullis Pt 30
(Ioaamp~)
(Zo)L ~ )~ Z + (75 + 11 (Ugt 30)(106
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CVLf( BON~ Z ~T 500] 14
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p~~a8~3 J Amiddot2ENGINEERING NOTE
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==============-----========-------------------------------- =
o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
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a14E+04
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BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
3
METHOD OF ANALYSIS
The analysis required for the four connections involves analyzing the forces acting
on the connections as well as the moments acting on those connections Therefore the
correct analysis must include both reactions SORC I-DEAS 3-D modeling has been
chosen to perform the fmite element analysis However a limitation arises in that this
software does not allow for a direct application of a moment onto a solid part Since I am
modeling all four connections as solid parts I must devise a method that allows me to
completely and correctly model my connections I experimented with numerous elements
and meshing techniques in order to fmd the best analysis method I also consulted with
SORe After trying various techniques I found a method that yielded acceptable
solutions This method will be called the lumped mass model The lumped mass model
allows for a moment to be applied to solid and the creation of this lumped mass model is
outlined in How to Create Moments on a Solid The outline is written in SORe 1shy
OEAS commands and is presented on the following page
Lumped Mass Model
The lumped mass model begins by creating a structure which is also referred to as
a solid part The structure is then meshed where the meshing process involves
subdividing the structure into nodes and finite elements in order to perform fmite element
analysis A fmite element is a discrete entity used to subdivide the geometry of the
structure and each element is a simple shape such as rectangle or a triangle The number
of fmite elements created is determined by the shape and size of the elements This in
tum determines the number and location of the nodes In a fmite element model nodes
are the points where the elements are connected The nodes are what is needed to
continue the development of the lumped mass model
The moment application process begins by choosing a node on the surface of the
structure near the location where the moment is to be applied The selected node is then
copied at some distance away from the structures surface The distance chosen is
irrelevant since the lumped mass model translates the forces directly to the surface and
4
does not require a moment arm length This new node is designated as the lumped mass
and allows for six degrees of freedom(OOF)
5
Constraint Elements
Now that the lumped mass is created it must be constrained to the surface of the
structure Constraining the lumped mass to the structure allows the moment which is
applied to the lumped mass to translate to the structure The leading candidate for
constraint is a constraint element A constraint element connects a single node to a set of
nodes and transmits all translational and rotational forces from the single node to the set
of nodes chosen Thus the constraint element originates from the lumped mass and
connects to the elements on the surface of structure thereby translating the moment
acting on the lumped mass to the elements on the surface of the structure However in
order to transmit the moment from the elements on the surface of the structure to the
elements making up the entire structure the elements on the surface must have six
degrees of freedom as well
Thin Shell Coating
Thin shell coating has been chosen to transmit the moment from the elements on
the surface of the structure to the elements making up the entire structure The thin shell
coating perfonned on the surface of the structure is done for two reasons First it is used
to change the elements on the specified surface from three DOF elements to six DOF
elements This allows for the transmission of the moment from the lumped mass through
the constraint elements to the elements on the surface where the elements on the surface
can now accept rotational degrees of freedom as well as translational degrees of freedom
Second the thin shell coating method provides for the transmission of the moment
throughout the entire structure Since the structure already consists of elements that are
similar in size and shape any force or moment applied to one element will automatically
transmit that same force or moment to adjoining elements Thus by creating a thin shell
coating on the surface of the structure I am allowing the surface elements to receive force
and moment reactions which are in tum transmitted to all the elements in the structure
However there is one precaution that must be mentioned
6
Precaution
The constraint elements used to constrain the lumped mass to the elements on the
surface of the structure create a dissimilar mesh between This occurs because the
geometry of the elements on the surface of the structure are different fonn the geometry
of the constraint elements According to I-DEAS Creating Elements with Special
TechniQues the precaution for joining dissimilar meshes is that the results for any
elements near [this] mesh interface should be suspect In order to avoid suspect results
for elements near the mesh interface these elements are not selected for display during
post processing
7
CANTILEVER BEAM ANALYSIS
In order to validate the lumped mass method results I created several cantilever
beam models First I modeled a cantilever beam as seen below in Fig 1 The cantilever
beam is 10 x 2 x I and is made of steel The left end of the beam is held rigid while a
10000 in-lb moment is applied to the other end acting in the z-direction The resulting
bending stress should be a maximum at 15 ksi based on static calculations where the
moment is the force multiplied by the distance and the bending stress is the moment
multiplied by the distance from the neutral axis to the outer most fiber divided by the
moment of inertia COb - ~c) The results from the ftnite element analysis (FEA) are
15 ksi which agrees with the calculated bending stress of 15 ksi
M
Fig 1 Cantilever Beam 1 0x2x 1 Fig 2 Cantilever Beam lOx2xl with 1 0000 in-lb Moment Applied with Extension and Lumped
Mass Applied
The second cantilever beam model Fig 2 begins with the same dimensions used
in Fig 1 but now there is an additional beam section which extends off the end of the
cantilever beam The additional material allows me to (1) avoid suspect results near the
mesh interface and (2) post process the original cantilever beam section Now I can
constrain the lumped mass where the 10000 in-lb moment in the z-direction is applied
to the surface of the additional material Thus when I post process my model to
determine the maximum stress I can chose to post process only a portion of the extended
8
material This allows me to avoid the suspect results completely while still incorporating
the effects of the moment applied to the lumped mass
The results from the lumped mass method as applied to the cantilever beam are
shown in Table 1 The first maximum Von Mises stress for the cantilever beam 15 ksi
is the theoretical stress which all the models should predict I used this theoretical stress
as comparison for all the cantilever beam models tested
I post processed the second model of the cantilever beam which includes the
extended beam section and the lumped mass interface Figure I-B in Appendix B shows
that this maximum Von Mises stress is 29 ksi a stress that is 9333 higher than the
theoretical stress This result is precaution mentioned early stating that the results for
any elements near a mesh interface should be suspect II And as cautioned the high
stresses occur at the mesh interface
For the third model I post processed only a portion of the extended beam section
and excluded the lumped mass interface as seen in Fig 2-B The maximum Von Mises
stress dropped to 24 ksi With this post processing method I have been able to minimize
the suspect results near the mesh interface and the maximum Von Mises stress is now
only 60 higher than the theoretical stress However the true shape of the cantilever
beam must be analyzed as closely as possible Thus I post processed a fourth model
The fourth model eliminates the entire extended beam section on the side of the
applied moment as seen in Fig 3-B The result is a maximum Von Mises stress of 176
ksi This maximum Von Mises stress is only 1733 higher than the theoretical
maximum stress of 15 ksi
I used a fifth model to determine whether or not the extended beam section on the
opposite side of the lumped mass affects the results Figure 4-B shows the maximum
Von Mises stress for the fifth post processed model which post processes only the
original cantilever beam The stress remained the same at a maximum at 176 ksi
TABLE 1 Moment Resuhs for all Cantilever Beam Lumped Mass Models
PART CONDITION MAX VON MISES STRESS (ksi)
DIFFERENCE FROM THEORETICAL
Cantilever Beam 1 0 000 in-Ib moment applied to end of beam 15 0 With lumped Mass and Extensions 29 9333 Without lumped Mass 24 6000 Without Elements on lumped Mass Side 176 1733 Without lumped Mass and Extensions 176 1733
0
10
CANTILEVER BEAM RESULTS
From the cantilever beam models I found that the lumped mass model produces a
stress that is conservatively higher than that of the theoretical stress value Therefore this
method will only increase the factor of safety in my design Thus I will proceed with the
method of adding material to the original design then applying a lumped mass to the
additional material and fmally post processing only the original shape of the platform
connections
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
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Figure 3 Assembly of Plate Connection at Nodes 1 and 288
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20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
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p~~a8~3 J Amiddot2ENGINEERING NOTE
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o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
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APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
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1451
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Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
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I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
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CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
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Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
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l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
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jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
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dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
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dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
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dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
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dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
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F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
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a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
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109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
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B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
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VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
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24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
4
does not require a moment arm length This new node is designated as the lumped mass
and allows for six degrees of freedom(OOF)
5
Constraint Elements
Now that the lumped mass is created it must be constrained to the surface of the
structure Constraining the lumped mass to the structure allows the moment which is
applied to the lumped mass to translate to the structure The leading candidate for
constraint is a constraint element A constraint element connects a single node to a set of
nodes and transmits all translational and rotational forces from the single node to the set
of nodes chosen Thus the constraint element originates from the lumped mass and
