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JSC - 26098
Design Mass Properties II
Mass Estimating And Forecasting For AerospaceVehicles Based On Historical Data
Systems Definition BranchTechnology and Project Implementation OfficeEngineering, Directorate
November 1994
National Aeronautics and Space AdministrationLyndon B. Johnson Space CenterHouston, Texas
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DESIGN MASS PROPERTIES H
MASS ESTIMATING AND FORECASTINGFOR
AEROSPACE VEHICLES
BASED ON HISTORICAL DATA
by
Willie Heineman, Jr.
Approved by:
Charles Teixeira
Chief, Systems Def'mitionBranch
• and
Manager, Technology & Project Implementation Office
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
LYNDON B. JOHNSON SPACE CENTER
HOUSTON, TEXAS
NOVEMBER 1994
JSC-26098
USING THIS REPORT
This report is intended to be used primarily for conceptual design efforts where time is notnormally available for rigorous detailed analysis. A cross check with the tools, techniques, anddata in this report is suggested along with an awareness of the rapidly advancing technologies.
This report, for the most park is based on ISC spacecraft hard.ware data beginning.with . _Mercury and ending with the Space Shuttle Vehicle. As illustratea anove, Mercury is (tam point 1and so on through data point 6 which is the Space Shuttle Vehicle. Data point 1 is broken downinto data point 1A, 1B, 1C, and 1D representing the Mercury Launch Escape System, the MercuryReentry Module, the Mercury Retro Pack, and the Mere.my Adapter Section .1-espectivel.y..Thisapproach is used throughout the report. Several ouaer points are usea touowmg oata point o.Appendix D of the report should be referred to for a complete data point listing along with theaccompanying data.
,.°m
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TABLE OF CONTENTS
Item Page
SUMMARY ............................................................................... 1
INTRODUCTION ....................................................................... 3
BACKGROUND ......................................................................... 5
PART 1 - MASS ESTIMATING ....................................................... 7I
PART 2 - MASS FORECASTING .................................................... 25
: REFERENCES ........................................................................... 33
APPENDIX A- ESTIMATING AND FORECASTING EXAMPLES
APPENDIX B - DEFINITIONS AND GUIDELINES
APPENDIX C - DATA FACTORS AND PLOTS
APPENDIX D - DATA BASE AND DATA POINTS
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LIST OF FIGURES
Figure Page
Figure 1 Manned Spacecraft and Space Stations .............................. 8
(Based on average density and volume)
Figure 2 Manned Spacecraft and Space Stations .............................. 10
(Based on mass and volume)
Figure 3 Propulsion Vehicles (Estimating Curves) ........................... 12
Figure 3.1 Propulsion Vehicles (Estimating Basis) ............................. 13
Figure 4 Body Structure .......................................................... 14
Figure 4.1 Body Structure, Adapters and Shrouds .............................. 15
Figure 4.2 Body Structure, Propellant Tanks .................................... 16
Figure 5 Vehicle Systems (Fixed) ............................................... 18
Figure 6 Crew and Passenger Systems ......................................... 19
0rLxedand Variable)
Figure 7 Structure and Systems ................................................. 20
Figure 8 Dry Mass and Area ..................................................... 22
Figure 9 Dry Mass and Volume ................................................. 23
Figure 10 Mass Growth (All Vehicles) .......................................... 26
Figure I I Mass Growth of Apollo Spacecraft .................................. 27
Figure 12 Mass Growth of Skylab Spacecraft .................................. 29
Figure 12.1 Mass Growth of Skylab OrbitalWorkshop ........................ 30
Figure 13 Mass Growth of Shutlle Orbiter ...................................... 32
LIST OF TABLES
Table Page "
Table 1 Mass Growth of Skylab Orbital Workshop ......................... 31
vi
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LIST OF SYMBOLS
Ab body wetted area
Ade design-envelope area with a volume, Vde
Apr pressurized area
At tail wetted area
Aw wingwettedareaAwet total wetted area
Db body diameter
Lb body length
Mb mass of body structure
Mc mass of crew
Mpl mass of payload
Mcpf mass of crew and passengers that is fixed
Mopu mass of crew, payload, unusable fluids and gases, etc.
Mopv mass of crew and passengers that variesMec mass of expendables and consumables
MD dry mass
Mfl mass of usable fluids
Mfo mass of usable food
MG gross mass
Mga mass of usable gases
MI inert mass
Mldg landing mass
Mlg mass of landing gear
Mp mass of usable propellant
Mpu mass of unusable propellant
Ms mass of structure system
Msy s mass of dry systems except for Ms and Mtps
Mlps mass of thermal protection systemNc numberofcrew
Ncp numberofcrew andpassengersNd number of days of design m_on
vii
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LIST OF SYMBOLS (Continued)
RhoG gross density
Rhob density of body structure
Rhosys density of dry systems except for structureandTPS
Rhotps densityof thermalprotection systemSw wingtheoretical, aerodynamicarea
Vde design,envelope volume with a surface area, Ade
Vpr pressurized volume
viii
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DESIGN MASS PROPERTIES II
Mass Estimating and Forecasting
for Aerospace VehiclesBased On Historical Data
SUMMARY
Mass estimatingand forecasting techniques are presented which are based on the fewest
and most inclusive design parametersthat occur at the earliest time in the design life of a newly
evolving aerospace vehicle.
Estimatingtechniques arebased on design-envelopeareaand volume. While both of these
parameters usuallychange with the designprocessover time, the presented estimating techniques
accountfor this change throughgeneralizedsizing variations. Accuratesizing during conceptual
design is crucial to accuratema_ estimation. Additional design parametersfor massestimating,
sizing, and systems derivationsareintroducedin the first part of this report.
Forecasting techniquesare also presentedin the secondpartof this report. After a weight
estimate is madein conceptualdesign, acompatiblemass-growthforecastis made. This forecast
accounts for the inexorable mass growth that affects aerospacevehicles before they become
operational.
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INTRODUCTION
The estimating and forecasting techniques in this report are intended to be used for
aerospace vehicles in the early phases of design, particularly in conceptual design.
There are many approaches to estimating and forecasting the mass of newly evolving
vehicle designs throughout Government and industry. Most of these approaches require many
design parameters that cannot be used with reasonable assurance of applicability. Not knowing
what the final designing parameters turn out to be is the true nature of conceptual design.
Therefore, the need exists for mass estimating and forecasting techniques that are
reasonably reliable, depend on the minimum number of design parameters, and are applicable over
a wide range of vehicle designs. The techniques in this report are intended to ftll this need to the
extent that design hardware data are available. Considerable use is made of a systematized
computer data base from which to retrieve mass and design data.
This report is in two parts; part one, which presents the estimating techniques; and part
two, which presents the forecasting techniques. This is done to emphasize the distinction, that
although related, the estimate should be treated separate from the forecast. This report emphasizes
that regardless of the mass estimate that is made in conceptual design, a mass forecast should also
be made. This is in recognition of vehicle mass growth that occurs throughout the program life of
any aerospace vehicle.
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BACKGROUND
Mass estimation, like other estimation processes involving complex vehicles, is difficult to
achieve with accuracy. With the rapidly improving technologies, it is becoming increasingly more
difficult to derive estimates during conceptual phases of design. It is felt that there are three major
areas of consideration that must be explored in order to achieve reasonable estimating accuracy in
conceptual design: (1) consistently recorded and reported mass and design data; (2) fundamentally
derived estimating and forecasting techniques based on hardware data; and (3) relentlessly
researched and applied data pertaining to the advancing technologies.
In relation to 1, above, DESIGN MASS PROPERTIES, Guidelines and Formats for
Aerospace Vehicles, JSC-23303, March 1989, should provide a significant contribution to
consistent recording and reporting (reference 1). This document on estimating and forecasting is
intended to supply the needs expressed by 2, above. A substantial effort is devoted to developing
fundamental estimating relationships based on early known design parameters as they apply to
conceptual design. This provides direct tools for conceptual design as well as check points for
later phases of design. At the least, good estimating and forecasting tools should be based on
hardware proven data to provide credence and a fwm baseline from which to project the advancingtechnologies.
5
MassvsVde
FIGURE 1ESTIMATING CURVES
Manned S )acecraI_ and S ,,eStations10e
..................... 4..- LEGEND:.... f-- O VehicleGrossMass,Me notIncludingTPS.... _ .... j : :
....... t...... A VehicleBodyStrictureMass,Mbnot Inc.TPS= !
...................... _".... [] ThermalPint.ion System Mass, Rt_tp=
I100,000" =-:::=::::::::::::=::::==2:=......................... 4-.....
....................... (- ....
Mass .::::..'-.::.::.:::.:::-.-:- ::i:::
Me I _
ib ....................................
I: ,.-t :M° 10,000- "_.-__!!!:_:_:2_:'-."2-=-....... :::: DATAPOINTS:
oo Mt_ ::::_:::::::--::g_ _ _ lB. MemuryReentryModule............ I__............... 2A. GeminiReentry Module................... 3B, ApolloCommand Module
(Ibs) __ 3E. ApolloLunarModule-Ascent(pre_udzed volume only)
4C. SkylabMultipleDockingAdapt.
/ .-A 31.s ' . 4F. SkylabOrbitalWorkshop1,000 "_--_-:::::_ "" 6A1. ShuttleOrbiterCrewCompt.
_'_ _:::..:: mOB Mo = 67.58 (Vd: '7°) 6/),2. ShuttleOrbiterBody-,_.............!.... _._. -- Z_- - Me) = 10.42(Vd:'OS) ' " '.......................i...............L.... i
i - = Me - Mb = 57.78 de°'74) . •t .... My, (V t i 1 I i _ J
II i I""_'" M,,,.=20.54(v,°.') i i i_ i==Ii i i100
100 1,000 10,000 100,000 _I
Design-Envelope Volume, V_ (fts) _°_oo
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PART 1 - MASS ESTIMATING
Techniques for developing mass estimatesfor aerospace vehicles have been developed for
use in conceptualdesign. The massestimating techniquesare based on design-envelopeareaandvolume.
Developmentof the estimatingtechniquesarebased on historicaldata. The historicaldata
includes existing or previously flown spac_raft and launch vehicles. A least squares regression
was applied to the historical data. The least squares method was considered applicable since the
datawas fairly consistent and did not contain any outliers. A power curve fit of the form
y = a + xb was chosen since the curve appears as a straight line on a log-log plot.
Figure 1 shows a plot of averagegross mass, body-structure mass, systems mass, and
thermal protection system (TPS) mass versus total design-envelopevolume for non-winged,manned vehicles. Vehicle gross mass, MG, (curve A) represents the total mass of a spacecraft
without the mass of the TPS, Mtps. Mtps is not included due to the differences in the missions
performed by the vehicles represented by the data points. For example, the Apollo command
module had a TPS sized for lunar retmn velocities and Skylab only had the TPS required for orbitoperations. The variation in MG is ± 15 % for any given total design-envelopevolume, Vde.
Curve B shows the body-structuremass, Mb, as a functionof the total design-envelope
volume, Vde. The variationin Mb is + 35 % for any given Vde. Mb has a greater variation(±35 %)
than MG (+ 15 %) for a given Vde. Also, it shouldbe noted that Mb does not includeMtps.
The systems mass, Msys, (curve C) represents the mass of all of the systems that comprise
the vehicle except for Mb and Mtps. Systems mass, Msys, is the result of subtracting the body-structure mass, Mb, from the gross mass, MG.
The thermal protection systemmass, Mtps, (curve D) is derived by using data points 1B,
2A, and 6A2, representing the Mercury reentry module, the Gemini reentry module,and the
ShuttleOrbiter body, respectively. These three data points form the Mtps relationshipfor low-
Earth-orbit reentry vehicles. Cm_e D is not applicablefor TPS mass estimates of orbiting space
stations or vehicles operatingunderdifferententry conditions.
1_o vs Vde
FIGURE 2ESTIMATING CURVES
Manned Spacecraft and Spa(e Stations100' ......... .t................. ' J : J_ _ , , _,,,,,,,,,,= ! ..:........._...-..L.._.....:..._...:-........................... . --;........._............ _-.--;.-.._'--.i--.......... -'_.........................1 LEGEND. I_..........,..-. ! ....._. _.-.._-.......... 4.................. _ O Vehicle Gross D_ity, Rt_ G not Including TPS Ii .........F---_-----_---'H--'i-...................... A ..........._.......,.....i.....i...4-..i-........... t .......................] Vehide BodyStructureDensity,Rhoh_not Inc.TPS I.,.........._'............, ,.....:..._...:._;,t,
• i : : : :r I [] Thermal ProtectionSystem Density,Rho,,, | I i , i i i ]..................................... •l -r-- • ........... t'"'1"""t ""'!'"'!"_" -
IB 2A .... iT i t i i lI
i
Density I 0- aya-.r--i-__..,___ DATAPOINTS:
Rhoe -'--_-_---::_.---_..-. ::.':: 2A. Gemini Reentry Module3B. ApolloCommandModuleRho b I"_. .._ _,.. 3 ....4
_IB_"'-_'E 1-..:_ ..:, ._ 3E. ApolloLunarModule-AscentRh°_, ........................... . ._ ........ (pressudzed volume only)
o Rhotpe :,, "- 4C. SkylabMultipleDockingAdapt....... 4F. Skylab Orbital Workshop"'- 6A1. ShuttleOrbiterCrew Compt.| I i r'°- ,
(Ib/ft3) I i i "'i....... 6A2. ShuttleOrbiter Bodyi i i | i .... .i-................ , .....