connects to the elements on the surface of structure thereby translating the moment
acting on the lumped mass to the elements on the surface of the structure However in
order to transmit the moment from the elements on the surface of the structure to the
elements making up the entire structure the elements on the surface must have six
degrees of freedom as well
Thin Shell Coating
Thin shell coating has been chosen to transmit the moment from the elements on
the surface of the structure to the elements making up the entire structure The thin shell
coating perfonned on the surface of the structure is done for two reasons First it is used
to change the elements on the specified surface from three DOF elements to six DOF
elements This allows for the transmission of the moment from the lumped mass through
the constraint elements to the elements on the surface where the elements on the surface
can now accept rotational degrees of freedom as well as translational degrees of freedom
Second the thin shell coating method provides for the transmission of the moment
throughout the entire structure Since the structure already consists of elements that are
similar in size and shape any force or moment applied to one element will automatically
transmit that same force or moment to adjoining elements Thus by creating a thin shell
coating on the surface of the structure I am allowing the surface elements to receive force
and moment reactions which are in tum transmitted to all the elements in the structure
However there is one precaution that must be mentioned
6
Precaution
The constraint elements used to constrain the lumped mass to the elements on the
surface of the structure create a dissimilar mesh between This occurs because the
geometry of the elements on the surface of the structure are different fonn the geometry
of the constraint elements According to I-DEAS Creating Elements with Special
TechniQues the precaution for joining dissimilar meshes is that the results for any
elements near [this] mesh interface should be suspect In order to avoid suspect results
for elements near the mesh interface these elements are not selected for display during
post processing
7
CANTILEVER BEAM ANALYSIS
In order to validate the lumped mass method results I created several cantilever
beam models First I modeled a cantilever beam as seen below in Fig 1 The cantilever
beam is 10 x 2 x I and is made of steel The left end of the beam is held rigid while a
10000 in-lb moment is applied to the other end acting in the z-direction The resulting
bending stress should be a maximum at 15 ksi based on static calculations where the
moment is the force multiplied by the distance and the bending stress is the moment
multiplied by the distance from the neutral axis to the outer most fiber divided by the
moment of inertia COb - ~c) The results from the ftnite element analysis (FEA) are
15 ksi which agrees with the calculated bending stress of 15 ksi
M
Fig 1 Cantilever Beam 1 0x2x 1 Fig 2 Cantilever Beam lOx2xl with 1 0000 in-lb Moment Applied with Extension and Lumped
Mass Applied
The second cantilever beam model Fig 2 begins with the same dimensions used
in Fig 1 but now there is an additional beam section which extends off the end of the
cantilever beam The additional material allows me to (1) avoid suspect results near the
mesh interface and (2) post process the original cantilever beam section Now I can
constrain the lumped mass where the 10000 in-lb moment in the z-direction is applied
to the surface of the additional material Thus when I post process my model to
determine the maximum stress I can chose to post process only a portion of the extended
8
material This allows me to avoid the suspect results completely while still incorporating
the effects of the moment applied to the lumped mass
The results from the lumped mass method as applied to the cantilever beam are
shown in Table 1 The first maximum Von Mises stress for the cantilever beam 15 ksi
is the theoretical stress which all the models should predict I used this theoretical stress
as comparison for all the cantilever beam models tested
I post processed the second model of the cantilever beam which includes the
extended beam section and the lumped mass interface Figure I-B in Appendix B shows
that this maximum Von Mises stress is 29 ksi a stress that is 9333 higher than the
theoretical stress This result is precaution mentioned early stating that the results for
any elements near a mesh interface should be suspect II And as cautioned the high
stresses occur at the mesh interface
For the third model I post processed only a portion of the extended beam section
and excluded the lumped mass interface as seen in Fig 2-B The maximum Von Mises
stress dropped to 24 ksi With this post processing method I have been able to minimize
the suspect results near the mesh interface and the maximum Von Mises stress is now
only 60 higher than the theoretical stress However the true shape of the cantilever
beam must be analyzed as closely as possible Thus I post processed a fourth model
The fourth model eliminates the entire extended beam section on the side of the
applied moment as seen in Fig 3-B The result is a maximum Von Mises stress of 176
ksi This maximum Von Mises stress is only 1733 higher than the theoretical
maximum stress of 15 ksi
I used a fifth model to determine whether or not the extended beam section on the
opposite side of the lumped mass affects the results Figure 4-B shows the maximum
Von Mises stress for the fifth post processed model which post processes only the
original cantilever beam The stress remained the same at a maximum at 176 ksi
TABLE 1 Moment Resuhs for all Cantilever Beam Lumped Mass Models
PART CONDITION MAX VON MISES STRESS (ksi)
DIFFERENCE FROM THEORETICAL
Cantilever Beam 1 0 000 in-Ib moment applied to end of beam 15 0 With lumped Mass and Extensions 29 9333 Without lumped Mass 24 6000 Without Elements on lumped Mass Side 176 1733 Without lumped Mass and Extensions 176 1733
0
10
CANTILEVER BEAM RESULTS
From the cantilever beam models I found that the lumped mass model produces a
stress that is conservatively higher than that of the theoretical stress value Therefore this
method will only increase the factor of safety in my design Thus I will proceed with the
method of adding material to the original design then applying a lumped mass to the
additional material and fmally post processing only the original shape of the platform
connections
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
I
I I
j i D (- TYP (__________________l~==_L_________________l Ii) I
i ~
I
middot I
I
bullI I middotbullbull bull
iI I
t-------------fr-----------middot---shy I
middotmiddot middot
middot I
bull I -A shy I
I middot IL_ -fI
~-----------------i t-
I bull
DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
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CVLf( BON~ Z ~T 500] 14
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p~~a8~3 J Amiddot2ENGINEERING NOTE
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o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
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APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
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Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
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I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
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286
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AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
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dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
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Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
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RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
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l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
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dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
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t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
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F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
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Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
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Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
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NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
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BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
5
Constraint Elements
Now that the lumped mass is created it must be constrained to the surface of the
structure Constraining the lumped mass to the structure allows the moment which is
applied to the lumped mass to translate to the structure The leading candidate for
constraint is a constraint element A constraint element connects a single node to a set of
nodes and transmits all translational and rotational forces from the single node to the set
of nodes chosen Thus the constraint element originates from the lumped mass and
connects to the elements on the surface of structure thereby translating the moment
acting on the lumped mass to the elements on the surface of the structure However in
order to transmit the moment from the elements on the surface of the structure to the
elements making up the entire structure the elements on the surface must have six
degrees of freedom as well
Thin Shell Coating
Thin shell coating has been chosen to transmit the moment from the elements on
the surface of the structure to the elements making up the entire structure The thin shell
coating perfonned on the surface of the structure is done for two reasons First it is used
to change the elements on the specified surface from three DOF elements to six DOF
elements This allows for the transmission of the moment from the lumped mass through
the constraint elements to the elements on the surface where the elements on the surface
can now accept rotational degrees of freedom as well as translational degrees of freedom
Second the thin shell coating method provides for the transmission of the moment
throughout the entire structure Since the structure already consists of elements that are
similar in size and shape any force or moment applied to one element will automatically
transmit that same force or moment to adjoining elements Thus by creating a thin shell
coating on the surface of the structure I am allowing the surface elements to receive force
and moment reactions which are in tum transmitted to all the elements in the structure
However there is one precaution that must be mentioned
6
Precaution
The constraint elements used to constrain the lumped mass to the elements on the
surface of the structure create a dissimilar mesh between This occurs because the
geometry of the elements on the surface of the structure are different fonn the geometry
of the constraint elements According to I-DEAS Creating Elements with Special
TechniQues the precaution for joining dissimilar meshes is that the results for any
elements near [this] mesh interface should be suspect In order to avoid suspect results
for elements near the mesh interface these elements are not selected for display during
post processing
7
CANTILEVER BEAM ANALYSIS
In order to validate the lumped mass method results I created several cantilever
beam models First I modeled a cantilever beam as seen below in Fig 1 The cantilever
beam is 10 x 2 x I and is made of steel The left end of the beam is held rigid while a
10000 in-lb moment is applied to the other end acting in the z-direction The resulting
bending stress should be a maximum at 15 ksi based on static calculations where the
moment is the force multiplied by the distance and the bending stress is the moment
multiplied by the distance from the neutral axis to the outer most fiber divided by the
moment of inertia COb - ~c) The results from the ftnite element analysis (FEA) are
15 ksi which agrees with the calculated bending stress of 15 ksi
M
Fig 1 Cantilever Beam 1 0x2x 1 Fig 2 Cantilever Beam lOx2xl with 1 0000 in-lb Moment Applied with Extension and Lumped
Mass Applied
The second cantilever beam model Fig 2 begins with the same dimensions used
in Fig 1 but now there is an additional beam section which extends off the end of the
cantilever beam The additional material allows me to (1) avoid suspect results near the
mesh interface and (2) post process the original cantilever beam section Now I can
constrain the lumped mass where the 10000 in-lb moment in the z-direction is applied
to the surface of the additional material Thus when I post process my model to
determine the maximum stress I can chose to post process only a portion of the extended
8
material This allows me to avoid the suspect results completely while still incorporating
the effects of the moment applied to the lumped mass
The results from the lumped mass method as applied to the cantilever beam are
shown in Table 1 The first maximum Von Mises stress for the cantilever beam 15 ksi
is the theoretical stress which all the models should predict I used this theoretical stress
as comparison for all the cantilever beam models tested
I post processed the second model of the cantilever beam which includes the
extended beam section and the lumped mass interface Figure I-B in Appendix B shows
that this maximum Von Mises stress is 29 ksi a stress that is 9333 higher than the
theoretical stress This result is precaution mentioned early stating that the results for
any elements near a mesh interface should be suspect II And as cautioned the high
stresses occur at the mesh interface
For the third model I post processed only a portion of the extended beam section
and excluded the lumped mass interface as seen in Fig 2-B The maximum Von Mises
stress dropped to 24 ksi With this post processing method I have been able to minimize
the suspect results near the mesh interface and the maximum Von Mises stress is now
only 60 higher than the theoretical stress However the true shape of the cantilever
beam must be analyzed as closely as possible Thus I post processed a fourth model
The fourth model eliminates the entire extended beam section on the side of the
applied moment as seen in Fig 3-B The result is a maximum Von Mises stress of 176
ksi This maximum Von Mises stress is only 1733 higher than the theoretical
maximum stress of 15 ksi
I used a fifth model to determine whether or not the extended beam section on the
opposite side of the lumped mass affects the results Figure 4-B shows the maximum
Von Mises stress for the fifth post processed model which post processes only the
original cantilever beam The stress remained the same at a maximum at 176 ksi
TABLE 1 Moment Resuhs for all Cantilever Beam Lumped Mass Models
PART CONDITION MAX VON MISES STRESS (ksi)
DIFFERENCE FROM THEORETICAL
Cantilever Beam 1 0 000 in-Ib moment applied to end of beam 15 0 With lumped Mass and Extensions 29 9333 Without lumped Mass 24 6000 Without Elements on lumped Mass Side 176 1733 Without lumped Mass and Extensions 176 1733
0
10
CANTILEVER BEAM RESULTS
From the cantilever beam models I found that the lumped mass model produces a
stress that is conservatively higher than that of the theoretical stress value Therefore this
method will only increase the factor of safety in my design Thus I will proceed with the
method of adding material to the original design then applying a lumped mass to the
additional material and fmally post processing only the original shape of the platform
connections
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
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LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
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20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
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200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
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ENGINEERING NOTE
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o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
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5 1(320 1~1bs
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1451
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Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
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I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
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286
A ~
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CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
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Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
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RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
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RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
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STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
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324E+04
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162E+04
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257E+04
2JIE+04
205E+04
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770E+OJ
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FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
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810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
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STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
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356E+03
178E+03
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S4SE+06
494E+06
424E+06
363E+06
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l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
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a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
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109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
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B07E+04
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951E+03
856E+03
761E+03
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381E+03
286E+03
191amp+-03
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BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
6
Precaution
The constraint elements used to constrain the lumped mass to the elements on the
surface of the structure create a dissimilar mesh between This occurs because the
geometry of the elements on the surface of the structure are different fonn the geometry
of the constraint elements According to I-DEAS Creating Elements with Special
TechniQues the precaution for joining dissimilar meshes is that the results for any
elements near [this] mesh interface should be suspect In order to avoid suspect results
for elements near the mesh interface these elements are not selected for display during
post processing
7
CANTILEVER BEAM ANALYSIS
In order to validate the lumped mass method results I created several cantilever
beam models First I modeled a cantilever beam as seen below in Fig 1 The cantilever
beam is 10 x 2 x I and is made of steel The left end of the beam is held rigid while a
10000 in-lb moment is applied to the other end acting in the z-direction The resulting
bending stress should be a maximum at 15 ksi based on static calculations where the
moment is the force multiplied by the distance and the bending stress is the moment
multiplied by the distance from the neutral axis to the outer most fiber divided by the
moment of inertia COb - ~c) The results from the ftnite element analysis (FEA) are
15 ksi which agrees with the calculated bending stress of 15 ksi
M
Fig 1 Cantilever Beam 1 0x2x 1 Fig 2 Cantilever Beam lOx2xl with 1 0000 in-lb Moment Applied with Extension and Lumped
Mass Applied
The second cantilever beam model Fig 2 begins with the same dimensions used
in Fig 1 but now there is an additional beam section which extends off the end of the
cantilever beam The additional material allows me to (1) avoid suspect results near the
mesh interface and (2) post process the original cantilever beam section Now I can
constrain the lumped mass where the 10000 in-lb moment in the z-direction is applied
to the surface of the additional material Thus when I post process my model to
determine the maximum stress I can chose to post process only a portion of the extended
8
material This allows me to avoid the suspect results completely while still incorporating
the effects of the moment applied to the lumped mass
The results from the lumped mass method as applied to the cantilever beam are
shown in Table 1 The first maximum Von Mises stress for the cantilever beam 15 ksi
is the theoretical stress which all the models should predict I used this theoretical stress
as comparison for all the cantilever beam models tested
I post processed the second model of the cantilever beam which includes the
extended beam section and the lumped mass interface Figure I-B in Appendix B shows
that this maximum Von Mises stress is 29 ksi a stress that is 9333 higher than the
theoretical stress This result is precaution mentioned early stating that the results for
any elements near a mesh interface should be suspect II And as cautioned the high
stresses occur at the mesh interface
For the third model I post processed only a portion of the extended beam section
and excluded the lumped mass interface as seen in Fig 2-B The maximum Von Mises
stress dropped to 24 ksi With this post processing method I have been able to minimize
the suspect results near the mesh interface and the maximum Von Mises stress is now
only 60 higher than the theoretical stress However the true shape of the cantilever
beam must be analyzed as closely as possible Thus I post processed a fourth model
The fourth model eliminates the entire extended beam section on the side of the
applied moment as seen in Fig 3-B The result is a maximum Von Mises stress of 176
ksi This maximum Von Mises stress is only 1733 higher than the theoretical
maximum stress of 15 ksi
I used a fifth model to determine whether or not the extended beam section on the
opposite side of the lumped mass affects the results Figure 4-B shows the maximum
Von Mises stress for the fifth post processed model which post processes only the
original cantilever beam The stress remained the same at a maximum at 176 ksi
TABLE 1 Moment Resuhs for all Cantilever Beam Lumped Mass Models
PART CONDITION MAX VON MISES STRESS (ksi)
DIFFERENCE FROM THEORETICAL
Cantilever Beam 1 0 000 in-Ib moment applied to end of beam 15 0 With lumped Mass and Extensions 29 9333 Without lumped Mass 24 6000 Without Elements on lumped Mass Side 176 1733 Without lumped Mass and Extensions 176 1733
0
10
CANTILEVER BEAM RESULTS
From the cantilever beam models I found that the lumped mass model produces a
stress that is conservatively higher than that of the theoretical stress value Therefore this
method will only increase the factor of safety in my design Thus I will proceed with the
method of adding material to the original design then applying a lumped mass to the
additional material and fmally post processing only the original shape of the platform
connections
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
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LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
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250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
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20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
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200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
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Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
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RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
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240E+03
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RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
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176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
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RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
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STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
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257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
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STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
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810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
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RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
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S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
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a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
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687E+Ol
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109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
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B07E+04
727E+04
646E+04
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951E+03
856E+03
761E+03