::: _ Rh% = 67.58 (Vde "0'24) :'-"i:::::::::....... !
.... _ "Rho b = 10.42 N .oJT_ I .......'- de " ""T ........ i i _ i
....... [................ [:j *..... RhOy, = RhoG - Rhob = Syst.Mass ..Curve = Rhi ! I !....... _"................ _ i E _ '
=s7.76(v,, ' i i,--.. --*-,1-................
"" Rhotp = = 26.54"'_ (Vd i !,'_0.1 -__ _ .i
I00 1,000 10,000 I00,000 ,_
Design-EnvelopeVolume, Vd_ (ft_) C_',Ooo
JSC -26098
The plots of figure 1 can also be found in reference 2 which was published in May 1971.
oAt that time, data for the Skylab Program and the Shuttle Program were not available. The slope of
the curves were determined from other large bodies such as aircraft.
It is pointed out that variations like + 15 % for MG and +35 % for Mb are entirely
reasonable for fast-level estimating during conceptual design. This is substantiated by the fact that
some mass estimates of previous vehicles grew more than 50 % from concept to operation despite
the benefit of considerable effort in design and analysis. There is more discussion on forecasting
mass growth in Part 2 of this report.
Figure 2 shows a plot of mass density versus design-envelope volume for gross vehicle,
body-structure, systems, and thermal protection system for non-winged, manned vehicles. This
plot is the same as figure 1 except that mass density is plotted directly instead of mass. The overall
trend of mass density with changing vehicle size can be seen in this figure.
Figure 3 shows a plot of mass ratio versus gross mass. The mass ratio, MpfM G (also
known as mass fraction) is defined as the usable propellant, Nip, divided by the vehicle gross
mass, MG. Several estimating curves have been developed from the hardware data points.
Significant data points are identified for clarity.
The fast number of the data point refers to the project, the following letter refers to the
stage or module, the subscript number one (1) refers to the in-flight condition without interstages
and adapters, and the subscript number two (2) refers to the ground (or pre-ignition) condition.
Additional subscript numbers refer to other identifying conditions. For example, 3K1 is the
Apollo Program vehicle (3), the Saturn S-l/stage (K), in the in-flight condition (1).
Data point 71, Centaur, is without insulation panels which are jettisoned during first-stage
boost. Since none of the other data points reflect jettisoned insulation, 71 is adjusted to 73, which
includes insulation panels to make the data compatible. The circle symbols represent stages or
vehicles propelled by LO2/LH 2, the squares represent liquid storables, and the triangles represent
LO2/RP-1 propellant. The diamond symbols represent studies of LO2fl-lydroearbon propelled
winged boosters.
JSC - 26098
Algorithms def'me Curves A and B, the two most important relationships developed to date.
Curve A is applicable for the preliminary sizing of LO2/LH2 expendable stages while curve B is
more applicable for LO2/hydrocarbon and liquid storable expendable stages. Note that there is a
range of values of propellant bulk density between curves A and B so that different values may be
used to estimate the mass ratio of a given stage mass for a given propellant density. Bulk density
is the average density of the usable propellant for vehicles with more than one kind of propellant
Figure 3.1 is included to more completely and dearly identify the data points that were
considered in this study.
Figure 4 shows a plot of average areal density of body structure versus design-envelope
area. Historical pressurized and non pressurized vehicle body structures are used for curve
development. There is a general increase in average density with increasing area. Also, the more
simple structures are near curve A which represents the minimum unmanned values. Curve B is
the minimum, manned values which is represented by the Mercury reentry module, data point lB.
This data point has a design-envelope area of 139 square feet. Curve C is the average, manned
values. It should be noted that most of the data points near curve C are pressurized body
structure_.
It should be pointed out that curves A and B define the minimum of density per design-
envelope area for unmanned and manned body structure respectively. Therefore, data points can
be above these lines, but additional scrutiny should be applied ff a point falls below these curves.
Figure 4.1 shows a plot of average areal density of body structure versus design-envelope
area for launch vehicle shrouds and adapters. This plot indicates the same slope as found for
figure 4. In fact, curves A and B of figure 4.1 are the same curves A and B of
figure 4. Curve A' is the average of curves A and B and is also shown as a formula in
figure 4.1.
Figure 4.2 shows a plot of propellant tank body-structure mass versus volume for a
number of different vehicles with a variety of propellant types, tank sizes, and shapes. While there
appears to be a considerable scatter of values is should be remembered that this does not
necessarily mean that the data are not applicable to conceptual design where there is a constant
change of input parameters. Solid lines paralleling the curve fit for MTNK bound the + 30 %
variation for the larger volume tanks.
11
F[GURE 3
1.6 ESTIMATING CURVES
i _ ;....
X :LO_/LH 2 ........ i ....... i ..... :....
LO_/RP-I _ i : : :
on .............,.... : :.......,,:,LO_/HYDROCFIRBON ..... CO V_" T| NR1L'E"_ "':'"
LIQUID STORRBLES ..... gT_IFF'B'NEO ....... i'" : i L-4-._'._-i_;--_IIf-1"'6"/'''!'''0, 9 _ SOLIDS ! _ : : : . "....... _....... ':..... ;'"
b o
: : : -3K : :
• : : : ..... J,_...r"_.... _.... : G.CI! ....... _....
! i "i .... :
IIIR_S ........... c......... :'"".#RUP'E[. , . . !'""?'_"_J; .... : :: obC.K..i60 Oi...... :: ' :'" .;FIUTT_E ' L|.TI_H....Ii.V,....... !........ _......... :..... .
• . . • . • . ' • IRATIO : aEt_,' -:"S._OR_B,'E".'""'C)"'"*_"'"'..i---_.i.S.TEP-...O.i........._........P-.C' '.......28": i .........:
0.8 ::......... i ...... :.... SB 1, TITRN IV, STEP 2(SN_CT) ................ !........ '..; ....I_;C _S:I_LIDI ES
Ix) DRTR POINTS: _ : (73.46 PCF BLK DENS) _....14.LHGE,Q-_
Mp/MG 3K 1. S-II IN FLIGHT '_ilE_.:.T;._._.*:;.:.9C1" (74.07TITANfV,PCFSTEPBLKI (,,,L- : :3K 2. S-II GROUND I:
--'" 3L 1, S-IC IN FLIGHT '_....
----ii 3L_. s-_c GROUND_i.... CURVES :--.. 6C 1. SRB (PRE 51L) l'_.... Ill Mp /M G = 0.3006 + 0.1889 (IoglOMG) - 0.0132 (IoglOM _ )2
0., ? --- 6C_. SRB (POST 51L) --
--'" 71. CENTRUR MITHOUT ....INSULRT ION PNLS ,2B
Mp / MG = 0.2945 + 0.1669 (IoglOMG) - 0.0107 (IoglOM _--.. 73. WITH INSUL PNLS ii ...._" S 1 .RTLRS IN FLIGHT
--,. 6_. RTLFISGROUND [i..... _ I ! _!i' .............L.......L.....i..I ! ! i i, : : : I..Li.::.::.I "e.s
5 58 586 50egI le lee 1 see le see
M , (;ROSS rJR_S OF STAGE OR VEHICLE, THOUS OF POUNDSG
NOTE: Mp IS USFlBLE (MFlIN IMPULSE) PROPELLFlNT MRSS.PFIYLORD IS NOT INCLUDED IN STRGE OR VEHICLE MASS.
PIRDATAel CCSD IJH 2G AUG 93
o_
_DDo
FIGURE 3.1ESTIMATING BASIS
t,g ......................................................................................................................................................................................................:..................-- i
Z PROPULSIONVEHICLES-- 0 :
- i _-- 82 _ 3L 1I
- NOTE: SBi [] 3K, _ _:- : sc. Q
- . ss. ,,/.c ISB sEoo. : u:-- USRBLE MflIH-IMPULSE [_]<.-_ JSC S?UDY 0
PROPELLRNT ONLY. RCS 0 : SHUTTLE V SC (PRE 51L)
MRSS --,, RND MID-COURSE COR- ?_...:.-ST_RB_E ....... v , . -- ---_'_J-":_'§b ":'''_'sc''(POS_'_'I'b)''''-- RECTION PROPELLBNT IS STRGE: '-- TRERTED RS INERT MRSS. . i
RRTIO - PRYLORDS RRE NOT INCL. 0 3J 2 :
_0.8-- ,................................................
-- 3F-- ' WINGED
Mp/MG - LEGEND= [] 0 _2 0 BOOSTERS
0 LO2/LH2^ ORTR POINTS: BB. SHUTTLE ET (REF)_ LO2/RP-I 3C. RPOLLO SERVICE MOD 6C. SHUTTLE SRB
6.7 --- _ LO2/HYDROCRRBON ......... _C .El .... BE, RPOLLO LUNRR HOD(R) ?. CENTRUR-- _ LIQUID STORRBLES 3F. RPOLLO LUNRR MOD(D) 8. RTLRS
-- V SOLIDS 3J. SRTURN S-IVB SB. TITRN IV (STEP 2)
LUNRR: 3K. SRTURN S-II SC. TITRN IV (STEP 1 )•,,. ............................... :................ ;........................ MODULE .......... 3L. SRTURN S-IC SD. TITRN IV (STEP g)
-- " ' LM(R} NOTE: SUBSCRIPT 1 IN FLIGHT; 2 OH GROUHO.
Mp/MG=e_½7
0.6
! 10 100 I 000 10 800
M , GROSS MRSS OF STAGE OR VEHICLE, THOUS OF POUNDSG
ESTFOR13 CCSD WH 26 AUG 93 0
FIGURE 4
ESTIMATING CURVES
100 ..: .._ BODYSTRUCTURE
__iii_iiiiiI ORTR PO I NTS: 3J, RPOLLO/SRTURNS-IVB STRGE i_iiiiiiii i
5 _ IB. MERCURY REENTRY MODULE 3K. APOLLO/SATURN S-ll STRGE
.......... 1D, MERCURY RDRPTER SECTION 3L, RPOLLO/SRTURN S-IC STRGE .i...!..}..!
2R. GEMINI REENTRY MODULE 4C. SKYLRB MULTIPLE DOCKING RDRPTER! i i i.......... EB. GEMINI RDRPTER STAGE 4F, SKYLRB WORKSHOP i'"!"ii
3B. RPOLLO COMMRND MODULE 5R. RPOLLO-SOYUZ i i }i.......... 3C. APOLLO SERVICE MODULE 6R2, SHUTTLE ORBITER L..L.L:....
30. RPOLLO SPRCECRRFT LM RDRPTER SB, SHUTTLE ERTERNRL TRNK ! :: ! !
3E, APOLLO LUNAR MODULE, RSCENT ' _ _ _ ! _ _3F. APOLLO LUNAR MODULE, DESCENT i :: _ i i r-] 3L i _10 .-. D
_".... i...... ............2..........._" " -- " I]B
L ; _ ! ! : °............ t ..?.._..?.-:................ :......... :...... :......... :...:-.:.-:
........................ ; NOTE: MbIS MRSS OF BODY STRUCTURE IN POUNDS. "':":'":': "''""!" " "i-""_"" ....,,,,.._,_,._.'....'..,',.,....._...',..',,._......:....,..;-..-,,;..-
............: CURVES: .._...i.•_': : :. LEGEND:
: R MINIMUM, UNMANNED, Mb= 0.71 (Ade) 1"15 i i /..%............ _ _ MANNED•._., i. :
_ i B MINIMUM, MANNED, Mb= 1.27 (Ade)1"15 i i i PRESSURIZED
: (Ade) 1 15 E] UNMANNEDC AVERAGE, MRNHEO, Mb= 2.00............ " NONPRESSUR IZED: I I III
i : i If iii i : i l i !i, ! ! ! '' 'I I I l iiii I I I i l I I I II I I I,,t III
5 5 5 5100 I 000 10 000 100 000
DESIGN-ENVELOPE RRER, ha, (SO FT) _oESTFORIH CCSD WH 26 AUG 93
c_okoDo
FIGURE '-I.I
100 ESTIMRTING CURVES
- 'iili- BODYSTRUCTURE i _- : : RDRPTERSRND SHROUDS i i i : :.': . _ :_!
- OflTR POINTS: NOTE: ! FIje IS SIDEI.IRLLRRER-- [0. MERCURY RDRPTER M b IS MRSS OF BODY OF RDRPTERS, SHROUDS,
2So GEMIHI RDRPTER STRUCT IN POUNDS
_ 3D, RPOLLO RDRPTER (ORSHED LINE CURVE)R n RHD IHTERFRCES OHLY.BR, RTLRS/CEHTRUR SHROUD
9B2. TITRN IV SHROUD = 0.99 (Ade)1"15 CURVES R RHD B RRE RLSO
9B3. [US SKIRT (TITRH IV) _I SHOWN IN FIGURE 4.
............i"::"-i'""i........i"-_"i-_.-I..............._........i......i........i'-!-'i'i-l................i........._---_Tii--_-!.................!.........i......!.......i--i--i-i-
............_........._......_.-..'.-._.-+..i.+.................-........_......_......._i_...............i-_i........_!ii"__-:'__
............__ "--"_.__._ -_:'":'_"-__:: ....i i i IFT'TTI..............._.... •
c_ Mb/F)¢I e ' _ : ,: ( " _:__....-------T, ," _ -(-_'+.' ,_: -30 i'\i ._._L_ _. _ i_
( LB )/( SQ FT ) _. --: -"--:,,°;"0.' :::::::: _ :_::!!:' :! :! ._'-:CUR_/E..... R" i i i i i i i
............!.........!......!........_...:..:..:.. ..........................;.........;................i...i..i..i................}.........::.......::.........:'"i""_":.................._........._......_........_'"_"_"_"
............_.........;......_........!...:,..!..!.................,.'........._......_.........¢...;.._.._................_.........:.......:.........:..._...:..,.................._.........;......;........_..._.._.._.