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286E+03
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BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
7
CANTILEVER BEAM ANALYSIS
In order to validate the lumped mass method results I created several cantilever
beam models First I modeled a cantilever beam as seen below in Fig 1 The cantilever
beam is 10 x 2 x I and is made of steel The left end of the beam is held rigid while a
10000 in-lb moment is applied to the other end acting in the z-direction The resulting
bending stress should be a maximum at 15 ksi based on static calculations where the
moment is the force multiplied by the distance and the bending stress is the moment
multiplied by the distance from the neutral axis to the outer most fiber divided by the
moment of inertia COb - ~c) The results from the ftnite element analysis (FEA) are
15 ksi which agrees with the calculated bending stress of 15 ksi
M
Fig 1 Cantilever Beam 1 0x2x 1 Fig 2 Cantilever Beam lOx2xl with 1 0000 in-lb Moment Applied with Extension and Lumped
Mass Applied
The second cantilever beam model Fig 2 begins with the same dimensions used
in Fig 1 but now there is an additional beam section which extends off the end of the
cantilever beam The additional material allows me to (1) avoid suspect results near the
mesh interface and (2) post process the original cantilever beam section Now I can
constrain the lumped mass where the 10000 in-lb moment in the z-direction is applied
to the surface of the additional material Thus when I post process my model to
determine the maximum stress I can chose to post process only a portion of the extended
8
material This allows me to avoid the suspect results completely while still incorporating
the effects of the moment applied to the lumped mass
The results from the lumped mass method as applied to the cantilever beam are
shown in Table 1 The first maximum Von Mises stress for the cantilever beam 15 ksi
is the theoretical stress which all the models should predict I used this theoretical stress
as comparison for all the cantilever beam models tested
I post processed the second model of the cantilever beam which includes the
extended beam section and the lumped mass interface Figure I-B in Appendix B shows
that this maximum Von Mises stress is 29 ksi a stress that is 9333 higher than the
theoretical stress This result is precaution mentioned early stating that the results for
any elements near a mesh interface should be suspect II And as cautioned the high
stresses occur at the mesh interface
For the third model I post processed only a portion of the extended beam section
and excluded the lumped mass interface as seen in Fig 2-B The maximum Von Mises
stress dropped to 24 ksi With this post processing method I have been able to minimize
the suspect results near the mesh interface and the maximum Von Mises stress is now
only 60 higher than the theoretical stress However the true shape of the cantilever
beam must be analyzed as closely as possible Thus I post processed a fourth model
The fourth model eliminates the entire extended beam section on the side of the
applied moment as seen in Fig 3-B The result is a maximum Von Mises stress of 176
ksi This maximum Von Mises stress is only 1733 higher than the theoretical
maximum stress of 15 ksi
I used a fifth model to determine whether or not the extended beam section on the
opposite side of the lumped mass affects the results Figure 4-B shows the maximum
Von Mises stress for the fifth post processed model which post processes only the
original cantilever beam The stress remained the same at a maximum at 176 ksi
TABLE 1 Moment Resuhs for all Cantilever Beam Lumped Mass Models
PART CONDITION MAX VON MISES STRESS (ksi)
DIFFERENCE FROM THEORETICAL
Cantilever Beam 1 0 000 in-Ib moment applied to end of beam 15 0 With lumped Mass and Extensions 29 9333 Without lumped Mass 24 6000 Without Elements on lumped Mass Side 176 1733 Without lumped Mass and Extensions 176 1733
0
10
CANTILEVER BEAM RESULTS
From the cantilever beam models I found that the lumped mass model produces a
stress that is conservatively higher than that of the theoretical stress value Therefore this
method will only increase the factor of safety in my design Thus I will proceed with the
method of adding material to the original design then applying a lumped mass to the
additional material and fmally post processing only the original shape of the platform
connections
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
I
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j i D (- TYP (__________________l~==_L_________________l Ii) I
i ~
I
middot I
I
bullI I middotbullbull bull
iI I
t-------------fr-----------middot---shy I
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middot I
bull I -A shy I
I middot IL_ -fI
~-----------------i t-
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DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
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o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
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APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
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Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
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I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
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CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
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Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
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l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
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jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
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t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
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dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
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t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
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F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
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Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
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VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
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24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
8
material This allows me to avoid the suspect results completely while still incorporating
the effects of the moment applied to the lumped mass
The results from the lumped mass method as applied to the cantilever beam are
shown in Table 1 The first maximum Von Mises stress for the cantilever beam 15 ksi
is the theoretical stress which all the models should predict I used this theoretical stress
as comparison for all the cantilever beam models tested
I post processed the second model of the cantilever beam which includes the
extended beam section and the lumped mass interface Figure I-B in Appendix B shows
that this maximum Von Mises stress is 29 ksi a stress that is 9333 higher than the
theoretical stress This result is precaution mentioned early stating that the results for
any elements near a mesh interface should be suspect II And as cautioned the high
stresses occur at the mesh interface
For the third model I post processed only a portion of the extended beam section
and excluded the lumped mass interface as seen in Fig 2-B The maximum Von Mises
stress dropped to 24 ksi With this post processing method I have been able to minimize
the suspect results near the mesh interface and the maximum Von Mises stress is now
only 60 higher than the theoretical stress However the true shape of the cantilever
beam must be analyzed as closely as possible Thus I post processed a fourth model
The fourth model eliminates the entire extended beam section on the side of the
applied moment as seen in Fig 3-B The result is a maximum Von Mises stress of 176
ksi This maximum Von Mises stress is only 1733 higher than the theoretical
maximum stress of 15 ksi
I used a fifth model to determine whether or not the extended beam section on the
opposite side of the lumped mass affects the results Figure 4-B shows the maximum
Von Mises stress for the fifth post processed model which post processes only the
original cantilever beam The stress remained the same at a maximum at 176 ksi
TABLE 1 Moment Resuhs for all Cantilever Beam Lumped Mass Models
PART CONDITION MAX VON MISES STRESS (ksi)
DIFFERENCE FROM THEORETICAL
Cantilever Beam 1 0 000 in-Ib moment applied to end of beam 15 0 With lumped Mass and Extensions 29 9333 Without lumped Mass 24 6000 Without Elements on lumped Mass Side 176 1733 Without lumped Mass and Extensions 176 1733
0
10
CANTILEVER BEAM RESULTS
From the cantilever beam models I found that the lumped mass model produces a
stress that is conservatively higher than that of the theoretical stress value Therefore this
method will only increase the factor of safety in my design Thus I will proceed with the
method of adding material to the original design then applying a lumped mass to the
additional material and fmally post processing only the original shape of the platform
connections
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
I
I I
j i D (- TYP (__________________l~==_L_________________l Ii) I
i ~
I
middot I
I
bullI I middotbullbull bull
iI I
t-------------fr-----------middot---shy I
middotmiddot middot
middot I
bull I -A shy I
I middot IL_ -fI
~-----------------i t-
I bull
DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
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CVLf( BON~ Z ~T 500] 14
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p~~a8~3 J Amiddot2ENGINEERING NOTE
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o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
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APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
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Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
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I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
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286
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AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
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dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
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Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
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RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
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l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
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dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
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t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
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F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
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Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
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Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
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NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
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24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
TABLE 1 Moment Resuhs for all Cantilever Beam Lumped Mass Models
PART CONDITION MAX VON MISES STRESS (ksi)
DIFFERENCE FROM THEORETICAL
Cantilever Beam 1 0 000 in-Ib moment applied to end of beam 15 0 With lumped Mass and Extensions 29 9333 Without lumped Mass 24 6000 Without Elements on lumped Mass Side 176 1733 Without lumped Mass and Extensions 176 1733
0
10
CANTILEVER BEAM RESULTS
From the cantilever beam models I found that the lumped mass model produces a
stress that is conservatively higher than that of the theoretical stress value Therefore this
method will only increase the factor of safety in my design Thus I will proceed with the
method of adding material to the original design then applying a lumped mass to the
additional material and fmally post processing only the original shape of the platform
connections
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
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I
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i ~
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iI I
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I middot IL_ -fI
~-----------------i t-
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DETAIL 1