............i.........!-i.........!i!_.......................i-..............!-.;..i-...i.i................i.........i..-_-.--'-ii-ii..................._........._......:,...,.._._..i._.
i i ! ....'.............._ _ _ _ ....i-.-v!!!................".........._......'....
..........................................i i! ................iiii.................................... i:;i5 100 5 1 000 5 10 000 s I00 000
DESIGN-ENVELOPE RRER, Ra, (so FT) ,_ESTFOR_I CCSD _JH _G FIUG 93
FIGURE 4.2_" '! _ _ i"
........_......_'"'"..............._" " ESTIMRTING CURVES
LECEHO: BODY STRUCTURE : =0 LOs/LH 2 IqWPIIL,LRNT TBNKB
! _ LOE/RP- | '7_"ILIQUIO STORRBLES +30 PERCENT
TOTAL BODY STRUCTUREINCL TRNKS, TRNK SUE,
: : ! : INTERSTRGES, RNDt0 000 _....,...
_....._.... i !"-.'i" _..... _B"!"i-ii
POINTS: .................. ,._ERC.EBI.i.
1, SHUT ORB RPU PROPEL ............ _....... :'TRNK'S"'RND!"TRNK'_'!8. SHUT ORB OMS PROPEL ............ _........ INSUL.D.HL¥.,..._._.I._S. RPOLLO LM RSCENT (RVERRCE _URUEi4, RPOLLO LH DESCENT ............ _. ZERO PERCENT_
5, RPOLLO SM FUEL ! i ' 0.7_
TRHK S. RPOLLO SM OXID M._NK : V TNK )1000
flRBg _... i--.-.;"" _ ' ............._.......i.... �ž�n�r.._..,..i..._ !
........!'"_'_T"e_k "'_'"'_""_"' : : : i
MTNK ' i'(_ ............ _...... 15 / i ! ! !L
POUNDS i i- , i........ ¢....... ;"'"_ ...................... ' ............. _...... _'"'""" 7, SRTURN S-IC RP-I
B, SRTURN S-IC LOX
100 / 9. SRTURN S-II LOX/LH2'"' }... •............_......_.....,................_......!'""_"" 10. SRTURH S-IVB LOX/LH2
............;......:'""_"' : : : 11 SHUTTLE ET LH2
_ : ' : : : 12, SHUTTLE ET LOX
_H_..._.._HO...V_L.U_E 13. TITRN IV, STEP 2INCLUDE TRNK _1_ |T_UCT_ I_HD 1_. TITRN IV, STEP I/
.......IBNK'"BOOY'"B_RU__RE'INSUER¥|OB_
101 10 100 1000 10 000
v_NK TRNK VOLUME, CUBIC FEET
TRHKSB1 CCSD WHO
JSC - 26098
Figure 5 shows a plot of systems mass versus design-envelopearea for a number of
different types and sizes of vehicles. It is importantto point outthat the systems mass referred to
in figure 5 is the INERT MASS (see appendixB) of systems but not including structure, TPS,
main engines, main engine systems, crew and passengers, and crew andpassenger systems. The
mass for structure, TPS, crew and passengers, and crew and passenger systems are estimated on
an individual basis in this report.
By using the datapoints that are available,curves A, B, andC are developed. Curve A
represents the systems mass for non-winged reentry spacecraft sized for one or two crew
members. Curve B is similar to curve A, but is used for sizing vehicles with largercrew sizes.
Curve C can be used to size the systems mass for winged reentryspacecraft.
Mass allowancesfor personneland personnelprovisions can be calculatedby using thecurve in figure 6. Values forfixed and variable items mustbe accountedfor. The fixed valueof
310 pounds per crew orpassengeris a minimumvalue that accounts for a person and seat only.Variablemass includesitems thatare affectedby the numberof missiondays and the numberofcrew andpassengers. Examples of items that am includedin the variable massare food, water,
and clothing. The equationshown for variable mass in figure6 was determinedby performingaregression on the six data points noted.
Figure 7 shows a plot of structureand systems massversus pressurizedvolume for a
number of vehicles. The result is reasonably good whenit is consideredthat there are vastdifferences in vehicle sizes, shape, type, mission duration,loads, and so on.
Again, it is pointedout that sUuctureandsystemsdo notinclude thermalprotectionsystem,crew and passengers, andexpendables for crew and passengers. These excluded systems are
estimated on an individualbasis in this report.
17
F IGURE 5
ESTIMATING CURVES108 : ; SYSTEHS
i.........}""":.......'-_" VEHICLE, FIXED .: : : : : (INERT MASS OF SYSTEMS BUT NOT INCLUDING ......... !...... '_. ......?....
......... :.._...._ ......: ....: : : ! ! STRUCTURE, TPS, MAIN ENGS, RND IIRIN ENG SYSTS) ,_.
f : _ : ! i
....... DRTR POINTS: ..............._ :: !lB. MERCURY REENTRY MODULE ............... _......... _...... _.....
2R. GEMINI REENTRY MODULE !HERMES -
2B. GEMINI RDRPTER SECTION ._...,! ....3B. RPOLLO COMMAND MODULE /
SR. SHUTTLE ORBITER /-/':f
10: _ "'>"":....... !
#_....... ; ....... i ............... ( ......... ! ...... } ....
SYSTEBS : :
MASS !/ : : _BOMBERS AND TRRNSPORTS i i
.... "': "i......;'"'t'"'i'"::_ REW'_IUM BER '"('2"'" TO"'S" _'"i"i' !': : :: F-16 ', : : . . . :: : :: 1 _ ._R + EB
M s y s ....................... V :'" :'"'" "" : 1oo CUR E _i ,-'.'.'" ('REFERENCE')'}"i('.R. EEERENCE)'''''': ......_........ i'"i"i"}'
........... =......... _......"......... : ..._...:,..!..
i CUR V_. iR i' "" * BUT RLSO NOt INCLUDING CREW ANDTHOUSANDS : : : J_ PASSENGERS AND CREW AND PRSSEHGER
OF • SYSTEMS.1
POUNDS ....................?_ NOTE: Msy s IS MASSOF SYSTEMSIN POUNDS.: CURVES:
i Rd e)0.56............ _: R REENTRY SPRCECRRFT, NON-WINGED, CREW (1-2), Plsy 5 = 97.86(
........... _': S REENTRY SPRCECRRFT, NON-WINGED, CREW (2-3), M SgS= 13H.99(R )0.56
............ !. C REENTRY SPRCECRRFT, WINGEO, CREW (½-7), Msy s = 208.49(Rde) 0"56
: _ iii _ _ _ _ : _ : iii : : :
100 1 000 10 000 100 00EL,DESIGN-ENVELOPE AREA, Ra, (SO FT)
ESTFORI5 CCSD UH 27 RUG 93
FIGURE BREFERENCE: ESTFOR31 ESTIMATING CURVES
_':,,.,.,_ ...... 2.,.._.... _,'-.:._........... :--.---"......... /. ......................................................................,.........,.'...:.-:..........._....-.:. SYSTEH$ ..._J.._...._...,.._..;.i.;..........i......;...._...,..._..i._._........;......"' i !! ::_ :i::_::l:".::_:!:!.:::::::::t.::::_::::i:[ :i:__:- ......_......:...-,.. :::{: : ..........+.....i. CREW RND PRSSENGERS: _ ! /: : _ / :::: : : : I ::::
i : i : ::: /" : : : : : :: : : : : : ::, ........"..,..i..,.i...'...i..'.i.i...........i......L..L.I.i..i.i...........,......_...,..[ ..._,...,......!..,'..1,','.'"............"......_+-1!-'_-iDATA POINTS: : : : i:::: , : : : ,:::: : : : : ::::
; : I :;;:, _ ! ! ! ! !i_ _ ! ! i iiii
IB, MERCURY REENTRY MODULE .... i...... i L.l..-i-j_ .......... i'"'"i'"'i'"i"i'_"ii ........... i...... i'"'i'"i"i"i"i';....... 2fl, GEMINI REENTRY hODULE ..... . ...............
i 3B. RPOLLO COMMRND MODULE i qF h ,/_-ii i i i i i iii i i i i i iiiI e _e_ i_ _E. RPOLL0 LUNRR MODULE : _/ :::: ! ! ! !!!!! ! _ ! _ i!!!
---.i-7"'Z! _F. SKYLRB 0RBITRL IJORKSHOP .... ;......_.../...,..... :+.'.._........... :,.....,...,_ .... _..:..:.:........... :...,.._.,--t..... _..:.._._
=::! iiiiiii2 i iiiiiIiiiiiiiiii iiiiiiiiiii:iiiiiiiiii i: iiiiiiiiii iiiiiiiiiiiiiiiiiiiiiiiii i:iiiiiii;H -- 1 1¢ p V ......... _....._....=..... _-_._.;........... _.....$...:...' ._.Li.i ......... _ ......"...'.- -._.._-':._............ "."...... _-...-..... .:._..;_............ _...... _--.._...1-.;-_..;.;
........._.....'......,...,_.._._._..........................!..i.!:-/--i ......]-l-i_] ............i......ii ....i iiil ..........i......i l.....i ili: : : | ; :;: : ::; / ; : ; I ; ;;; ; ; : l ; ;;; : : ; I ;:::
.........:,: .......:,,............,:, ....._) ........i......!!_!!!_ ...........i......i Hiiiil ..........._......i ili_i_i ilili i ..........6R-- _ _ _ i _ : : : : : :::" : : : : ::::
: : 1 ' : " ........_ . MASS 1 eee I ' I ; _,;: _ : : .,_[ i :._ I:.:.:.:. . .. ,,..., . , ,.._.._1_ ........ :......:... .:................. ;...._._ ...... _.'............
: : : :.:: • • _ i:i: :::::::J2 NOTE:........ :......:'"T'" "'T':'": ........... ! ......:.._;.. :i__ • ........ is i:::
; : : I :::: ........ _ " : L..;._._._.............:. FIXED MASS:........i......i_"""iii _"'_....._";'!"_.............: : :: Mopf 18 MASS OF CRE'WAND PASSENGERS........ !......!.........I _'H':.........._ .........t'-) _! _! THAT IS A FUNCTION OF PERSONNELONLY: : : , : : : : , :
POUHDS : : : = ::::........ |......_'":" "_.'":':....._/'i" i_B "_i_i ............:- - 310 (Ncp) IN POUNDS.
: : :'_,'_ !i VARIABLE MASS:Lee 1....., ......,..._......:.+:.,...........: ...._....:.....,.;..................•--_/_.-._................. '.........._'_".:".'............_ IS MASS OF CRE-'tNAND PASSENGERS
........................ :"..................:....:...:'"":""':'"":'"'_:_:i:::::::::::::_ _i:: :::!:i:_!:::::::::::: Mcpv_ : _ :, :;:! : _ : THAT IS A FUNCTION OF PERSONNEL AND
........i......i..Z...I..__.i._.i.I.........._......L...:.X...iJ.::_............. MISSIONDURATION: :IT :::: ; : : .::: :
........_...._L.;..I..+._._.!.I.........._......i...._.._..:-J..........- - = 8.20 Nd)1"18INPOUNDS.
, . .. : :, i _i I!ii. i _i I_i.. s _
1{} lee 1 eee le eee
HcpH d or" (NUMBER OF CREW AND PASSENGERS )( NUMBER OF DAYS)r/}
ESTFOR1G CCSD WH 27 RUG 93 ('3t'_
oo
F IGURE 7
STRUCTURE AND SYSTEHS•. NOT INCLUDING:.......:......_...._........... o....i,...!.._
....... (....... "."'"_..... THERMAL PROTECTION SYSTEM, CREW FIND PASSENGERS ......... :....... '......:...RNO EXPENDRBLES FOR CREW RND PRSSENGERS
........ ! ...... {....¢.,.
......... ) ...... ;....|,..
STRUCTURE PLUS SYSTEHS
leg gee rls + Msvs ::i::i:i:i_F.::.:..-.:.....g. 62 ....... ; .......:'"
: 187.86 (V ) • • •r
1. pou.os t" ....... ......_.,..;..,
HI_SS _ ::: : : :'":'" ._:T_it n_r-_.'" ".."': :::: ! !
' i i _ : : rRiU.CTURE
o 1g egg :::::::::::::::::::h .......... _...... t....t .............. :.....,1 ) ............... ;...... _-..._ ....
: _ DRTfl POINTS:POUNDS ........i......_...._.... ...
........; ......;"7," i.- lB. MERCURY REENTRY MODULE
!/ ! 2R. GEMINI REENTRY MODULE
I 888 /: 3E. APOLLO LUNAR MODULE ASCENT3B. FIPOLLO COMMAND MODULE
•_ i qF. SKYLAB ORBITAL WORKS:HOP: : 6A. SHUTTLE ORBITER CABIN
" fill tiiiit188 I Dee 18 gee 180 egg
Vpr , VOLUME PRESSURIZED, CU FT uoESTFORL}5 CCSD WH 3g AUG 93 Ib
o_
@0
JSC - 26098
Figure 8 showsa plot of DRY MASS versuswetted areafor a number of vehicles, winged
andnon-winged, but all are manned. Mercury is the smallest hardware valuewhile the Shuttle
Orbiter is the largest hardware value. The Shuttle Orbiterhas been normalized to the other data by
removing the main engines.
The solid-linecurve fits the data well in that Mercuryrepresentsthe left end point, Hermes
represents the mid point, andthe ShuttleOrbiter represents the right end point. It should be noted-,a
that all except one study data point fall on or above the solid-linecurve giving credence to the mass
. values obtained. The lone exceptionis the Shuttle H studyvehicle of 1988. Therefore, this curveshould be used to estimate the minimumDRY MASS of a vehicle under study.
The dashed-line curve is 15 % by mass below the solid-line curve for a given wetted area.
This represents a reference curve for the possibility of improvingthe overalldesign technology.
A rectangular grid plot is shown as an insertin figure 8 to illustratethe differencesin the
two different types of plots.
Hgure 9 shows a plot of DRY MASS versus wettedvolumefor the same vehicles of
figure 8. Essentially, the same may be said of wetted volume as was said for wetted area except
that the scatterof data points is greater. This indicates that the DRY MASS is more areadependent
than volume dependentand therefore wettedarea shouldbe used as the preferredestimating
parameter.
The solid-linecurve fits the hardwaredatawell and again,all of the studydata points fall
on or above this curve with the lone exception being the Shuttle II of 1988.
The techniques presentedhere are good for developingmassestimates for many different
vehicle types during conceptualdesign. Other techniques exist and should be used when
applicable. Comparing resultsfrom differentestimating methods is always a good practice.
21
FIGURE 9
ESTIMFIT ING CURVES
....! ��O�:::i:_RY HRSS _NOVOLUH.,E ..... .i................_.........'...... H..i
R B t i: ZZ::Z:Z ZZ _ -.-I-..... ::: ii
iiii :::]iii ::::iii :::ii..::._i_.::..@i. i i i[/ ! K"L__@,-7_:,_g-;:?;;GG; \ : ] [i!!!!_..:i H............... .....
::i_ :::::_i ::::iWi":::i:i_i.._..l_._.._..e_ i / ! : : " : i _ ! : : : : : :............................................ : : : : ' 911_11 . : :
..........................,,,......,_,:::::::i:ii::::iii._i i __/ ! _ :,,, /£/. _I ORB1
................... .: .: .' : : sc_,_oo_e(_ux) : : SHUTTLE: : : _ m
iiii :::_ ::::._iiil:::i'Gi_:::::ii_i'.::::_iW_! ! _i : : : : as¢(_o,> : :10 e z-.'z: ::::i_iid@:::::;:::: :::::iiii
I
llll_l .JllllS| ..lSl_d ..|.?.1.11_,,.Jl_lJ ,:: |IlSi " ":."l "l.""_" ? +": : : : HEllaE_i,_l . !
DRY ii.i_::::iWii ::::iiiiii ::::i_ '.::::_ :::::_iiiGi....!...i....L;..+..,.,,.,,_..._,,,_,..:.......;.... LESS 15X.................................... : : ; '. : : .
.................... ""? ....... Illr,:o ........... :......... : ...... _....
MR89 ..am ...... .-........ tile ....._11 .......,1, _ ! ! i FOR TECHNOLOGY
--url- ::::_,::::::i_i!!ii!_........................:::::_•"...._"' ............:...................................................................... , : ::1
_ _1"111 ..I._I_._II'N..III_'"'ILII ._.?.Tl"'ll?.................... I15_111_"'_E_'_SC'. ( IN POUNDS ) e * ? l
THOUS ................ HERMES, p! M D : 95,09 ( V d¢ ) I_1| ...._ll ............................ ll_l£1l I ; "i"'';1 _'1• 111 1111 Ills I1_ II! : "
,,,,..,.,,:..,,,,_..,._,..,,,.....,,_: o:o 4.IiiiFiFiFiFi ii ___ i :(_e i !! / ._._Ei....y...!...._..i,.;.._E_,..;;_......i.... 'i E !
16............__ ,_.........,....;............. , oA,.E .,,:ME,cu,._I,,,.,.o.oo,1_0!...!...!..!:::::::::::::::::::::::::::::::::::: _c : cE.,._ _ _ _ _.... ....... .......i'...... i':_,w" :'' .i..i..i- G- .__ 'q''_E_S''''" _''''" ".'''" "" " "''" _ "'" "_'" 1''_ "'" "'i' "''' _
............ !................ ."......... :..._..:._. GEt$1"_l MASS MPROVEhENT
............ ,................ :......... :-.-:..._..;.._. .'X .. --_............i.........:.....;........._...L_...:...........G!........._......... _--_-_- "o -i ! i i id i_[ E.::_ , , ,........,____- " : ,'l fl ,HOUS•' I MASS IN POUHOS [_ ,._ .............. 7r..>.: ............... I..nm,_It:':..I ........................... LBS
: . / : : 17_o : :
I A.AR(_Z.so_T_i:: 0 / i_... _:,.,,_._-.i_, i i....I ', _o,_,,,.|_, ...i._'l; _ , __1 _ i ;,Y,,,,,,I,,,,i,,,,I,,,,i,,,,h,,,i,,,,i,,,,i,,,,i,,,,i,,,,I- ........ -...................... .......................... .... -.
: : : . : : : : * • . ) . ; . ; .
166 1666 16660
VOLUhE, V de CU FT _,MASSFIROG CCSD WH 24 AUG 93
_D
JSC -26098
PART 2 - MASS FORECASTING
A vehicle mass-growth forecastis madeafter an initialmassestimate has been derived.
Mass forecasting applies growth factors to mass estimates in order to predict the vehiclemass at
final production. Historically,vehicle mass estimatesgrow as the design become more mature
based on many reasons. These reasons include items left out of the original estimate, requirement
changes,ballast, and installationitems among others. As the vehicle design matures,appropriate
reduction of the mass growth allowanceshould be incorporated.
Forecasting should also predict the effect on mass of emerging technologies. New
technologies often reduce mass by increased performanceor by reduction in size. New lighter
materials, offering greater strength and stiffness, is one example of increased performance. The
cost benefit of the new technologiesand materialsmust be estimated and weighed against the
possible mass savings.
Parameters suchas vehicle density andprogramdurationalso contributeto massgrowth of
aerospacevehicles. Vehicle density in conceptualdesignis a design parameter that indicates thepotential for mass growth of aerospace vehicles. Low density allows volume for mass growth.
Vehicle program duration, from concept through operation,is usedfor forecastingthe mass
estimate (growth allowance included)made in conceptualdesign.
Figure10 shows data that pertain to the massgrowth of a vehicle duringthe development
phase. Generalized massgrowth curves forvarious NASA vehicles are shown to illustrate the
types of curves as well as the magnitude of the growth. The mass growth ranges from 10 to 60%.
The growth curve shown for the Shuttle Orbiteronly accounts for growth duringthe Phase C/D
portion of the program. Therefore, for this one curve, concept is meant to describe the vehicle
maturity at the beginning of phase C/D. Earlier phasesof the Shuttle developmentare not shown
due to changing requirementsandconfiguration.
Figure 11 shows to scale the Apollo Spacecraft as it was conceived in 1961 and as it
appearedat the first lunar mission. Note that the mass of the 1961 configurationis 58,220 pounds
whereas the final configuration in 1971 is 116,265pounds which is a factor of approximately two.
The masses are for the gross launchconditionwhich includespropellants.
25
FIGURE 10=
HISTORICAL MASS GROWTHi =1 H i
DATA POINTS:lB. MERCURYPJ_FI_t_YMOD 4F. SKYLABWORKSHOP
2. GEMINI SPACECRAFT 4. SK__.,_ SPACECPJ_.FT3B. APOLLO COIV_'D MOD 6A. SHUTTLE ORBITER3E. APOLLO LUNAR MOD (A) (PHASE C/D ONLY)3. APOLLO SPACECRAFT
I
60 --4F
3B
40 -- 4
MASSGROWTH 1B
(PERCENT) 3E
CONCEPT OPERATION ,
PROGRAM PHASE
FIGURE 11
RPOLLO SPRCECRRFTCF _ ( 1961 )
REFERENCE: NRSR PROJECT RPOLLO WORKING PRPER NO. 1031
LES RPOLLO SPRCECRRFT WEIGHTS RS OF OCTOBER 2, 1961 220"O
150"0 116"0
CM _ _'_ ...... r :_-,.......o._" : f \
............. _ ..... = ..... _:_ ..........SM1 ,
RDRPTER ; , , , ,! .-.......j_ I /LEM S ice
_ INCHES
-- 170"0( SHI"
TOTRL LRUNCH WEIGHT = 58220 POUNDS
RPOLLO SPRCECRRFT(1968 RND 1971) ................
'e 100 IINCHES _ .............. -'/
260"0982.2"
TOTRL LRUNCH WEIGHT = 108932 POUNDS (1868) ¢__5
116265 POUNDS (1971), ¢.,)
RPOLDReB CCSD UH E5 AUG 93xooo
JSC - 26098
Figures 12 and 12.1 show the Sk-ylabmass growth based on the initial mission
requirements of October 1, 1969. The curves extend to the launch date of May 14, 1973.
In figure 12,the curve labeled combination is for all of the modules combinedof Skylab
which are identifiedunder the legend. The combinationcurve is divided into the design process
curve andthe missionrequirementscurve. The designprocesscurve reflects the mass that the
contractor has the responsibility for whereas the missionrequirements curve reflects the mass
increases that resulted due to changingrequirements imposed on the contractorby the customer
after the initial mission requirements.
Figure12.1 is for the SkylabOrbital Workshoponly and shows curves that are s'nnilarto
those shown in figure 12. The Workshop reflects the largest of all the modules. Two large
increases in mass are shown in the last half of 1970. The fwst is crew-relatedsubsystems and the
second is crew-related and electrical-related subsystems. These two large increases are chosen for
example only.
Table 1 shows the detailed listingof the changes that comprisethe two changes above
broken down by mission requirements and designprocess.
Figure13 shows the ShuttleOrbiterdrymasshistoryfromproposal,May 1972 to
February1990. It is pointed out thatthis plotreflects PhaseC, D, and E only. PhasesA and B of
the Shuttle developmentare not applicabledueto changing requirementsand configuration. Phase
B extension datawhich includes expendabledesignsarenot included.
Appendix A offers examples of estimatingandforecastingthemass of varioustypes of
spacecraft. Each example providesimportant insightsfor thespeciftcapplication. To improve
future forecasting techniques, tools are being developed to automatethe processof allocatingthe
growth allowance as a function of design maturity.
28
FIGURE 12
TOTnL SKYLnB HASS gRG THRELATIVE TO INITIRL MISSION REQUIREMENTS (101G9) _L
PLOTS INCLUDE ALL MOOULES , _ /'!\V
+40 ........................................................................................................._ _ / ,_/-PS5114173 l \
196412 LB
+35 ........./ RTMCOMBINATION LEaeNO: r_ >\
PS iS PRYLORO flHROUO IRTH IS APOLLO TELESCOPE MOUNT I TMOR |S MULTIPLE OOCKIHG MODULE I
+_0 ....... _ RM |S AIRLOCK MODULE ..... Fi ]i., MDR: OMS |S ORBITAL WORKSHOP _ I
MASS !_ |u is INSTRUMENT UNIT (OF BOOSTER) _!RF:
R.
GROWTH +25 DESIGN PROCESS _ ! _LL
PERCENT +20 i i
: _'ILMISSIO H REQUIREMENTS,o,I,69i.° ..____!................ a......14025? _ ............._. ...... ows+15I
II
Ill
+10 ..... _': I REFERENCE: J:/
"v_" EO-_OOE-I575, SKYLR8 PROGRAM, PRYLORO INTEGRATION /
: SKYLRB .EIGHT GROMTH STUDY (FINAL REPORT)
MRRTIH MRRIETTR REORSPRCEo DENVER, COLORRDO eO201 ....... :+5 nucusT_7, isT_. L........ J ........
LRUNCH
14 MAY 73
1969 1970 1971 1972 1973
CALENDAR YEARO
SLGROWOI CCSD WH 30 AUG 93
FIGURE 12.1
SKYLBB O BITBL O KSHOP HASS G ONTHRELATIVE TO INITIAL HISSIOH REQUIREHEHTS (10/69)
+CO ...................................................................................................................... _............................................_............................................
I EHoo_-,,,s.,K,_. P,_RR,.PR,_oRo,,TEO,.T,O"J I SKYLRB MEIDHT GROMTH STUDY (FIHRL REPORT)
�ë.......................................................................... , ......................... I hRRT|N MARIETTR REORSPACE, DEHVER, COLORAO0 80201 ...
--_ ,ILEGENO: I [ AUGUST 2% 11119"3" ]U
_ I oMSIs ORBITAL.OARSHOP 5/14/73-- ( Iu I$ |NSTRUnENT UN|T (OF _OSTEm) 78195 LB REF
+60 ................HRSS - i ............................................................................................. _ .......................... OHLY_L_
GROWTH +50 .............................. ' l
COMBIHATION _
PERCENT +40 : owsCREMRELA_EOA_ELECTRICAL DESIGN IPROCESS :RELRTEO $UBSYS_MS CRUSE _ : ::MOST OF INCRER_. _
°/7o (SEETAaUinR _MISSIOH REQUIREMENTS I+20 .........'................'_: ' !
Z.................