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~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
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CVLf( BON~ Z ~T 500] 14
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p~~a8~3 J Amiddot2ENGINEERING NOTE
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o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
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5 1(320 1~1bs
r 11 A-shy
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1451
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Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
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I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
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CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
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Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
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l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
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F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
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a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
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109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
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B07E+04
727E+04
646E+04
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46SE+04
404E+04
323E+04
243E+04
162E+04
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951E+03
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761E+03
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286E+03
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BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
10
CANTILEVER BEAM RESULTS
From the cantilever beam models I found that the lumped mass model produces a
stress that is conservatively higher than that of the theoretical stress value Therefore this
method will only increase the factor of safety in my design Thus I will proceed with the
method of adding material to the original design then applying a lumped mass to the
additional material and fmally post processing only the original shape of the platform
connections
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
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bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
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20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
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o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
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I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
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286
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AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
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dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
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RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
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dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
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l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
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jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
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257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
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RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
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dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
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RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
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60SE+06
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S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
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a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
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109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
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B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
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VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
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24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
11
PLATFORM CONNECTION DESIGN
The design of all four platfonn connections begins by following the method used
for the cantilever beam The connections are drawn flfSt and then the additional material
is added I followed the procedure How to Create Moments on a Solid and applied the
reaction moments to the lumped mass corresponding to each of the four connections The
connections at nodes 1 and 288 are the plate connections for the platfonn and nodes 313
and 26 are the bracket connections for the platfonn
Boundruy Conditions
The boundary conditions are comprised of three parts The fIrst boundary
condition applied to the connections is the reaction forces The reaction forces at the
connections are shown in a previous analysis by Russ Rucinski in Appendix A Page A6
shows a summary of all the reaction forces and moments as they pertain to each node
connection
The second boundary condition specilles which surfaces will be held rigid The
rigid surfaces chosen are the surfaces of the plates and brackets which are in contact with
the cryobridge These surfaces will have no rotation or translation
The third boundary condition is the application of the 28000 lb minimum fastener
tension which is applied to all bolt holes as pertaining to the requirements of the
American Institute of Steel Construction (AlSC)
Case Scenarios
The analysis for the four node connections begins with three different case
scenarios for each connection The flISt case scenario presents the post processing of
each connection design including the extended material and the lumped mass The
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
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bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
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20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
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o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
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I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
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dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
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Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
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l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
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jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
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dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
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t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
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F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
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Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
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dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
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dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
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24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
12
extended material is the rectangular 8 x 4 x114 steel tubing known as a boom The
addition of the boom not only provides a surface to constrain the lumped mass but is also
a true representation of the assembled platfonn The second case scenario post processes
the connections excluding the lumped mass and a partial section of the boom The fmal
case presented post processes the connection excluding the lumped mass a partial section
of the boom and the fastener tension All three case scenarios post processed follow the
same case scenarios used to test the cantilever beam discussed previously Table 2
presents the results of these cases for all four connections and Appendix B presents the
stress plots for all the models Once a maximum Von Mises stress is found the material
selection process can begin
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
I
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j i D (- TYP (__________________l~==_L_________________l Ii) I
i ~
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I
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middot I
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I middot IL_ -fI
~-----------------i t-
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DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
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CVLf( BON~ Z ~T 500] 14
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p~~a8~3 J Amiddot2ENGINEERING NOTE
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o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
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I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
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CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
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Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
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l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
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jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
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dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
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F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
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Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
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dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
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24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
13
TABLE 2 Comparison of Moment Results for all Lumped Mass Models
PART CONDITION MAX VON MISES STRESS
Lumped Mass Partial Boom and Fastner Tension Excluded
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
I
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i ~
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bull I -A shy I
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~-----------------i t-
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DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
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CVLf( BON~ Z ~T 500] 14
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p~~a8~3 J Amiddot2ENGINEERING NOTE
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ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
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LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
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lIfIU Fu-fo 100 t Io()IIQ
125
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APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
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1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
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I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
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CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
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Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
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Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
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l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
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24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
14
Node Connection 288
The plate connection at node 288 is modeled ftrst Fig 5-B shows the Von Mises
stress results for the ftrst scenario the post processing of the plate including the boom
section and the lumped mass With a maximum Von Mises stress of 4860 ksi this model
is clearly beyond the acceptable stress range since the targeted maximum stress should be
less than 36 ksi At a maximum stress less than 36 ksi I can utilize ASTM A36 steel
which is abundantly available
The second scenario results plotted in Fig 6-B show a dramatic decrease in the