II
+ 1 0 .......1.011.ZB9..L.. l...................._....................................................................................................................................5004? e LAUNCH
1_ MAY 73I
1969 1970 1971 1972 1973
CALENDAR YEAR
SLGROW02 CCSD NH 30 RUG 93 20
TABLE 1
SKYLRB ORBTBL WORKSHOP HRSS GOHTHRELRTIVE TO INITIRL MISSION REQUIREMENTS (I0/69)
NOTE: hRS$ SHO.N IS l" POUNOS. RUGUST 1970 HOVEHBER 1970SUBSYSTEM o.so. tottrs$ is $OOqTL$.
MISSION DESIGN MISSION DESIGho.$ ON S/t4/?g Is ?OlS$ LB. REQUIREMENTS PROCESS REQUIREMENTS PROCESS
........_.U_..._._R.R_ .........................................................................................................q..................................q.................................P...............................t_.!...........
........_B.q.!.o...ff._._.tq_.....................................................................................................o..............................ts.s..................................o..............................:.ka..........
.........!._U_.!.g_..._O..._.R.!.N_.....................................................................................................q...................................q..................................P..................................._..........
........_!_.DL_g._.R_k..RN_.._.E_.!._..._.E_ ......_._._._.......................................0.................................._..................................g..............................:.S_..........
........_..__L._._O..GR._ .................................................................................................q..................................q..................................0..................................._..........
........_.._U_g_._ ..........................................................................................................................q...................................q..................................g.............................._.2B..........
........_._ff._..._.!._._.,_......................................................................................................o............................._._..................................o..............................:.2.!...........
........_S_R._R_..._.!._.!._._........................................................................................................_2.a...........................t_2._............................t_a............................_.!.Oe..........
........_g_._..._._L_._._..............................................................................................................0...................................q.................................0............................t.!.9_..........
........_..._E_._O_E._..._.O..."_.".I._ ....................................................................................q...................................q.................................g............................t,l.SS..........INSTRUMENTRTION RflD COMMUNICRTION 0 -13 +3_ +8_
........£R_._...R_"_E_LS.YS_.E_.._._._ ...............................................................................q............................._2.S..................................0.............................._ ..........
........_._.._.E_S_._.q_.._.................................................................................................q...................................0..................................P..................................._..........
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........_!_B_.E...H_!._........................................................................................................................q...................................q..................................P..................................._..........
........H_.{..._B_.{_B_ ........................................................................................................._B.{...................................q..................................P............................tg_.!...........
........P.B_H..._.S_o_.q_Bzx.qBs....................................................................................................n_.s...................................q..................................P..................................._..........
........£B_H..._B_EB_ ..............................................................................................................tg.s...................................q................................t8...................................q..........
........_B_H...@._".L_Zg.H_GE.._B_..._R.R{_..................................................................t._._...................................q.........................._.2.!.5.............................._._S..........
............................................_._.!._.._.s._H_g.{.?................................... . _.3 ................................... q.................................. p.............................................., o
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........_EEZ_Z..{gq.!._ ......................................................................................................._.............................. t_.5................................ p .................... O
........_..._._ ................................................................................................................q.................................._............................._s .............................._.9_..........
..............CREW SYST.EMS...$Tg.@RGE. CONTRINERS ..................., +90.5................................._ q.............................., ¶3 ..............., 0CREM SYSTEMS SUPPORTS +593 0................................................................................................................................................ +I ..... +_38 ........
........ExEE._.!._E_.[_....................................................................................................................._.!.s_........................... :_s._................................................................................... +_I , +_s
[email protected]_._.;.NERS .................................................................................,[email protected]......................., Z._5p.3............................................................, 0 , +15EXPERIMENTS SUPPORTS 0 +ES 0 +qO
TOTRL +5138 -$68....................................................................................................................................................................................................................................._5 ........................._.2_.3_..._..
SLGROU03 CCSD UH 30 RUG 93_
FIGURE 13Ire -- •
• FORECASTING CURVES
• SHUTTLEORB|TEa DRY HRSSHISTORYI• (0V-I03)
100 ..................:...................:.................................................: ......•............ttRR 73 _FIRST 150K ' '
• " . FEd 9(
se "'tToK : ! I -: .... . ........ :.... . ":.:':--'_.- -" :-- ." :_ ....i : _-.,oi _:_u i ! iZ_-c:PP_US25
DRY : i _ :( : : . _. _ .. L)_ : .'. : i i i : i PERCENT
asc -< : I ._'L.=:' ':' ':'-.-':'.--': /K--'. thRSS e4SR C : P PLUS 2?
•............ ....i,..;;..... ..........................I//THOUS i : : i i [] : /'--7: :FLIGHT : i :OPE RTI:ON ! : i : i I (_' " : " • .... . ' ' . ' CURRENT
t_ I..; .... :.......... P.... .... : ........ / "/: ........ :RPR 81.: ..... • .... :JUN 02:. .... •.... :.../(_ C DESIGNE;{_ : : ' : ' _ _ :STS-I :STS-4 :L_ 15_'X68' X65K _"
• " ' R'P "R' I -- _ " •• POOSL _ . : • .OF :/,'_ P DES,ON L >._ . , :SLI - 2690 SO FT
:L-_ 15'XSe'X6?K _ : : :REF L ; 1290,3 IN50 ........."....................................................................................
"Sij = @898 SQ FT ' . " . " , , .... ." WET RREFI : 12021 SO FTPOUNDS _ REF L : 1328.3 IN ' ' ' ' '
•WET RRER : 11985 SO FT LEGEND:2{) --"" ...........................................
,.r-_--RTP 0 STRUCT + TPS P IS PROPOSRL ORBv •
JUL 72 [] REMRINIHG SYSTS C IS CURRENT ORB
10 "": .........:...." _i" "''":....:'....i:-....:' /_ MARGIN RTP TOPROCEEoISaUTHORITYi ; i i ^^i,, i i,, i,,,,, ,I 1701 I, 21_ I?q1_1_"_1"_1781 1801 1821 18ql 1861 1881 1901 ,-_
CRLENDRR YERR P_PROPOSAL I
tJ
IIRY 7;= ESTFOR20 CCSD NH 31 RUG 93 c_C)
DO
JSC - 26098
REFERENCES
1. DESIGN MASS PROPERTIES, Guidelines and Formats for Aerospace Vehicles, JSC-
23303, by Willie Heineman, Jr., NASA, Lyndon B. Johnson Space Center, Advanced
Programs Office, Systems Definition Branch, Houston, Texas, March 1989.
2. NASA TECHNICAL NOTE, FUNDAMENTAL TECHNIQUES OF WEIGHT
ESTIMATING AND FORECASTING FOR ADVANCED MANNED SPACECRAFT AND
SPACE STATIONS, NASA TN D-6349, by Willie Heineman, Jr., NASA, Manned
Spacecraft Center, Houston Texas, May 1971.
3. Military Specification, MASS PROPERTIES CONTROL REQUIREMENTS FOR MISSILE
AND SPACE VEHICLES, MIL-M-38310BCUSAF), Amendment 2, January 15, 1976.
4. GUIDELINES FOR MASS PROPERTIES CONTROL ON INTERNATIONAL SPACE AND
MISSILE SYSTEMS, issued by INTERNATIONAL SOCIETY OF ALLIED WEIGHT
ENGINEERS, INC., Recommended Practice Number 2, April 1, 1985.
33
JSC - 26098
APPENDICES
Appendix A - Estimating and Forecasting Examples
Appendix B - Definitions and Guidelines
Appendix C - Data Factors and Plots
Appendix D - Data Base and Data Points
JSC - 26098
APPENDIX A
ESTIMATING and FORECASTING EXAMPLES
Data Item Page
Example 1 - Manned, Non-winged,ReentryVehicle ................................ A-1
Example 2 - PropulsionVehicles ....................................................... A-2
Example 3 - Manned, Winged, Cargo Orbiter ......................................... A-3
Example 4 - Manned,Pressurized,Space Modules .................................. A-6
EXIPIII PLEMANNED, NON-WINGED, REENTRY VEHICLE
ESTIHRTIHC; FGECASTIH;REFERENCE FIGURE 10
REFERENCE FIGURE 1 I
OE$1GN.-EHVELOPE VOLUrIE 1@, _._.._,_ I DATA PO ! NTS :lB. hERCURY REENTRY 1100 4F. SKYLRB 14ORKSHOP
....... -e----t---_-- -_---_---i--t-_-t_, 2. r-ErtlNl SPACECRAFTV,4 e • eel} CU FT _.t_1-_' 4. SKYLRB SPACECRAFT
.........__..'_."-'P"':'" _'"_"" '_ 38. APOLLO C0MrIRNO 1100 eft. SHUTTLE ORBITERI _.-;'.'_,'. t i i_. 3E. APOLLO LUNAR MOO(R) (PHASE C/O ONLY)
100,000, __ = I | : ill ; = I : I._..,,IF =l.-: : , :.P. 3. APOLLO SPACECRAFT
__ I I * ,' ' • I I I|I _ I " : ''_I': 68 ..........................................................._-T-_4_ 4 F_.i.,.-ir.-H !!I!
-I_o ". io.o_ __E_l_ __ _ MASS 38.............. 'I--t. -i-i- ,._ o----iw-- :-t--_ --1--Pi-M" .... _ L_ i,liamlye_
' ' ' ' ''r;' -" ' I : iI __,e'---I ¢ _='_M_**_=*_,_ GROWTH 18
_, =¢*'i. "_" ..... II . Dm/,_ =,,._ 3E
:.........=:,"a_...-:_ ::==:1_" _"'_T=T,T_,:c,__'--_---::_-::::3:::._::--a.- i • . :i._::::=...-..-='-.-.'}.--_..-I--" "_ • tOA3_:'_ "l'_ GR..........i'"""+"l ..... u-.,., ;w._# "_ _. "H"i' ã�#�K�(PERCENT )
I ' i mill l" I . _,_/ , : : I I : :l.........._-----_---T-I_=_.'.-_""-..':.:;.... _..i._,.i.i.I___ll__ ; _ = I-#-"-'='_J "_ i I ! HilII
I I i i i i loo ....... CONCEPT OPERATIONe lit sl.i _oo 'l.ooo to.oco 'l_.o,_
I i
GIVEN: =,,,=,-_,,_.,,<,=,..v,o,'l GIVEN:DESIGN-ENVELOPE VOLUME, Vde = 898 CU FT BASED ON CONCEPT GIVEN THE 12542 LB ESTIMATE IH CONCEPTUAL ORDESIGN DRAWING. THIS VOLUME DOES HOT INCLUDE TPS. PREL]MIHARY DESIGN.
FINn: FIND:FIND THE ESTIMATED GROSS MASS, M OF THE REENTRY VEHICLE. FIND THE MASS GROWTH ALLOWANCE VALUE TO
MG : 67.58(880) e'?s; 18868 HO_ INCL TPS PER CURVE A. APPLY TO THE VEHICLE PROGRAM.FIND THE ESTIMATED BODY STRUCTURE MASS, M6 HOT INCL TPS. NOTE THAT THE ESTIMATED VALUES ARE AVERAGE
M6 = 18.42(888) e'e3= _676 LB NOT INCL TPS PER CURVE B RHD THEREFORE, RN RVRERRGE rlRSS GROWTHFIND THE REMAINING SYSTEMS MASS, 11 HOT INCL TPS. HOULO BE REASONABLE.
Ils_ = CURVE R - CURVE B = 10868 - 2676 = 8192 LB.s A MASS GROWTH ALLOWANCE VALUE OF 25 PERCENT
FIND THE ESTIMATED BODY TPS MASS, M tpS IS CHOSEN SINCE MERCURY AND GEMIHI ARE26.54(808) e'Er= 1674 LB. FAIRLY GOOD EXAMPLES OF THIS TYPE OF
M_ps VEHICLE.THE TOTAL ESTIMRTEO GROSS MASS OF THE VEHICLE
IS 26?6 + 81S2 + 16?4 : 12542 LB. THEREFORE, RH OPERATIONAL VEHICLE MASS OF
APPLY THIS ESTIMATE TO R PROGRRMITIC PROJECTION 1.25(12542) : 15679 LB WOULD BE PROJECTED.
BY USING THE FORECASTING TECHNIQUE ON THE RIGHT.EFl111× CCSD WH G MRY 93
_n nl"_n nr_,n E
PROPULSION VEHICLES
ESTXHflTXNG F0ECRSTIHGINCHES REFERENCEFIGURE 3 REFERENCEFIGURE 101.e
.-- .....-, lcL, I IORTnPOINTS:d, i ;_. GEH[NZ SPACECRAFT q. SKYLRB SPACECRAFT
3R. APOLLO COrlrtRND nOD ER. SHUTTLE ORBITER
__ I ,. RPOLLOSFRCEORRF,MASS
I HYO e.O -- =%. _ m_ =,,. " 60 .........................................................
! np/111¢ I_. ?Ira It', e_P Jq'IEt, I_lt |N I_.|IlXl _ |¢T q| )=o PCF eta[ O[ks ....