maximum Von Mises stress The second scenario post processes the plate excluding a
portion of the boom and the lumped mass and should be in agreement with the results
from the cantilever beam analysis The stress level dropped as expected from 4860 ksi to
811 ksi However the high stress concentration area changed from the mesh interface
between the lumped mass and the boom to the fastener tension area around the bolt holes
Since these stresses are compressive stresses and not bending stresses I can neglect their
presence when determining the maximum bending stress Also if the plate connection
was to fail at the bolts the bolts would fail ftrst during the pre-tension installation period
Therefore one more scenario must be presented to better approximate the stresses acting
on the plate
The ftnal scenario is the post processing of the plate excluding the boom section
on the applied moment side the lumped mass interface and the fastener tension applied
around the bolt holes Fig 7-B shows that the maximum Von Mises stress is now only
257 ksi
Node Connection 1
The results presented for node connection 1 are very similar to those for node
connection 288 since their geometry is exactly the same However due to the locations
of the plate connections on the platform node 1 has a lower maximum Von Mises stress
All three scenario results for node 1 follow the same trends as the scenario results for
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
I
I I
j i D (- TYP (__________________l~==_L_________________l Ii) I
i ~
I
middot I
I
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iI I
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middotmiddot middot
middot I
bull I -A shy I
I middot IL_ -fI
~-----------------i t-
I bull
DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
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CVLf( BON~ Z ~T 500] 14
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p~~a8~3 J Amiddot2ENGINEERING NOTE
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11 111 Fc IC 2 ( ~) 77 8~jII+ 3 lUfl~) = i I
f = B ItS
(Lot 4t) 2 2 3-13 AIJ6C~ p~ OSA Zltf 4FI Z3e i
J
EAIIS ) 1 -f 1C B Su~ - 312shy1
3 3 ~w B ~ ~ 12
3~ Ft bull 6 VLLlI~ ~ u~~ 1Ar~ fNW =- q
10 c r fJampgt S r~
Dec ~ P(A-e Iq IIon 1(1- JI 40 II w 70 Untb-IC
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o [ OTIlt OS I e 8 IbS)
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t
2 J shy J uJ tshy ( tY ~ J J I shyDOClVl
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==============-----========-------------------------------- =
o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
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r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
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~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
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b
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c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
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+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
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bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
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Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
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-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
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(t = 27~ tS lt ~ ~ vq tS) ot
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24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
IS
node 288 and the cantilever beam The maximum Von Mises stresses are 422081 and
178 ksi as seen in Figures 8-B 9-B and IO-B respectively
In order to verify the results found for node 1 I calcu1ated the stress in the plate
and compared it to the FEA results The stress in the plate is mostly due to bending
caused by the 16320 in-lb moment acting in the y-direction The calculation for the
stress in the plate can be followed below
l ~
T ~
1_
2 24 KSl
1)--
0 (C A~
0 0 v
(lb3l0 -Ib)( S ~) _
Bt~(II~) 12
The maximum calculated bending stress for the 8 wide I thick plate is 1224
ksi The PEA model result as seen in Fig IO-B for case scenario three shows a
maximum Von Mises stress of 178 ksi Both results closely agree however the stress
comparisons also show that the stresses produced by the FEA will be conservatively high
via the lumped mass method
Node Connection 313 and 26
Node connections 313 and 26 show similar results to those of node connections
288 and 1 in that the stresses on the bracket are best approximated when post processing
the model excludes the lumped mass interface and the additional material For the third
case scenario the brackets maximum Von Mises stresses are near 10 ksi
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
I
I I
j i D (- TYP (__________________l~==_L_________________l Ii) I
i ~
I
middot I
I
bullI I middotbullbull bull
iI I
t-------------fr-----------middot---shy I
middotmiddot middot
middot I
bull I -A shy I
I middot IL_ -fI
~-----------------i t-
I bull
DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
OA() k~~f(
~F ntS~amp4 o~
IltNDOO 0 Ii 21 Lv A
3 AlVA-OL~ J ~AH~(sJ () T4IfiES) VlIPott Cvt6Q c~ tpoundkO$ C+-c-_
S-i ~ Gltx) 10 A 00 IT il t-J bull
VAtshy vUSC - 631+lshy20 ~ bullis Pt 30
(Ioaamp~)
(Zo)L ~ )~ Z + (75 + 11 (Ugt 30)(106
=- ~ 2 + 3 Cj t i IAIgt 8gt2S tA)
W1 -- 237 ~S 1 ) I
- AoO u-TIJt~ IJJ TIlft~ 9PE~)~ 1IP eELOW- b ~ S 10
CVLf( BON~ Z ~T 500] 14
o FERMILAB PIIQACf IEAIAL-QATEOQIn ~
p~~a8~3 J Amiddot2ENGINEERING NOTE
PLA 4=Q 2vt DeS I 6rJ cA -c~
-OAtgt GS-r H AAte 0011 IAIMSION 011 tl- 2o-~
-
q02bFt 1l 101 Ft(lIrrlrlL) bull 201
71 Fltt (to ec) - I if I 10 fc (PIA~) qO
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11 111 Fc IC 2 ( ~) 77 8~jII+ 3 lUfl~) = i I
f = B ItS
(Lot 4t) 2 2 3-13 AIJ6C~ p~ OSA Zltf 4FI Z3e i
J
EAIIS ) 1 -f 1C B Su~ - 312shy1
3 3 ~w B ~ ~ 12
3~ Ft bull 6 VLLlI~ ~ u~~ 1Ar~ fNW =- q
10 c r fJampgt S r~
Dec ~ P(A-e Iq IIon 1(1- JI 40 II w 70 Untb-IC
~O lIC 100 It IHlllc-if- foTAC - -I 82 I~
301bS
o [ OTIlt OS I e 8 IbS)
A3 Jultto~ti ~ uJ tl )
~ 2 ~ ~
t
2 J shy J uJ tshy ( tY ~ J J I shyDOClVl
shy L
==============-----========-------------------------------- =
o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
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~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
16
RECOMMENDATIONS
The plate and bracket connections are best approximated by the lumped mass
method and the material selection is based on the FEA results presented in Table 2 The
maximum Von Mises stress for the four connections excluding the fastener tension is
257 ksi for node 288 The maximum allowable stress is a combination of bending stress
and tensile stress and is 066 of the yield strength for a given material per AISC 1514
ASTM A572-Grade 42 steel or a grade of steel with a higher yield strength is
recommended The yield stress for this steel is 42 ksi and according the AISC standard
for tension and compression on extreme fibers the maximum allowable bending stress is
277 ksi Therefore the stresses in all four connections are below the allowable when
using ASTM A572-Grade 42 steel or greater
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
I
I I
j i D (- TYP (__________________l~==_L_________________l Ii) I
i ~
I
middot I
I
bullI I middotbullbull bull
iI I
t-------------fr-----------middot---shy I
middotmiddot middot
middot I
bull I -A shy I
I middot IL_ -fI
~-----------------i t-
I bull
DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
OA() k~~f(
~F ntS~amp4 o~
IltNDOO 0 Ii 21 Lv A
3 AlVA-OL~ J ~AH~(sJ () T4IfiES) VlIPott Cvt6Q c~ tpoundkO$ C+-c-_
S-i ~ Gltx) 10 A 00 IT il t-J bull
VAtshy vUSC - 631+lshy20 ~ bullis Pt 30
(Ioaamp~)
(Zo)L ~ )~ Z + (75 + 11 (Ugt 30)(106
=- ~ 2 + 3 Cj t i IAIgt 8gt2S tA)
W1 -- 237 ~S 1 ) I
- AoO u-TIJt~ IJJ TIlft~ 9PE~)~ 1IP eELOW- b ~ S 10
CVLf( BON~ Z ~T 500] 14
o FERMILAB PIIQACf IEAIAL-QATEOQIn ~
p~~a8~3 J Amiddot2ENGINEERING NOTE
PLA 4=Q 2vt DeS I 6rJ cA -c~
-OAtgt GS-r H AAte 0011 IAIMSION 011 tl- 2o-~
-
q02bFt 1l 101 Ft(lIrrlrlL) bull 201
71 Fltt (to ec) - I if I 10 fc (PIA~) qO
CL -t 4 Sl~) bull Z C 0 3 3 F~ 2 ltl~s) c ~5
11 111 Fc IC 2 ( ~) 77 8~jII+ 3 lUfl~) = i I
f = B ItS
(Lot 4t) 2 2 3-13 AIJ6C~ p~ OSA Zltf 4FI Z3e i
J
EAIIS ) 1 -f 1C B Su~ - 312shy1
3 3 ~w B ~ ~ 12
3~ Ft bull 6 VLLlI~ ~ u~~ 1Ar~ fNW =- q
10 c r fJampgt S r~
Dec ~ P(A-e Iq IIon 1(1- JI 40 II w 70 Untb-IC
~O lIC 100 It IHlllc-if- foTAC - -I 82 I~
301bS
o [ OTIlt OS I e 8 IbS)
A3 Jultto~ti ~ uJ tl )
~ 2 ~ ~
t
2 J shy J uJ tshy ( tY ~ J J I shyDOClVl
shy L
==============-----========-------------------------------- =
o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
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~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
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Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
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+1 ~ 128amp lb- Z ~ Ib
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+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
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bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
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6 - ~ ( I t bO - Ibs) 15 Z- PSI
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24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
17
BOLT PATTERN DESIGN
The bolt patterns are chosen in accordance with American Institute of Steel
Construction standards for minimum spacing and minimum center-to-center distance for
each hole AISC specifies for minimum spacing in 11641 that the minimum distance
between the centers of holes shall not be less than 2-213d where d is the nominal
diameter of the fastener In this design the nominal diameter is 75 inches Therefore
the minimum allowable distance is 2 inches I chose to use 25 inches as my minimum
distance for the design of the 1 plates(nodes 1 and 288) Also the minimum allowable
edge distance is 1-114 according to AISC Table 11651 However in my design I will
use an edge distance of 1S inches Both the center spacing distance and the edge distance
are chosen to be larger than the allowable minimums in order to increase the reliability of
the design
After choosing the bolt spacing I analyzed the fastener group using the elastic
method2 Each fastener group is made up of 34 bolts A325 Grade Here the allowable
tension stress due to bending is 44 ksi and the allowable shear stress is 175 ksi The
detailed calculations in Appendix C show that the maximum tensile and shear loading
will be less than the allowables For the node 1 and 288 connection the tension due to
bending is 87 ksi and the shear stress is 0213 ksi For node 26 and 313 connection the
tension due to bending is 272 ksi and the shear stress is 20 hi The results of these
calculations show that the fastener groups can withstand the reaction forces and moments
caused by the loads acting on the platform Therefore the fastener groups shall be
manufactured as designed in Figures 3 and 4 using 34 bolts grade A325
1 AlSC page 4-58 and Steel Structures Design and Behavior 2rr4 Edition Section 4-8 by Cbarles Salmon and John E Johnson 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
I
I I
j i D (- TYP (__________________l~==_L_________________l Ii) I
i ~
I
middot I
I
bullI I middotbullbull bull
iI I
t-------------fr-----------middot---shy I
middotmiddot middot
middot I
bull I -A shy I
I middot IL_ -fI
~-----------------i t-
I bull
DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
OA() k~~f(
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3 AlVA-OL~ J ~AH~(sJ () T4IfiES) VlIPott Cvt6Q c~ tpoundkO$ C+-c-_
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VAtshy vUSC - 631+lshy20 ~ bullis Pt 30
(Ioaamp~)
(Zo)L ~ )~ Z + (75 + 11 (Ugt 30)(106
=- ~ 2 + 3 Cj t i IAIgt 8gt2S tA)
W1 -- 237 ~S 1 ) I
- AoO u-TIJt~ IJJ TIlft~ 9PE~)~ 1IP eELOW- b ~ S 10
CVLf( BON~ Z ~T 500] 14
o FERMILAB PIIQACf IEAIAL-QATEOQIn ~
p~~a8~3 J Amiddot2ENGINEERING NOTE
PLA 4=Q 2vt DeS I 6rJ cA -c~
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-
q02bFt 1l 101 Ft(lIrrlrlL) bull 201
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==============-----========-------------------------------- =
o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
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24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
) ) )
8- 14- BOOM
THICK PLATE
875 INI
38shyREINFORCEMENT MATERIAL
I
x 4- x
1 -
THICK
1--- 23 50
I 224 TYP ~ 250
I~r Itl 800 I I 1
LLI II
5 50 TYP --t--
88shy OIA THRU
1 50
TYP 1 00 -f[J~ 1 00
250 TYP 5[ rID J47
TYP 300~ 6 HOLES
Figure 3 Assembly of Plate Connection at Nodes 1 and 288
00
BB
I I middot --- I I I I I I
I
I I