( .LIOI x ! e.1 Pc..w_.e=.L)) I-- R n,/ns.*, qe H.i..L I $_Imsimo*Ici-- O #.s.¢.L GROIJTH
*., F- _.. t t k ,lil._. !' ._ I t) l)il_ i Re SR;_'3_:I" I se I* 10o m I coo re*l* eee (PERCENT)'
i_ Itll * GRO$| IIRS$ OF STI_II: OR W[H|CI*I[, ¥HOU$ O_ POUNDIIt_ CONCEPT OPERATION
GIVEN: GIVEN:R CONCEPTUAL DESIGN OF R PROPULSION STAGE IS SIZED BRSEO GIVEN THE DRY MASS OR THE BURN-OUT rlRSS OF
OH RH ASSUMED MASS RATIO OF 9.92 FOR LIQ OXY/LIQ HYD THE PROPULSION STAGE IN PRELIMINARY ORRT R MIXTURE RATIO OF 5 TO 1. THE TOTAL USABLE MAIN CONCEPTUAL DESIGN.IMPULSE PROPELLANT IS CALCULATED TO BE $60000 POUNDS BASED
ON THE DIMENSIONS ABOVE. THE GROSS MASS IS CALCULATED TO FIND=BE 1021000 POUNDS BASED ON R MASS RATIO OF e.s; _. FIND THE MASS GROWTH RLLONRHCE VALUE TO
FIND: APPLY TO THE P_nel_Rr_.THE DRY MASS Lii.< _OkN-UU_ i=rib, S DOES NOT GROW
FIND THE ESTIMATED MASS RATIO BASED OH THE GROSS MASS THAT RS MUCH RS MANNED SPACECRAFT AND SPACE
IS OBTAINED FROM THE ASSUMED MASS RATIO ABOVE. STATIONS. NOR DO THEY GROW RS MUCH AS MOST
RT R MIXTURE RATIO OF 5 TO 1, R BULK DEHSITY OF IS._S IS UHMRNNED SPACECRAFT. THESE ALL GROgOBTAINED FOR LIO OXY/L]O HYD PROPELLANT. THIS CORRESPONDS ABOUT _'5 PERCENT ON THE AVERAGE.TO CURVE B OF THE PLOT ABOVE WHICH YIELDS R MASS RATIO OF
APPROXIMATELY _.91 RT APPROXIMATELY 10_1000 POUNDS. R MASS GROWTH RLLOWRHCE OF 15 PERCENT IS
THEREFORE, THIS SUGGESTS THAT THE ORIGINALLY ASSUMED MASS CHOSEN BASED ON ]'YPICRL V_:_,LUE3 FOR _TRGES.RATIO OF 0.9i- _ IS TOO LARGE FOR THE SIZE STAGE SHOWH.
RT THIS POINT, IF R ;'IRSS RRTIO OF 0.92 IS STILL DESIRED, '--,
THE STAGE GROSS MASS MUST BE INCREASED BY RESIZING RS
SEEN FROM CURVE B OF FIGURE 3 • EXAMP2X CCSD NH 13 NOV 92 c_
EXA! " 'LE 3MANNED. WINGED, CARGO ORBITER
ESTIItRTIHG FORECASTING
1_ :--_----t_-Pm---_-_-m_t_r_ia..;.; ;;_a ............. DRTR POINTS:; ; ;;;_;;: ;..;. ;,;;;.T.;;.;,_;,;.';;;:: .... _ "::::-:,,_,,,, IS. ,ERCURY REENTRY NO0 qF. SKYLAe ,ORKSNOP
• _ltR tOlNlll d I tltll I 1 I I tltlll* J*11J_r_l _. GrhlHl SPRCECRRFT q. gKYLRB SPACECRAFT
._ m.,_mm.m,m_l I lllll ] I IIIJh'l j_ 3S, RPOLLO COflhRN rl hOD OR. SHUTTLE ORBITER
IL mIml _mm L__ 3E. APOLLO LUNAR MOO(A) (PHASE CIO ONLY)Iii. illlllll _ IlIClrIlll
w. m _=mmms 3. RPOLLO SPRCECRAFT
S.T_.S !!!!!!!! ! i L_::---A T-_!iiiii iiiiii_I I I IIIII I _'; I¢_;1/. I I l_'ltfll I I II! TM ...........................................................
I'IRSS ! I III' _I,*" I .LIJ.I'I Jill I I p'l'immm, n ;-m,.1*_,rlll SO I,,I.F
R$llFT_IFII/1"_/I I IIIII "FTT3"IIIII I It1111 ,ASS 3B
"-- IIIIIIII I IIIIIIII IIIIIII -OF I i ................................
a0Tll: H_v I II roll IP _ so mine. I B".'_ :_s: 3E
--- Rlmmm i1_¢1¢m_, mlmw. I=1= cm-I_nsv = • _.l*ll4.)°'l_ 98 _'o
--- II UIN_ I_¢lca_vo _lkOll_ _(H_NII I. IIq*ll¢_ )o.le _R
• *ii,,J i , ,I,,,,I . ,,I,,,,I , , ,1i_ (_III Illl) III I ill II III IIIL_ osstc..-_.v_Lo_[_*i_, %. (=l I_) CONCEPT OPERRT ION
GIVEN: GIVEN:BODY DIRMETER, Ob• 8 FT; BODY LENGTH, L== He FT: NO MRIN ENGINES. GIVEN THE 35 880 LB ESTIIIRTE IN CONCEPTURL
OR PRELIMINRRY DESIGN.
NUMBER OF CREI, I RND PRSSENGERS, D_R_I : 8.NUMBER OF DRYS DESIGN MISSION TION, N_= 2. FIND:RSSUME LRNDING MRSS, Mldg: 50000 LB. RSSUME Mldg/S _ : 80 PSF OR FIND THE MRSS GROWTH RLLOURNCE VRLUE TO
OR RPPROX THE VRLUE OF SHUTTLE ORBITER. S_ IS THE THEORETICAL RPPLY TO THE VEHICLE PROGRRrl.
PLRNFORM RRER OF THE WING. NOTE THRT THE ESTIMRTED VRLUES RRE RVERRGE
FIND: RND THEREFORE, RNO RVERRGE MASS GROWTH
SIZE WING RND TRIL; MRSS OF STRUCTURE, THERMRL PROTECTION SYSTEM, RLLOURNCEWOULDBE RERSONRBLE.RND REMRIHING SYSTEMS. (SEE OERIVRT[ON ON THE NEXT PRGE. ) RS IN EXRHPLE I, THE ALLOWANCE FOR R IIRNNED
THE REMRINIHG SYSTEMS, Msus CRH BE DERIVED FROM FIGURE 5 RBOVE VEHCILE SHOULD BE 25 PERCENT. THEREFORE,WHEN THE WETTED RRER IS KNOWN RS DERIVED ON THE NEXT PRGE. RN OPERRTIONRL VEHICLE IIRSS OF 1._5(35_000)
OR FROM FIGURE 5 , CURVE C = _09.¢t9(_13B )e._{ = 16_ 0½0 LB. = ¢t3/750 LB WOULD BE PROJECTED.
NOTE: THE 50 eee =_ is RLSO THE INERT MASS OR FUNCTIONRL NOTE: THERE IIRY BE CRSES OF VEHICLE
CODES 1. THROUGH11. (OR RSSUMEDRS RPPROXIMRTELY TRUE. ). DESIGNS WHERE DESIGN MRTURITY HRS DEVELOPED
RLSO IN THIS EXRMPLE, THE 58 008 Ib IS THE GROSS rIRSS SIHCE THE IN CONCEPTURL RNO PRELIIIlNRRY DESIGN TO
IS/e_e LB INCLUDES THE SYSTEMS THRT COMPRISE IT. THE EXTENT THRT R SMRLLER RLLOWRNCE WOULDRERSONRBLE (BUT NEVER LESS THRN 15 PERCENT_
PER;ROtX CCSD UH 27 RUG 93
Do
EX_NPLE 8 ( CONT [NUEO )MANNED, WINGED, CARGO ORBITER
i
ESTIH RTING
1. BODY WETTED RRER, Rb = e. S5(l"fDL) + (T10_½) = 1,828D 8 FT_'_ SO FT, WHERE 8.85 RCCOUHTS FOR THE NRRROWING OF THE BODY
¢
(96 IN)
8RSEO ON RN RVERRCE D OF 5.H FT.
-'- _ -- 2. ASSUME LANDING MRSS, Mid= = 58/808 LB.
3. ASSUME MIdI/S _ = 8e PSF OR RPPROXIMRTELY THE VALUE OFSHUTTLE ORBITER. S, IS THE THEORETICAL PLRHFORM RRER OF
THE WING. THEREFORE, Sw IS 58_eBB/gg = 625 gO FT.
½. WING WETTED RRER, R N = 2(I.B?S N- B.S2LO) = 9½t SO FT.
INOTE: WHERE 1.87 RCCOUHTS FOR THE WING CURVRTURE AND B.S_L'.1\ I / ,ccooHTSFo, .VER OEC.O,D.ENGTHTHEWINOBODYIS OEF1NED BY KLhN. I
I _ INTERSECTION. THIS AVERAGE VALUE MAY CHANGE .
ill Ce ]']'1F" 5. ASSUME TAIL AND CRNRRO WETTED RRER, R t = 8. 18 R_ =_k
-- U__ VEHICLE IGSSO FT.
_ "'"L;7,_ ........ p= s. THEREFORE, TOTAL _JETTED AREA, Awe t ;" le_8 + 941 + 169 = 2138 SO FT.
/ M tp5 = 6.78R_tt = 1½½96 LB. FOR THE SHUTTLE ORBITER,
M s + Mtp $ • 7.53 LB PER SO FT. THIS VALUE IS REDUCEDBY 1(5 PERCENT TO REFLECT RN IMPROVED TECHNOLOGY.
_-"M 8. LRNDING GEAR MASS, MI9 = 8.84(LRNDING MRSS, Mldg) =CtN _ 2tB88 LB. e.SS
S. THE REMRINING SYSTEMS, Msy$ = 288.49R.e t = IS_B40 LB.
10. THEREFORE, TOTAL DRY MASS, M D = l.t4ss +
2seeo + 16, B_t0 = 3_,"_'_ ".!
11. MRSS REMRINING FOR CREW, PASSENGERS, PRYLORD, UNUSABLE
FLUIDS, GASES, RNO gO ON, M(pu = 5B, BB8 - 32_536 -",17/½S_ LB.
SEE THE NEXT PAGE TO ESTIMATE CREW AND PASSENGER
L I SYSTEMS.L = 48 FT ;,
(480 IN)
bo(3
PERCR02X CCSO WH 23 NOV 92
Do
EXAHPLE 3 ( CONTINUED >MANNED, WINGED, CARGO ORBITER
ESTIHRTING12. FROM FIGURE 6, THE FIXED MASS FOR CREW AND
PASSENGERS IS 310(Nee) : 31e(e) : 2,48e LB.ALSO, FROM FIGURE 1.5, THE VARRIBLE MASS
= 8.20 (NcpN d ) 1.18 : 8.20((8)(2)) 1.18 :: 214 LB.
REFERENCE FIGURE 6 is. THEREFORE, REMAINING FOR PAYLOAD, UNUSABLE
REFERENCE:rSTFOIt3! ESTIMATING CURVES FLUIDS, GASES, AND SO ON, IS 17,464 - 214.............."+""+' ��¸�2SYSTEM ...._............................................... ._.-+.+...+.+. .....-.{....,_.CREu RNO PASSENGERS _:'- .... Ð�2�[�-I ?+,258 LB.
• • :li:: • . - .,. , ILI'" .,: : • =;'- : : :,:::....... -.'..... .......,............"._._.................._........u .......................... 14. THE IHITIRLLY RSSUMEO So, Bee LB FOR THE LANDING........ ";'"+"_'" "+'!'" ""'+"_""3++"'++"; "+._+H .......... !''"!'"+, " +-'.+,"
I1. MKICUI¥11rlHTIYIIOnULi + ++l++h + + ++ +!+! i ++ +++ MASS IS ALSO THE INERT MASS, M I OR APPROXIMATELY....... I.........,+..............................................+--+-++++-+=,. ,po,.,.oco,.,.o .o_.t I + "'0,|" + ++ I++i THE 17, 250 LB ABOVE INCLUDES THE UNUSABLE FLUIDS...=t.,,,o,.,.O-UNnt,oou,..+ i+ niiii i ,'!l!iii AND GRSES WHICH IS A RELATIVELY SMALL VALUE.
to Bee :..:: ,.,. s_vLn otottRc uow_s.opI::::_::::_::I::_:+"::::::::::::::::::::::::::::::::::::::::::::::::::::::::::I:::::: ,. ,,,,,, o,,,,, c,,,,. :::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::FOR EXAMPLE, IF 17, Dee LB OF USABLE PROPELLANT
......4............ _+_........+-.++...+.++4._..........._..-+...+.-|.++. �..........+*++.........+..+..+...+.|.+ '�sREOUIRED, RND IF R LRRGE VALUE OF 57. WAS
.......+.....I+....... ,,+ .......+._+...,...,-.......... ,.........++.._..L.,.,.,.......................,..L.++...--+..........L...+....+...4.++.
]' ++ = + + +++ / + + + +H + + - ALLOWED FOR UNUSABLE PROPELLANT. THIS gOULD BEMASS .....4.....I....L.+4.+.".........J-..._...++.+.i.. ,+............+..+..I+H-...........,I......+L.+..I.++'.++.+.+.+.............L..L .-":.J+:".t• ' '" I 'I+ .... e ' ! ++++ ONLY 95{) LB FOR UNUSABLE PROPELLANT. THEREFORE,
1 ODD _....._.,i ! .!+! _ '¢o+._. _+_._ ........ ! ' :..!:i_ _ _ * ; ;:;: r .. NERRLY ALL OF THE 17.,_50 LB IS RLLOURNCE FOR
::::::::!::::+-':::i:::t:Z'_'.:::..:.z::_::::_.__:._..::::::::::_NOTE= PRYLORD OR CRRGO.