j i D (- TYP (__________________l~==_L_________________l Ii) I
i ~
I
middot I
I
bullI I middotbullbull bull
iI I
t-------------fr-----------middot---shy I
middotmiddot middot
middot I
bull I -A shy I
I middot IL_ -fI
~-----------------i t-
I bull
DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
OA() k~~f(
~F ntS~amp4 o~
IltNDOO 0 Ii 21 Lv A
3 AlVA-OL~ J ~AH~(sJ () T4IfiES) VlIPott Cvt6Q c~ tpoundkO$ C+-c-_
S-i ~ Gltx) 10 A 00 IT il t-J bull
VAtshy vUSC - 631+lshy20 ~ bullis Pt 30
(Ioaamp~)
(Zo)L ~ )~ Z + (75 + 11 (Ugt 30)(106
=- ~ 2 + 3 Cj t i IAIgt 8gt2S tA)
W1 -- 237 ~S 1 ) I
- AoO u-TIJt~ IJJ TIlft~ 9PE~)~ 1IP eELOW- b ~ S 10
CVLf( BON~ Z ~T 500] 14
o FERMILAB PIIQACf IEAIAL-QATEOQIn ~
p~~a8~3 J Amiddot2ENGINEERING NOTE
PLA 4=Q 2vt DeS I 6rJ cA -c~
-OAtgt GS-r H AAte 0011 IAIMSION 011 tl- 2o-~
-
q02bFt 1l 101 Ft(lIrrlrlL) bull 201
71 Fltt (to ec) - I if I 10 fc (PIA~) qO
CL -t 4 Sl~) bull Z C 0 3 3 F~ 2 ltl~s) c ~5
11 111 Fc IC 2 ( ~) 77 8~jII+ 3 lUfl~) = i I
f = B ItS
(Lot 4t) 2 2 3-13 AIJ6C~ p~ OSA Zltf 4FI Z3e i
J
EAIIS ) 1 -f 1C B Su~ - 312shy1
3 3 ~w B ~ ~ 12
3~ Ft bull 6 VLLlI~ ~ u~~ 1Ar~ fNW =- q
10 c r fJampgt S r~
Dec ~ P(A-e Iq IIon 1(1- JI 40 II w 70 Untb-IC
~O lIC 100 It IHlllc-if- foTAC - -I 82 I~
301bS
o [ OTIlt OS I e 8 IbS)
A3 Jultto~ti ~ uJ tl )
~ 2 ~ ~
t
2 J shy J uJ tshy ( tY ~ J J I shyDOClVl
shy L
==============-----========-------------------------------- =
o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
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~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
BB
I I middot --- I I I I I I
I
I I
j i D (- TYP (__________________l~==_L_________________l Ii) I
i ~
I
middot I
I
bullI I middotbullbull bull
iI I
t-------------fr-----------middot---shy I
middotmiddot middot
middot I
bull I -A shy I
I middot IL_ -fI
~-----------------i t-
I bull
DETAIL 1
DD 1-----60-----1
~~~E 1l c
bull-Jt J SECTION A-A DETAIL 1
bull
~ NOTE
bull 1 INTERMEDIATE WELDS 12 LONG FROM EDGES
L 7 bull 0 ( Armiddot 0 ~ bull
t -~ ~~--
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
OA() k~~f(
~F ntS~amp4 o~
IltNDOO 0 Ii 21 Lv A
3 AlVA-OL~ J ~AH~(sJ () T4IfiES) VlIPott Cvt6Q c~ tpoundkO$ C+-c-_
S-i ~ Gltx) 10 A 00 IT il t-J bull
VAtshy vUSC - 631+lshy20 ~ bullis Pt 30
(Ioaamp~)
(Zo)L ~ )~ Z + (75 + 11 (Ugt 30)(106
=- ~ 2 + 3 Cj t i IAIgt 8gt2S tA)
W1 -- 237 ~S 1 ) I
- AoO u-TIJt~ IJJ TIlft~ 9PE~)~ 1IP eELOW- b ~ S 10
CVLf( BON~ Z ~T 500] 14
o FERMILAB PIIQACf IEAIAL-QATEOQIn ~
p~~a8~3 J Amiddot2ENGINEERING NOTE
PLA 4=Q 2vt DeS I 6rJ cA -c~
-OAtgt GS-r H AAte 0011 IAIMSION 011 tl- 2o-~
-
q02bFt 1l 101 Ft(lIrrlrlL) bull 201
71 Fltt (to ec) - I if I 10 fc (PIA~) qO
CL -t 4 Sl~) bull Z C 0 3 3 F~ 2 ltl~s) c ~5
11 111 Fc IC 2 ( ~) 77 8~jII+ 3 lUfl~) = i I
f = B ItS
(Lot 4t) 2 2 3-13 AIJ6C~ p~ OSA Zltf 4FI Z3e i
J
EAIIS ) 1 -f 1C B Su~ - 312shy1
3 3 ~w B ~ ~ 12
3~ Ft bull 6 VLLlI~ ~ u~~ 1Ar~ fNW =- q
10 c r fJampgt S r~
Dec ~ P(A-e Iq IIon 1(1- JI 40 II w 70 Untb-IC
~O lIC 100 It IHlllc-if- foTAC - -I 82 I~
301bS
o [ OTIlt OS I e 8 IbS)
A3 Jultto~ti ~ uJ tl )
~ 2 ~ ~
t
2 J shy J uJ tshy ( tY ~ J J I shyDOClVl
shy L
==============-----========-------------------------------- =
o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
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dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
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dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
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l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
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l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
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bullbull
6
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I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
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- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
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middot-shy
--
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b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
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120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
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9
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(t = 27~ tS lt ~ ~ vq tS) ot
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24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
20
WELD SPECIFICATIONS
PJate Connection Nodes 1 and 288
The two 1 plates for the connections at nodes 1 and 288 are identical in size and
shape Each plate shall follow the dimensions as shown in Fig 3 According to AISC
the criterion for a fillet weld between two materials is based on the material thickness of
the thicker material However there appears to be no preference for welding thick
material to very thin material But there may be limitations for a fillet weld between a I
thick plate and the 11411 thick boom
Charles G Salmon and John E Johnson in Steel Structures speak of size
limitations which could apply to a weld between 1 II thick and 114 thick material The
size limitations apply to the welding process Since the welding process produces heat
energy the heat energy is mostly absorbed by the thicker of two plates being joined
Therefore one can see that the thicker material allows for more heat energy dissipation
vertically as well as horizontally Thus the thicker the plate the faster the heat energy
will be removed from the welding area This in tum produces lower temperatures at the
region of the weld Since a minimum temperature is required to provide a cohesive
connection between the two plates a weld of sufficient size is needed In other words
the thickness of the two plates needs to be comparable in size because lIunless a proper
temperature is maintained in the area being welded a lack of fusion will result
Due to possible limitations of a fillet weld based on the ratio of material
thickness a solution would be to weld a 38 thick material to the 114 thick boom and
then weld the 38 thick material to the 1 thick plate This approach is beneficial for two
reasons First this approach provides a reasonable material thickness ratio and thus more
adequately provides for the minimum temperature requirements for proper fusion By
welding an intermediate material thickness to the 11411 thick boom and to the I thick
plate we avoid the issue of excessive heat dissipation Secondly this approach provides
reinforcement for the 11411 thick boom at the point where the plate is welded to the boom
The detail of the 3811 thick reinforcement material as welded to the boom is seen in
Figure 4
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
OA() k~~f(
~F ntS~amp4 o~
IltNDOO 0 Ii 21 Lv A
3 AlVA-OL~ J ~AH~(sJ () T4IfiES) VlIPott Cvt6Q c~ tpoundkO$ C+-c-_
S-i ~ Gltx) 10 A 00 IT il t-J bull
VAtshy vUSC - 631+lshy20 ~ bullis Pt 30
(Ioaamp~)
(Zo)L ~ )~ Z + (75 + 11 (Ugt 30)(106
=- ~ 2 + 3 Cj t i IAIgt 8gt2S tA)
W1 -- 237 ~S 1 ) I
- AoO u-TIJt~ IJJ TIlft~ 9PE~)~ 1IP eELOW- b ~ S 10
CVLf( BON~ Z ~T 500] 14
o FERMILAB PIIQACf IEAIAL-QATEOQIn ~
p~~a8~3 J Amiddot2ENGINEERING NOTE
PLA 4=Q 2vt DeS I 6rJ cA -c~
-OAtgt GS-r H AAte 0011 IAIMSION 011 tl- 2o-~
-
q02bFt 1l 101 Ft(lIrrlrlL) bull 201
71 Fltt (to ec) - I if I 10 fc (PIA~) qO
CL -t 4 Sl~) bull Z C 0 3 3 F~ 2 ltl~s) c ~5
11 111 Fc IC 2 ( ~) 77 8~jII+ 3 lUfl~) = i I
f = B ItS
(Lot 4t) 2 2 3-13 AIJ6C~ p~ OSA Zltf 4FI Z3e i
J
EAIIS ) 1 -f 1C B Su~ - 312shy1
3 3 ~w B ~ ~ 12
3~ Ft bull 6 VLLlI~ ~ u~~ 1Ar~ fNW =- q
10 c r fJampgt S r~
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A3 Jultto~ti ~ uJ tl )
~ 2 ~ ~
t
2 J shy J uJ tshy ( tY ~ J J I shyDOClVl
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==============-----========-------------------------------- =
o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
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dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
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~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
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6
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PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
21
Bracket Connection Nodes 26 and 313
The two brackets for the connections at nodes 26 and 313 are identical in size and
shape Each bracket will be made of a 1 thick base plate with the dimensions as shown
in Fig 5 Four individual 34 plates or webs with dimensions shown in Fig 5 will be
welded to the 1 thick plates as designed The fillet welds shall be at least 516
according to AISC Table 1172A pertaining to the material thickness of the thicker part
joined The fillet welds lengths shall include the complete contact surface between the
34 webs and the 1 plate
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
OA() k~~f(
~F ntS~amp4 o~
IltNDOO 0 Ii 21 Lv A
3 AlVA-OL~ J ~AH~(sJ () T4IfiES) VlIPott Cvt6Q c~ tpoundkO$ C+-c-_
S-i ~ Gltx) 10 A 00 IT il t-J bull
VAtshy vUSC - 631+lshy20 ~ bullis Pt 30
(Ioaamp~)
(Zo)L ~ )~ Z + (75 + 11 (Ugt 30)(106
=- ~ 2 + 3 Cj t i IAIgt 8gt2S tA)
W1 -- 237 ~S 1 ) I
- AoO u-TIJt~ IJJ TIlft~ 9PE~)~ 1IP eELOW- b ~ S 10
CVLf( BON~ Z ~T 500] 14
o FERMILAB PIIQACf IEAIAL-QATEOQIn ~
p~~a8~3 J Amiddot2ENGINEERING NOTE
PLA 4=Q 2vt DeS I 6rJ cA -c~
-OAtgt GS-r H AAte 0011 IAIMSION 011 tl- 2o-~
-
q02bFt 1l 101 Ft(lIrrlrlL) bull 201
71 Fltt (to ec) - I if I 10 fc (PIA~) qO
CL -t 4 Sl~) bull Z C 0 3 3 F~ 2 ltl~s) c ~5
11 111 Fc IC 2 ( ~) 77 8~jII+ 3 lUfl~) = i I
f = B ItS
(Lot 4t) 2 2 3-13 AIJ6C~ p~ OSA Zltf 4FI Z3e i
J
EAIIS ) 1 -f 1C B Su~ - 312shy1
3 3 ~w B ~ ~ 12
3~ Ft bull 6 VLLlI~ ~ u~~ 1Ar~ fNW =- q
10 c r fJampgt S r~
Dec ~ P(A-e Iq IIon 1(1- JI 40 II w 70 Untb-IC
~O lIC 100 It IHlllc-if- foTAC - -I 82 I~
301bS
o [ OTIlt OS I e 8 IbS)
A3 Jultto~ti ~ uJ tl )
~ 2 ~ ~
t
2 J shy J uJ tshy ( tY ~ J J I shyDOClVl
shy L
==============-----========-------------------------------- =
o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
) ) )
34- PLATES -1 395 l-i I I
I - 1 98 TYP
150 TYP
1400 8-x4middotxl4- BOOM
88- DIA THRU 4 HOLES
I
-Ep-
200 TYP
~
8 00 TYP --l
[ 500 TYP
320middot
bull Figure 5 Assembly of Bracket Connection at Nodes 26 and 313
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
OA() k~~f(
~F ntS~amp4 o~
IltNDOO 0 Ii 21 Lv A
3 AlVA-OL~ J ~AH~(sJ () T4IfiES) VlIPott Cvt6Q c~ tpoundkO$ C+-c-_
S-i ~ Gltx) 10 A 00 IT il t-J bull
VAtshy vUSC - 631+lshy20 ~ bullis Pt 30
(Ioaamp~)
(Zo)L ~ )~ Z + (75 + 11 (Ugt 30)(106
=- ~ 2 + 3 Cj t i IAIgt 8gt2S tA)
W1 -- 237 ~S 1 ) I
- AoO u-TIJt~ IJJ TIlft~ 9PE~)~ 1IP eELOW- b ~ S 10
CVLf( BON~ Z ~T 500] 14
o FERMILAB PIIQACf IEAIAL-QATEOQIn ~
p~~a8~3 J Amiddot2ENGINEERING NOTE
PLA 4=Q 2vt DeS I 6rJ cA -c~
-OAtgt GS-r H AAte 0011 IAIMSION 011 tl- 2o-~
-
q02bFt 1l 101 Ft(lIrrlrlL) bull 201
71 Fltt (to ec) - I if I 10 fc (PIA~) qO
CL -t 4 Sl~) bull Z C 0 3 3 F~ 2 ltl~s) c ~5
11 111 Fc IC 2 ( ~) 77 8~jII+ 3 lUfl~) = i I
f = B ItS
(Lot 4t) 2 2 3-13 AIJ6C~ p~ OSA Zltf 4FI Z3e i
J
EAIIS ) 1 -f 1C B Su~ - 312shy1
3 3 ~w B ~ ~ 12
3~ Ft bull 6 VLLlI~ ~ u~~ 1Ar~ fNW =- q
10 c r fJampgt S r~
Dec ~ P(A-e Iq IIon 1(1- JI 40 II w 70 Untb-IC
~O lIC 100 It IHlllc-if- foTAC - -I 82 I~
301bS
o [ OTIlt OS I e 8 IbS)
A3 Jultto~ti ~ uJ tl )
~ 2 ~ ~
t
2 J shy J uJ tshy ( tY ~ J J I shyDOClVl
shy L
==============-----========-------------------------------- =
o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
23
WELD RECOMl1ENDATIONS
The fillet welds between the 34 base plate of the brackets and the 34 webs at
nodes 26 and 313 shall be at least 38 inches The weld shall run around the entire
connecting surfaces The fillet welds concerning nodes 1 and 288 are as follows The
fillet weld between the 114 thick boom and the 38 thick steel material shall be a 316
weld And the fillet weld between the 38 thick steel material and the 1 thick plate shall
be a 38 weld
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
OA() k~~f(
~F ntS~amp4 o~
IltNDOO 0 Ii 21 Lv A
3 AlVA-OL~ J ~AH~(sJ () T4IfiES) VlIPott Cvt6Q c~ tpoundkO$ C+-c-_
S-i ~ Gltx) 10 A 00 IT il t-J bull
VAtshy vUSC - 631+lshy20 ~ bullis Pt 30
(Ioaamp~)
(Zo)L ~ )~ Z + (75 + 11 (Ugt 30)(106
=- ~ 2 + 3 Cj t i IAIgt 8gt2S tA)
W1 -- 237 ~S 1 ) I
- AoO u-TIJt~ IJJ TIlft~ 9PE~)~ 1IP eELOW- b ~ S 10
CVLf( BON~ Z ~T 500] 14
o FERMILAB PIIQACf IEAIAL-QATEOQIn ~
p~~a8~3 J Amiddot2ENGINEERING NOTE
PLA 4=Q 2vt DeS I 6rJ cA -c~
-OAtgt GS-r H AAte 0011 IAIMSION 011 tl- 2o-~
-
q02bFt 1l 101 Ft(lIrrlrlL) bull 201
71 Fltt (to ec) - I if I 10 fc (PIA~) qO
CL -t 4 Sl~) bull Z C 0 3 3 F~ 2 ltl~s) c ~5
11 111 Fc IC 2 ( ~) 77 8~jII+ 3 lUfl~) = i I
f = B ItS
(Lot 4t) 2 2 3-13 AIJ6C~ p~ OSA Zltf 4FI Z3e i
J
EAIIS ) 1 -f 1C B Su~ - 312shy1
3 3 ~w B ~ ~ 12
3~ Ft bull 6 VLLlI~ ~ u~~ 1Ar~ fNW =- q
10 c r fJampgt S r~
Dec ~ P(A-e Iq IIon 1(1- JI 40 II w 70 Untb-IC
~O lIC 100 It IHlllc-if- foTAC - -I 82 I~