POUNDS ........!.-._...L .+._i ....."_.,..';.._+.'+.i.!!..........i FIXEO tlRSS=........+i'-+"'"L+.+.+.+._.++.+.f-;o-.+-+-+++li+_,........._ "":""',,,,",,"F,.E,""o, ,',,E.,.,'. ,'....=,+,,. NOTE:........,........._..+.+...,,.+.,,,. ++..+.++
i if+ !+ .(_ ++q+' !,.(. )|N|'OUNOS. RT THIS POINT, R DECISION IS NEEDED TO DETERMINElee ................. ,'. ..... VARIABLE _RSS: THE TYPE AND DENSITY RANGE OF THE PAYLOAD OR:'_.._I................":-"+. ���K�:::::::::z........ i..-.,+....="............ ": - .-:-.
...................._:_::I Ü�Å�U�=S._SS_EL_t[OtO CR¢. _XO CARGO TO BE CARRIED. PAYLOADS AND PAYLOAD BRY........4-.-.i....-'.... ::::::::: :: I"fTT:: h• pv
................!..;_.';.-.4.-i.';-._'L_+..-.....L..-I-...L.+..,..+..........L...+..._4"_'+..........._ P,SS[NO'=mltNnt V,mt+$ SIZING DRTR HAS BEEN PLOTTED IN A GENERALIZED/; : -- , 8.20 (XcpNd) 1.18! : : itS! + { ! {
......._._8...._.]..,.+,,_1.................._,I.....--._ MRNNER SHOWN IN FIGURE C-'-t, THESE DATR SHOULD/ O. i/{ i! _.._:!1 i {liHi_ i _ tliiii_ i +il+H PROVIDE A REASONABLE ESTIMATE FOR CONCEPTUAL
/ = ill_i,I i =illi=il i ,,t:::_l ; ;, ;1_ii_1 ; ; ;I;;; DESIGNS. IN ANY EVENT. RESIZING THE VECHICLEle tee I Bee te Bee
(NUMBER OF CREN AND PASSENGERS, Hop) (NUhBER OF DAYS, N d ) IS R MOST PROBRBLE SITIATION. AND MOST LIKELY.THE VEHICLE SHOULD BE RESIZED LARGER FOR THE
5e_eee LB LANDING MASS OR THE ASSUMED LANDINGMASS REDUCED FOR THE SIZE VEHICLE SHOUN.
PERCAB3X CCSD UH 3 DEC 93
EXAHPLEMANNED, PRESSURIZED. SPACE MODULES
ESTtHRTING FORECRSTINGREFERENCE FIGURE 10
HETHOD 1 o.T_POINTS:I_FI_I IO. IIERCURY REENTRY 110n HFo $KYLRB MORKSHOP
I "'_ I I ' I I _. GEItIN| SPBCECRAFT q. SKYLRB SPRCECRRFT3B. APOLLO COflMRNOMOO SHUTTLE ORBITER
l"'_'--_"_1 • vdlmlmWmmamli.mir-lPsl_.-_:_,_ 3E. RPOLLO LUNAR 1t00(9) (PHASE C/O ONLY)
.......................... _1 "_.,_ ,0._____" .__;_2_____._-t-___-=- --_---_---_---.-_-_! ,_ssE'" I_i_....................................................................................................i / /__i________i'_ _ __''_,'I "I" • 3EI IL liC_:,.;] ¢. _'_. GROWTHI; h __I.__] ..'..P-_..P..-I ._.e _ 2, 3
. ., . ::':" ... e_. _o_wooW 6R
_/ -e-,_,.._w.."_!1oe i i J i[!! CONCEPT OPERRTIOHIXI seo _.oo_ _o.ooo too.o_
I*------'-- e_:v ©',,Lm.,'," U_'.- _ _V,_-,..V. #)
IlVlNl GIVEN:HABITATION MODULE WITH A PRESSURIZED VOLUME OF 4414 CU FT, R CREW GIVEN THE 39800 LB ESTIhRTE IN CONCEPTUAL
OF FOUR WITH R STRYTIME OF 45 DRYS. OR PRELIMINRRY DESIGN.
FIND: FIND:FIND THE ESTIMATED MASS OF THE MODULE WITHOUT PROTECTIOH SYSTEMS FIND THE MRSS GROWTH RLLOWRNCE VALUE TO
RND PROPELLANT. RPPLY TO THE VEHICLE PROGRRM.
IN THIS CRSE, R VALUE OF _0 PERCENT IS
REFERENCE FIGURE 1 : THE PRESSURIZED VOLUME MRY BE CONSIDERED CHOSEH. ALTHOUGH MRNNED, REFLECTING
RPPROXIMRTELY THE SRMERS THE DESIGN-ENVELOPE VOLUME WHICH IS HIGHER GROWTH RRTES, IT IS HOT R RETURH
ESPECIRLLY TRUE FOR LARGE MODULES SUCH RS THE ONE SHOWN. VEHICLE, IN WHICH CASE, R 25 PERCENTe.T§
OR M G2 : 67.58(v d) : 39800 LB. NOTE THRT ONLY VOLUME IS USED VRLUE WOULD BE CHOSEH.
TO MRKE THE ESTIMRTE.I
ES] :OR5S CCSD WH 5 FEB 93
EXAHPLE 4 < CONT I NUED )MRNNEB, PRESSURIZED, SPRCE MODULES
..........................-..........._................................HETHOD :_.......i..-_-_._ -_............_.... , i'' '
MflSS - i : _ :/-7_ I /1"lr..... _ ......... t._ i "-. / I h /_ .i
: i i i L l : _ ._. i . FIi_ i141THOUT ....................... +...........! ...........................i..........._ ........_'--'_"" ....................."_i-_'_._ .......... __': ....................i............
- -i iFIND _ i i _ J_I { .--'_"I _-_ _._ NUMBER OF CREW
,_ PROPEL _ i i _._.._.:...._--" i -- "=-i i RND PASSENGERS. i-_ _ooeo ---_ ............................................._ .....................................................................................i......................................: I _ _ _ _ 3 _'- _ . : i. .o. 3s",'4- I _ _SE i'"_ i _ IMI__- 33eSl(H H.V7.._................._............!o,._.5...2.A.....:............,......................................_.. _ - • \ ,, . ,, / IN_OONOS.
Pou,os - IB...1..4.-"i_, _,
I 000 10 000 100 000 1 000 000 10 000 000
_cp_JV pr or (NO. OF CREW AND PRSS.)(NO. OF DRYS)(VOLUME PRESS., CU FT)QIVEN: FIND:
FIND THE ESTIMRTED MRSS OF THE MODULE WITHOUT
HRBITRTION MODULE WITH R PRESSURIZED VOLUME OF PROTECTION SYSTEMS RNO PROPELLRNT.
4414 CU FT, R CREW OF FOUR WITH R STRYTIME OF 45 WHEN THE SUBSTITUTIONS RRE MRDE IN THE FORMULR RBOVE,
DRYS. THIS IS THE SRME MODULE RND CONDITIONS THE MRSS IS CRLCULRTED TO BE 4245B LB. THIS ESTIMRTE
RS SHOWN IN METHOD 1. IS LRRGER THRN THE VRLUE FROM METHOD I BUT NOT
UNRERSONRBLY SO.ESTFOR5? CCSD NH 16 JUL 93
o
[__PL_ _ ( CONTTNUED )MANNED, PRESSURIZED, SPliCE MODULES
i
ESTIH RTXH6HP"THOD 3
ENPENOABLE8 FOR CREM RH O PASSENGERS
HG2 = 3tO)(Ncp ) �(ie?.es4)(vp,)+ 8.20 )(N c a) t24e + 3use + 8760 = 39600 LB
I- I , .s.121e I _, .0 I
r'----1 = iO?*Q6_{v r J • ." I I H IO INtO
iii!! .0 !.iillL i:::'I ----.....l'_^ • 0 =! eA. u,,,=.z _,,r _ - ,,,,I
F "" I'---"' I$I_ W. m'lt,AI llllellm, l_llxlliP
jssfO _ llml1'Lll SailS:|¢_
I I I Illlll I I I I*" * , *1''''1 a * 'l*"dI IERT tOO ! 008 lO SO0 100 088
I PRESS SUIT Vpp , VOLUIIE PRE88URIZEO, ¢U FT , , ,h,*,I , , oh,,,I L , ,h,,,I , , ,h,,,I
I Itv_ 8UtT N,,Jid ,r to Io8 i eel le IIN(NUMO[It OF CRI[II RNO PRSS[HG[RSXNUMBI[R Of' OAY|)
GIVEN:HABITATION MODULE WITH R PRESSURIZED VOLUME OF IS SOMEWHAT LOWER IN VRLUE THAN THOSE OBTAINED BY½½14 CU FT, R CREW OF FOUR WITH R STRYTIME OF 45 METHODS t AND 2 BUT STILL WELL WITHIN AN EXPECTEDDAYS. THIS IS THE SAME MODULE AND CONDITIONS RANGE FOR CONCEPTUAL DESIGN WITH FEW EARLY KNOWNRS SHOWN IN METHODS 1 AND 2. DESIGN PARAMETERS.
FIND:FIND THE ESTIMATED MASS OF THE MODULE WITHOUTPROTECTIOH SYSTEMS RND PROPELLRHT°WHEN THE SUBSTITUTIONS ARE MADE IN THE FORMULR ABOVE,THE MASS IS CALCULATED TO BE 39600 LB. THIS ESTIMATE
ESTFOR58 CCSD WH 27 RPR 93 2o
EXAMPLEN <CONTINUED)MANNED, PRESSURIZED, SPACE MODULES
VGLUHE CONSIDERATIONSVOLUME PRESSURIZED PE* NUMBER OF CREW
le eee ..o e.ssE.eERs
C "-" :_:: =================================================================================V p r p I|. r,(*¢ueY ite[#nev noouL[ _ ' ' ' : :: 1 : : : : ::
Zll GEIIINI it[ENTitY MODULE I !
..... _i, _)OI.LOLtmmtnOOUL[I_scr)rrl_...'..:.:t ........ :.... :...':...| ':..-:?'-_'._,.-,-"': ":- | t"r.-':.-[ ........VOLUME .. _'OLLOCOm_.a.OO_E !!: ! ! ! !!!! ; : _ ::::.....:,"_::=_'.o, l."d........,:d:.'_'FT_'_._._..-4........PRESSUR [ ZEDIIll 8HUlrTLE ORII|TER CABIN : : : : : : : ,,_: :: : / : ' : : : :
...... .. s,u_T_,o.,,,,,_.,. I_. 6��.:....._...!.J.._._._I.....,._...._...._...I._r+J ........_ _ _ ! : _ .I -: : :.._ :::J
_ i i _ ii_ i i i i_!!/./_ /,.!i j.<: iHiiPER I Bee .......:-...-.--.,.-t-.-.--:-.,........*.-.-_.--_--':,_!+_:-_:-......_..-.+-_+.:,+4.__-;---._.-_.-.,:..-t._:AP...-_.-
............... :..',..._.: .......... :....... ,_,.' L:_..<:.: ........ :..,.,:_...:..z.:._._,; [..../'._---M.;-- '-._--_.-_-_.........NUMBER ....... _....-:...:.., ,4._.; .......... ;...._',., r.:.-;.: ....... ,_'_'.-I...'...;..;."J); .... _-_-.M -:.-.._ .I-........: : : : : _ ._: " I" I • _:1': U ! : • : :::I
........"..-.'....:...t,.','-:_....._---.--.--,_-_:.........-'_'4+--tl.:--,t:......
oF .......i::i ._,.;.iI_ .......e._;2,.._ii_._-...i+i.i_;:_:_*}.".._i_L"__(!_..... CURVER> CREIJ ........_-.,4" :..; _>r" ."_1.i@../..i.;; ....,.4_:..-"sE'_:::,:_ ........:1"i_;i[:,,:::::.......... v_,./ N,,, c..,,_l_,.,,,' RND GO_" : LgP _,;,4: _ :i1_ _ : : ::::: __!": _.._.:: :_- : :;:1: o: ; "_;;_:lee
6.3_G(Vpp)"'"_" ""';""; ""i_.. .... - 3B "-';": ............... :""
>
: : : : : CURVE B IS TUO TIHES CURVE R VALUE.: : : : :
! _ : : : CURVE C IS FOUR TIMES CURVE R VRLUE.' ' ' 1 - " " T ....