301bS
o [ OTIlt OS I e 8 IbS)
A3 Jultto~ti ~ uJ tl )
~ 2 ~ ~
t
2 J shy J uJ tshy ( tY ~ J J I shyDOClVl
shy L
==============-----========-------------------------------- =
o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
o FERMI lAB
ENGINEERING NOTE
PLAFOIt~ D es I CltfJ
OA() k~~f(
~F ntS~amp4 o~
IltNDOO 0 Ii 21 Lv A
3 AlVA-OL~ J ~AH~(sJ () T4IfiES) VlIPott Cvt6Q c~ tpoundkO$ C+-c-_
S-i ~ Gltx) 10 A 00 IT il t-J bull
VAtshy vUSC - 631+lshy20 ~ bullis Pt 30
(Ioaamp~)
(Zo)L ~ )~ Z + (75 + 11 (Ugt 30)(106
=- ~ 2 + 3 Cj t i IAIgt 8gt2S tA)
W1 -- 237 ~S 1 ) I
- AoO u-TIJt~ IJJ TIlft~ 9PE~)~ 1IP eELOW- b ~ S 10
CVLf( BON~ Z ~T 500] 14
o FERMILAB PIIQACf IEAIAL-QATEOQIn ~
p~~a8~3 J Amiddot2ENGINEERING NOTE
PLA 4=Q 2vt DeS I 6rJ cA -c~
-OAtgt GS-r H AAte 0011 IAIMSION 011 tl- 2o-~
-
q02bFt 1l 101 Ft(lIrrlrlL) bull 201
71 Fltt (to ec) - I if I 10 fc (PIA~) qO
CL -t 4 Sl~) bull Z C 0 3 3 F~ 2 ltl~s) c ~5
11 111 Fc IC 2 ( ~) 77 8~jII+ 3 lUfl~) = i I
f = B ItS
(Lot 4t) 2 2 3-13 AIJ6C~ p~ OSA Zltf 4FI Z3e i
J
EAIIS ) 1 -f 1C B Su~ - 312shy1
3 3 ~w B ~ ~ 12
3~ Ft bull 6 VLLlI~ ~ u~~ 1Ar~ fNW =- q
10 c r fJampgt S r~
Dec ~ P(A-e Iq IIon 1(1- JI 40 II w 70 Untb-IC
~O lIC 100 It IHlllc-if- foTAC - -I 82 I~
301bS
o [ OTIlt OS I e 8 IbS)
A3 Jultto~ti ~ uJ tl )
~ 2 ~ ~
t
2 J shy J uJ tshy ( tY ~ J J I shyDOClVl
shy L
==============-----========-------------------------------- =
o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
o FERMILAB PIIQACf IEAIAL-QATEOQIn ~
p~~a8~3 J Amiddot2ENGINEERING NOTE
PLA 4=Q 2vt DeS I 6rJ cA -c~
-OAtgt GS-r H AAte 0011 IAIMSION 011 tl- 2o-~
-
q02bFt 1l 101 Ft(lIrrlrlL) bull 201
71 Fltt (to ec) - I if I 10 fc (PIA~) qO
CL -t 4 Sl~) bull Z C 0 3 3 F~ 2 ltl~s) c ~5
11 111 Fc IC 2 ( ~) 77 8~jII+ 3 lUfl~) = i I
f = B ItS
(Lot 4t) 2 2 3-13 AIJ6C~ p~ OSA Zltf 4FI Z3e i
J
EAIIS ) 1 -f 1C B Su~ - 312shy1
3 3 ~w B ~ ~ 12
3~ Ft bull 6 VLLlI~ ~ u~~ 1Ar~ fNW =- q
10 c r fJampgt S r~
Dec ~ P(A-e Iq IIon 1(1- JI 40 II w 70 Untb-IC
~O lIC 100 It IHlllc-if- foTAC - -I 82 I~
301bS
o [ OTIlt OS I e 8 IbS)
A3 Jultto~ti ~ uJ tl )
~ 2 ~ ~
t
2 J shy J uJ tshy ( tY ~ J J I shyDOClVl
shy L
==============-----========-------------------------------- =
o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
A3 Jultto~ti ~ uJ tl )
~ 2 ~ ~
t
2 J shy J uJ tshy ( tY ~ J J I shyDOClVl
shy L
==============-----========-------------------------------- =
o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
o FEAMILA8
ENGINEERING NOTE PAOJICf SEIIAL(ATEOORY PAQ(
~~~IMS as-z3lIsmiddot 4~
LOADS AItIi PI-AcOcgt A-r ilot APPRoPfLlltrE -OC~Os
0-) THEmiddot__ 5~U(nl~
lIfIU Fu-fo 100 t Io()IIQ
125
c)
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
) ) )
APPLleD LoADS ~IOACONS lA 1700 middot ll 3115 I~s
5 1(320 1~1bs
r 11 A-shy
Y
173 ls
1451
128(
Non LOADS DIFCpound1a ONLy fbOOO 01 Cu S-l amp1-1-( r=RON LOAD E~ M~-rE VAuJItS
[AI-I- VALuE Ir-J LeS ] E l(CEP A~ -JOEO
raquo lJ
~IU _1 _ -(H t r 3
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
I-DtAS Master Series 21 Simulation 20-Nov-96 132526 dks4d3s7ms_ruc1nskitrussbase1mf1Z
Group ID None Result Set 2 - BC lLOAD 1 REACTION FORCE_2 Report Type Contour Units IN Result Type REACTION FORCE Frame of Reference Part Data component Norm to Screen
Node Reacti-X React1-Y React1-Z Reacti-RX Reacti-RY Reacti-RZ
1 OOOOE+OO -5655E+02 2844E+03 OOOOE+OO -1632E+04 -3415E+03
26 -2518E+03 1478E+03 -4847E+03 -1 706E+04 OOOOE+OO OOOOE+OO
288 1451E+03 1286E+03 -2831E+03 4784E+02 1600pound+04 7227E+03
313 1067E+03 3372E+03 4835E+03 -1966E+04 OOOOE+OO OOOOE+OO
1ota1 OOOOE+OO 5570E+03 -4883E-04 -3624E+04 -3194pound+02 3811E+03
288 313 313 288 288 288 Maximum 1 451E+03 3372E+03 4835E+03 4784E+02 1600pound+04 7227E+03
26 1 26 313 1 1 Minimum -2518E+03 -5655pound+02 -4847E+03 -1966E+04 -1632pound+04 -3415E+03
Average OOOOE+OO 9237E+00 -8098E-07 -6010E+01 -5298E-01 6320E+00
2 ~ 0lt oJ ~ aoE 1shy
)t
286
A ~
tJOD~~ 2h t1 ~ 16) )( f 1 11tpr-JSIAfIO~ ~lkED
X eono t-JS F I X E Cgt
Y ~ K t) iA 11 0 ~ S ~ R EE J I
CON t-JEc oJRES~r-JT SPpound(FCATIO~S 8ASeD oJ 4 BOL-T
AT ~ D DES i ~ 2 ~ ~ ) 2 f3oI-TS P-lokJ( --1 A IS e 2~ f 313
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
))--lff yDlX B
Fi ~ uN j-B CIvJTLEvee BEAM sTReSgtSgtpound5 V 171+ LUt1fcb MAsgt AND El(TENOItlS ( M l 10000 - I~
dks4d3s7ms_rucinskiakuwazaki2mfl
RESULTS 2shy BC 1LOAD lSTRESS_2 STRESS - VON MISES MIN 226E-01 MAX 2908+04 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
290E+04
261E+04
232E+04
2038+04
1748+04
1458+04
16EI04
8698+03
5BOE+03
2908+03
416801
(A)
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
1=i Civre z-B CA-tJTlLevef BEAM STRffSses WrHi)uT i-U1fIl(EO Mttss ( ~nA-L j)lX)If1 eXCLUDeD
jdks4d3s7jms_rucinskijakuwazaki2mfl RESULTS 2- BC ILOAD ISTRESS_2
STRESS - VON MISES MIN 22GE-OI MAX 240E+04 VALUE OPTIONACTUAL FRAME OF REF PART
240E+04
216E+04
19lE+04
168E+04
144E+04
120E+04
f5 fHmiddotOJ
719E+OJ
479E+03
240E+03
2l6E 01
v
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
) ) )
Fi4tJre 3-amp (JtNIILeveR BeJtM Snampsst5 JTltDvr ~1IIT1U VO-VIle ()N LuMfeD MAs5 SJ1gte
dks4d3s7ms_rucinskiakuwazaki2mf1
RESULTS 2- BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 226E-Ol MAX 176E+04 VALUE OPTIONACTUAL
FRAME OF REF PART
176E+04
lS8E+04
141E+04
123E+04
106E+04
881E+03
704E+03
S28E+03
3S2E+03
176E+03
226E-Ol
()
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
-i-i 4v(t laquo -B LAtJTILeuli 6liiHvj SreeraquoES tJtTtfWT Lu~fii) 1155 4 E~TcItISlONs
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS - VON MISES MIN 226E-OI MAX 176E+04 VALUE OPTIONACTUAL FRAME OF REF PART
176E+04
15BE+04
141E+04
123E+04
l06E+04
ILBIE+03
704E+03
S2BE+03
3S2E+03
176E+03
226E-Ol
tiJ
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
) ) )
l==iQlIre 5-8 NODe Co~Nec TlOAl 299 L tJIII~e]) JvLtss ( Bcxgt11
dks4dls7ms rucinskiakuwazak12mtl
RESULTS 2shy BC ILOAb lSTRESS_l STRESS - VON HISES MIN 1S9E+Ol MAX 486E+06 VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
4S6E+06
437E+06
3BSE+06
340E+06
291E+06
24lE+06
I 94 E+06
146E+06
971E+05
486E+05
189E+Ol
0)
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
+=i~ureuro 6-B JOJ)E LtgtA1IVECTIOIll 298 L- UMPlJD vIt1-s5 1 PMrO~L amp011 poundXC-LtlPpoundl)
jdks4d3s7ms_rucinskiakuwazak12mf1 RESULTS 2- BC lLOAD 1STRESS_2
STRESS - VON MISES MIN 189E+01 MAX 611E+04 VALUE OPTIONACTUAL FRAME OF REF PART
811E+04
730E+04
649E+04
566E+04
487E+04
405E+04
324E+04
243E+04
162E+04
612E+03
169E+01
( ( ~
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
) ) )
t=i S1V~ 7-8 tJD])E JJII(lie ~TIO IV 289 LvlMpound) l4-1Ss P~1IA-L eco~ ~ FrJ-STElVet- TEtJSlotJ EXLLtJDED
dks4dJs7ms_ruclnskiakuwazaki2mfl RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES HIN 789E-02 MAX 257E+04 VALUE OPTIONACTOAL FRAME OF REF PART
257E+04
2JIE+04
205E+04
laOE+04
1 54 E+ 0 4
128E+04
10H04
770E+OJ
513E+OJ
257E+03
789E-02
QJ
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
shy1-1 ~vf1 ltg B NfYf)o (OflcnOfll 1 LUiVtPCD IA5 ( Boo
dks4d3s7ms rucinskiakuwazaki2mfl
RESULTS 2- BC ILOAD lSTR8SS_4
STRESS - VON HISBS MIN 358E+00 MAX 422E+01gt VALUE OPTIONACTUAL
FRAME OF REF PART SHELL SURFACE TOP
422E+06
380E+06
338E+06
495E+06
253E+06
211E+06
169E+06
17E+06
844E+05
42E+05
3588+00
V)
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
) ) )
t=i VfVl 9-B NODe (oAlIJECPON 1- LUf1P13b M~s lt -4-JtT711 t BlgtOM cxC-LvJ)eb
dks4d3s7ms_rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2
STRESS - VON MISES MIN 3588+00 HAX 810E+04 VALUE OPTIONACTUAL FRAME OF REF PART
810E+04
729E+04
648E+04
567E+04
486E+04
4058+04
J 24 E+04
243E+04
1 62E+04
811E+03
358E+00
OJ
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
- hQvrt 0- B NODeuro- (i)lNECnOAJ i LtJ~PBf) MAs~_ Y-4-ttTlltL BooM ~ i=tSTcv6e TElliSON Ex ct-vD E i)
dks4d3s7ms_rucinskiakuwazaki2rnfl
RESULTS 2shy BC 1LOAD 1STRESS_2
STRESS - VON MISES MIN 934E-02 MAX 178E+04 VALUE OPTIONACTUAL
~RAME OF REF PART
178E+04
160E+04
142E+04
1 25E+04
107E+04
890E+03
712E+03
5 HE+03
356E+03
178E+03
934E-02
I
VJ
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
) ) )
F1fiUre 11- B tJOIpound CJ)IJ1VEC70tJ 33 STfl15seS lrJITH- l-UMPe]) ~5 ~ BOOM
60SE+06
dks4d3s7ms rucinskiakuwazaki2mfl RESULTS 2- BC ILOAD 1STRESS_2 STRESS VON HISES MIN 6B2E+Ol MAX 60SE+06 DEFORMATION 1- BC 1LOAD 1DISPLACEMENT_I DISPLACEMENT MAG MIN OOOE+OO MAX 10BE-OI VALUE OPTIONACTUAL FRAME OF REF PART SBELL SURFACE TOP
S4SE+06
494E+06
424E+06
363E+06
IOJIHOb
l4lE+06
182E+06
1 21E+06
605E+05
68lE+Ol
VJ
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
t=itivre IZamp NO])E (OtJlJ8CTloN 33 STi2es) WI LtJMPreg J11~ ( Ptt-fimA-L BOoM poundXcuJDpoundfJ
dks4dls7ms_rucinsklakuwazaki2mfl RESULTS 2shy BC ILOAD 1STRESS_2 STRESS VON HISES MIN 687E+Ol MAX 814E+04 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_l DISPLACEMENT - MAG HIN OOOE+OO MAX aaIE-OJ VALUE OPTIONACTUAL FRAME OF REF PART
a14E+04
712E+04
6SIE+04
570E+04
4 89E+04
407E+04
126E+04
24SE+04
16JE+04
a20E+Ol
687E+Ol
l cP t
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
) ) )
Fi~u~ I~- B NoW C()AJtJBc no) 33gt S2c55 pounds ItJITft t=ttsTEvpoundf TEIJSIOIVpoundvPED AooIAS~ ( P1fjTIApound (3Q ampltLvj)EiJ
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2- BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 161E+Ol MAX 109E+04 VALUE OPTIONACTUAL FRAME OF REF PART
109E+04
962E+03
673E+03
764E+03
655E+03
546E+03
4378+03
329E+03
2208+03
111E+03
161E+01
CN
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
Fi Ufeuro 4-B POPE COfJltlecn()fv U ~TRes55 W IrH UJMPeJgt 11~ ~ Pfl-iTllfL ampoM CxCL-vi)6[)
dks4d3s7ms cucinskiakuwazaki2mfl RESULTS 2 BC ILOAD ISTRESS_2 STRESS - VON MISES MIN 53BE+Ol MAX B07E+04 DEFORMATION 1- BC ILOAD 1DISPLACEMENT_l DISPLACEMENT - MAG MIN OOOE+OO MAX 751E-03 VALUE OPTIONACTUAL FRAME OF REF PART
B07E+04
727E+04
646E+04
5fgt5E+04
46SE+04
404E+04
323E+04
243E+04
162E+04
B12E+03
53BE+Ol
lt l [jJ
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
) ) )
Hqure 15- B iVOJgtE COtJlfGltw 26 5reesses J17JI FASTlJIVGI r8IJSIDtv LtJMP6tgt 11~gt E PJHiTIAL Bi)()1 ampcL-VDED
dks4d3s7ms_rucinskiakuwazaki2mf1 RESULTS 2shy BC 1LOAD 1STRESS_2 STRESS - VON MISES MIN 155E+01 MAX 951E+03 DEFORMATION 1shy BC ILOAD IDISPLACEMENT_1 DISPLACEMENT - MAG MIN OOOE+OO FRAME OF REF PART
VALUE OPTIONACTUAL
951E+03
856E+03
761E+03
666amp+03
571amp+03
476E+03
381E+03
286E+03
191amp+-03
965amp+02
1 55amp+01
MAX 751E-03
01
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
3j1 DcgtLlS A3ZS G~De
F=~M A-1Sc PA-RT 1 4BlE I-AI
ILl )(SIFe ALlD1J ~B f-e LbAtgt
-An ciA-3re -c Q(G ) - D FYS 9 Z -os s II S +v~ I-zO 1(7 1fJA wM) 77
~ tp40- 8S j(S
NODE 1
l A-UtJW II $IN S7~~~ ( I) UA7iNfr -1YPE C~ J
+ j-shy ~x f2r ZJfNI Ii~ 311$ ~ 5 it - ----+ ~1pound= 5l$s -
1lt 163ZO
4AIY~ 111 -rkc ~7CI-E~ r ii) ~ ~ AS ( Mt -rmiddotc~O
l12eF AISC ltVCr ltI-Sf) AIJ~S7C6( S~JCTzeS )lt9(1 ~~VlQte
L z~ lbT70N Stt -rION c - f1 r C1IUS SA-uwt t SOI4W E
l i)INSOH IljSIJ )
01 Z75 J
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
C1
~ellcT70tJ iy (DIU Slf~~r) ~ I
r 9Vl~ Ib565middot 5 Ib ~IMl Ir _znBlbull 1V1SI
bullbull
6
-rENSlo ( (gt V ) I[
I
b PLA-E JlbTH- lti d PtA-1T ~FIII(r7)llaquo (
~ Ie (6 bblr) 2 2S ~Illt I IV )( 11 )
~ 16 320 I - I (~ 0
l~ XII ~~
ct~ stftlvL-tgt NtJr poundXCEcb ~i 11= ClJ(yenP2euroSS~ atT~N 7~
PIeCES IS TO IEMr4N IJr -rilE raP
~t gt 8 7 t=S1 lt ~ - 4 ttl o~
- ~I-Ie
-
+ f Zl a laquo ~ ~ 17I )$ 01( v
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
r ~l
d Z75
Jl 3 7zmiddotmiddot
Imiddotrn -I -~ ltamp _u = ~
b
Ll + Cd) A(
c ~ ~o - 11 S 4 Ib
Idl 1(371) +1 -s tS 3 8 ~Igt
Ii VALUAI f
2 -3 (JJ= ~x
f3r - ~ jtl- lb bull 115 Ih Z 07S)
2
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
C Lj
euro64cnow Ry
+1 ~ 128amp lb- Z ~ Ib
b
MAx SIIeAfl- LO) SgtC~ ~STEf~
+sIIt4Q ~ (fl~)~ (poundy -t -Cl)~ 2171b
Oi
ZZ1b
bull
~ 7lZ7 -1 (lt6 i f Iy-
No Jt~~ CAtU A~E AJ66DEllmiddot IJoDt 288 Q)NAlUTIOiJ
S-etS6tgt ~ LOweR ~1lJ NoDE J COIJ CrlOlIS --~t2Cr-epound~
tVbDC 288 CONNEt1 K)I1S A~c GX)lgt
middot-shy
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
--
) 47Y Ib Zgt ~Ip J8centlr
b
$N(6 TttE C4wvLA-7euroD LOAlgt IS Less jltHf ritE
A-LLlWABlpound I 3y aoi~ 4~E Ot
INeuro ~ 3~ COfJN6cTlON geAcrolS Oa~tf-rc
Olle-I Tile I)QL)~ 2b 1Ce- ~CT70us
28COo Ib (tI) Zii shy-- 2 I O~S ~I bd (3 51 II ~J
6 - ~ ( I t bO - Ibs) 15 Z- PSI
bel (395 11) ()I-I )
Ole
120 I Ib
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
-1115)97
jtt 1 I ~) ~7Ib - 267b~ -If -c __ + 4 v(1
C -Jlf +2 ~~ 337lb 8vJ Ib- f- i(I
J [( 10amp7)70 4- ($37i r
9
20DI ~
(t = 27~ tS lt ~ ~ vq tS) ot
SHe Aii
-J Z Q u lt ~ - 17 S ~SI 0
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980
24
BIBLIOGRAPHY
1 American Institute of Steel Construction Steel Construction Manual American
Institute of Steel Construction illinois 1980
2 Salmon G Charles and Johnson E John Steel Structures Design and Behavior 2ad
Edition Harper and Row Publishers New York 1980