lee 1 088 10 080 100 88e
V :,r. , VOLUME PRESSURIZED, CU FT
ONE OF THE MAJOR CONSIOERRTIONS IN THE DESIGN OF THE RESULTING CURVE A FITS THE REMRINIHG FOUR DATAANY VEHICLE IS THE VOLUME AND AREA RLLOIJRNCES FOR POINTS IJELL. ALSO, THE NUMBER OF PERSONS PROVIDESALL OF THE SYSTEtlS AND THE CREM RNO PASSENGERS. R GO00 FIT ON THE BASIS OF 1B (1), 3B (3), ANDTHE FIGURE ABOVE SHONS R PLOT OF VOLUME PRESSURIZED 6R (7), REPRESENTING MERCURY REENTRY MODULE, APOLLOPER PERSON VERSUS THE TOTAL PRESSURIZED VOLUME OF COMIIRNO MODULE, RNO SHUTTLE ORBITER CABIN, RESPECT-THE VEHICLE BASED ON R NUI1BER OF HRRDURRE DATA IVELY. CURVE B IS TUO TIMES CURVE R VBLUES FORPOINTS. THE RESULT IS CURVE R NHEN CERTAIN ADJUST- REFERENCE AND CURVE C IS FOUR TIMES CURVE R VALUES.I1EHTS ARE MADE. DRTR POINT _fl IS NOT USED BECAUSE NOTE THAT DRTR POINT 4F UITH R CREIJ OF THREE RESULTSTHE PRESSURIZED VOLUME PER PERSON IS TOO SIIRLL IJHEN IN OVER 3000 CU FT PER PERSON AT SLIGHTLY ABOVECOMPARED TO THE REST. LIKEUISE, ORTR POINT qF IS CURVE C. AT CURVE R, THE NUMBER OF CREU IS I4 UITH
G_NOT USED BECAUSE THE VOLUrIE PRESSURIZED PER PERSON BOO+ CU FT PER PERSON COMPARED TO 377 FOR SR. (-_
IS TOO LRRGE. EF42X UH 4 dUN 93
Do
( CONT I NUED )MRNNED, PRESSURIZED, SPRCE MODULES
i iii i
VSLUNE CONSIDERATIONS
)liT, POINT @ @ @ VOLU,E PRESSURIZED PER NUMBER_oOF__.._._CREN1600
(SEE PLOT) _ - ILI : : : : : : :/ ¢_ : .,_8- Irl J NUrlBkROF:CREW: : : : ..,,'_._ • _ J!t,,oo. . ..0 ,n.E.,:-_RS.7 : : : _'_:" : .....Z'"'Io
: i ' i i _ i i..-i i ! i• ._ 10"" : : : : _" : : : :
PRESSURIZED
.......•"........:.........: ........_ ..... _......_--_ ..... _ 12
RPOLLO SHUTTLE HRBITRTIOH80o
VEHICLE COMMRHD ORBITER MODULE .U..ER " _ _ "]_'" _:"_" ._-'--'"iMODULECABIN u, ....... .......i
eRE. =oo _l,,__ T--;
-..'. _...... ":.... '!"......... :-4 .... *.setPRESSUR VOLUME 36B 2840 4414 ensseNcER._00 /. _ (_=..=: /".._""I a.V. /,.......;.%.) E"_/(--'"'_'
,_> Vpr. (CU FT) E©u e'r""'_ /_,/'_'" i °_ i : |¢umee_, TWO TIMES THE VRLUE OF CURVE R. I
NUMBEROF CREW 3 7 4 _ooJ_.i ........."........i.......I==*.C=tour T.,ES_HEV,LUEOFCURVE,; IO_t: : : : I i i i i i i : :
aND PRSS, Nee ,,,i,,i,l,,,,i,,,,i,,,,I,,itl,,,,i,,,,i,,i,ii,,,i,,,,i,,,, |
Vpr/N •p 1_ 377 1I0_ _ _ s _ so taVpp , VOLUMEPRESSURIZED, THOUSOF CU FT
BRSEO ON THE PREVIOUS PLOT, R PRESSURIZED VOLUME PER THRT ONE CRN MOVE RROUND IN. BECOMES LRRGER PROVIDING
PERSON IS OBTRINED FROM CURVE R REPRESENTING IN R R BETTER LEVEL OF COMFORT. NO RTTEMPTS WERE MRDE TOGEHERRLIZED MRNNER THE VOLUME STRHDRRDS OF SPRCE DETERMINE "FREE" VOLUMES BECRUSE OF THE TIME IHVOLVEDMODULES TO DRTE. THIS PRESSURIZED VOLUME ENCLOSES RESERRCHIHG DOCUMENTRTION RS WELL RS STUDYING THE DRTR.
THE CREW RND PRSSENGERS RS WELL RS MRNY OF THE
SYSTEMS OF THE MODULE. THEREFORE IT SHOULD BE KEPT FIHRLLY. NOTE THRT DRTR POINT HM WITH R CREW OF FOUR.IN MIND THRT THE USE OF THE PLOTS RND CURVES SHOWN ENJOYS R VOLUME PER PERSON OF tlOO CU FT WHICH IS RBOVE
HERE HRVE CERTRIN LIIIITRIDHS RHD SOUND JUDGMENT IS CURVE C. PROCEEDING WITH THIS DESIGN IS OUESTIONRBLE.ESSENTIRL. OF COURSE, THIS IS TRUE OF RLL PLOTS RND IF THE MODULE IS MRINTRINEO RT ITS PRESENT SIZE OF
CURVES THRT PERTRIN TO CONCEPTURL DESIGNS PRRTICULRRLY. 441H CU FT, THE PLOT INDICRTES THRT R CREW OF EIGHT ISREOUIRED RT CURVE R. THIS MRY BE TOO SMRLL BRSED ON
NOTE THRT RS MODULES BECOME LRRGER, THE PRESSURIZED OTHER DESIGN CONSIDERRTIDNS. R COMPROMISE OF R CREWVOLUME PER PERSON BECOMES LRRGER RND THEREFORE IT IS DF SIX HERR CURVE B WRY BE THE WRY TO PRDCEED. 09RERSONRBLY RSSUMED THRT THE "FREE" VOLUME OR THE VOLUME (-_
ESTFOR61 CCSD UH 30 RUG 9_o_0
oo
JSC -26098
APPENDIX B
DEFINITIONS AND GUIDELINES
Data Item Page
Introduction ................................................................................ B- 1
Functional System Codes ................................................................ B-1
Functional Systems (table) ............................................................... B-6
JSC -26098
INTRODUCI'ION
Consistency is the most important consideration in the recording and reporting of mass
properties data. Consistency of definition and placement of the data makes it useful for
assessment of stand-alone designs or comparability between competing vehicle designs.
Consistency between designers and analysis will limit the confusion and possible misuse of the
data. Documentation of study results and presentations should all report the mass properties
data to the same format. Reporting the data in various formats allows for data scattering which
ultimately can lead to mass growth.
A vehicle mass recording and reporting format has been developed that can be used for
practically all types of vehicles. DESIGN MASS PROPERTIES, Guidelines and Formats for
Aerospace Vehicles, JSC-23303 defmes this format, along with the definitions that govern the
placement of the data. The definitions and guidelines from JSC-23303 follow for reference
purposes.
FUNCTIONAL SYSTEM CODES 1. THROUGH 13.
1. STRUCTURE
Wing, tail, body, fins, skins, primary, secondary, pressurized, unpressurized, fuel and
oxidizer tanks if integral with the body slructure, and so on.
Note: Reference 3 defines aerodynamic surfaces structure (wing, tail, and so on) as the
basic and secondary load-carrying members for all primary lifting and aerodynamic
conlrol surfaces, both fixed and movable, exclusive of the non-sta'uctural panels used for
induced environmental protection systems. Body structure is the basic and secondary
load-carrying members, exclusive of the non-su'uctoral panels used for induced
environmental protection systems.
2. PROTON
Heat, micro meteoroid, radiation, noise, and so on.
Note: Reference 3 defmes induced environmental protection as the devices which in
themselves, or in combination, protect the vehicle slructttre from the detrimental effects
of heat, noise, micro meteorites, and radiation.
B-1
JSC - 260983. PROPULSION
Main, maneuver, reaction control, tanks if not integral with the body structure, structural
supports, circuitry, and so on.
Note: Reference 3 defines main propulsive items that provide flight path thrust and
acceleration and include rocket engines, nuclear engines, propulsive devices, and related
equipment, such as fuel systems, oxidizer systems, and pressufiz_g systems.
Secondary propulsion systems, such as maneuver, reaction control, and attitude control,
are defined as control units, exclusive of navigation and guidance, which provide
relatively small amounts of thrust or force compared to the main propulsion system,
usually for purposes such as velocity control, attitude control, rendezvous, and docking.
4. POWER
Electrical source, hydraulic source, pneumatic source, conversion and distribution,
structural supports and so on.
Note: Reference 3 defines prime power source as systems used to generate power for
purposes other than propulsion, including the source of initial power. However, once
the power has been generated, any additional conversion equipment is listed under the
Power Conversion and Distribution group (that is, hydraulic, pneumatic, or electrical).
Power conversion and distribution is defined as the systems used to distribute eleclrical,
hydraulic, or pneumatic power. The source of initial power is included in the Prime
Power Source group.
5. CONTROL
Surface controls, thrust vector controls, structural supports, circuitry, and so on.
Note: Surface controls are normally associated with winged vehicles and are the
systems, generally exclusive of the integrated avionics, that move the control surfaces of
aerodynamic surfaces, such as elevons, rudders, speed brakes, body flaps, and so on.
This included actuators, plumbing, fluid within the systems, cockpit controls such as
rudder pedals, and so on. Thr_t vector controls are normally associated with booster
vehicles and are the systems, generally exclusive of the integrated avionics, that move
the main engines. This includes actuators, plumbing, fluid within the system, structural,
and so on.
B-2
JSC - 260986. AVIONICS
Guidance, navigation, communications, instrumentation, tracking, data processing,
structural supports, circuitry, and so on.
Note: Reference 3 defines guidance and navigation as a group divided into the following
major subgroups:
a. Guidance Source; receives a sensor signal.
b. Guidance Evaluation; evaluates signals, determines navigation requirements
and informs the output systems.
c. Output; activates the control systems.
Communications is defined as the equipment required for all means of communication
within, emanating from, and received by the missile or space vehicle. This includes
such items as transmitters, receivers, antennas, power amplifiers, television cameras,
and spares. Instrumentation is defined as measuring, signal conditioning, recording,
and programming systems for data sampling and recording, including the sensors,
circuiu'y, signal converters, and recording media from the measurement source to a point
of telemetryor permanentstorage.
(Note; The Shuttle Orbiteralso lists tracking and data processing under Avionics.)
7. ENVIRONMENT
Environmental control system, personnel provisions, crew station controls, panels,
pressurized volume, unpre_urized volume, structural supports, circuitry, and so on.
Note: Reference 3 defines environmental control as the system that controls internal
environmental conditions such as temperature, pressure, humidity, atmospheric
constituents, and odor for personnel and equipment. Personnel provisions are defined
as items within the crew cabin, such as accommodations, fixed life support equipment,
cargo handling, furnishings, and built-in emergency equipment. Crew station controls
and panels are defined as items consisting of crew station controls, pedestals, stands,
and display panels for all systems.
8. OTHER
Landing gear, parachute system, docking system, manipulator, structural supports,
circuitry, and so on.
Note: Reference 3 defines launch, recovery, and docking as the items that provide the
vehicle with the capability to be launched from or brought to rest with respect to a mass.
B-3
JSC - 260989. GROWTH
Percentage of DRY MASS, and so on.
Note: Reference 3 def'mes mass growth allowance as the mass allowance to account for
changes due to development and manufacturing problems, changes in design
requirements, and other in-scope causes that are not identifinble at the time. Also,
Reference 2 states, "The contractor shall develop and substantiate appropriate weight
growth allowances consistent with prior experience."
10. NON-CARGO
Unusable propellant, unusable service items (fluids, gases), reserve propellant,
personnel, structural supports, circuitry; and so on.
Note: Reference 3 defines unusable propellantas residual propellant and service items,
remaining in a item, which are not usable. Also, reserve propellant and service items are
the propellant and service items carried by a propulsion stage or module in excess of that
required to perform a mission with a nominal vehicle. Personnel is the crew required to
perform a particular mission, including the non fixed items required to support the crew
both inside and outside the spacecraft, such as personal gear, life support items, andcrew accessories.
11. CARGO
Payload, payload support equipment, structural supports, circuitry, and so on.
Note: Reference 3 defines cargo as items stored aboard the spacecraft that will be
required to perform certain functions during the mission. These items include scientifie
instruments and equipment to perform experiments, passengers, and associated
equipmenL
12. NON-PROPELLANT
Usable food, usable water, usable fluids, usable gases, structural supports, circuitry,
and so on.
B-4
JSC - 2609813. PROPELLANT
A. Usable pro_llant (furl thrust propellan0; main (delta v), maneuver (delta v), and soon.
Note: Reference 3 defines flail thrust propellant as propellant consumed during the
burning period from the specified value of thrust following ignition, or from lift-off
from the launch pad, to the specified value of thrust following the cutoff signal.
B. Unusable propellant and fluid losses
Note: Separate totals should be supplied for A and B, and if data for B are not available,
notes of estimates should be supplied for a, b, c, and d, either separately, or as a group.
Reference 3 defines unusable propellant and fluid losses as:
a. Inflight losses; propellant losses associated with the use of auxiliary propulsion
systems. These include losses for roll and attitude control, venting losses from
pressurization gases, and boil-off losses.
b. Thrust-decay propellant; propellant consumed from the specified value of thrusL
following the engine cutoff signal, to stage or module separation, or to zero value ofthrust.
c. Thrnst-bnildup propellant; propellant consumed from ignition to the specified value
of thrnsL or consumed prior to lift-off from the launch pad.
d. Pre-ignition losses; fluid losses associated with starting the primary propulsion
system of a stage or module which occur prior to the ignition signal.
B-5
FUNCTIONRL SYSTEMSMIL-M-98BleB < REF. 3 ) JSC-23383
, ,
1.0 RERODYNRMIC SURFRCES 1.0 STRUCTURE 1.0 STRUCTURE
2.0 BODY STRUCTURE 2.8 PROTECTION 1.o RERODYNRI'IICSURF2.0 BODY STRUCTURE
3.0 INDUCED ENVIR PROT 3.0 PROPULSION 2.0 PROTECTIONH.O LNCH RECOV AND DOCK q.B POWER 3.e INOUCED ENVZR PROT5.8 MRIN PROPULSION 5.8 CONTROL 3.0 PROPULSION
6.0 ORIENT CONTROL SEP ULL 6.0 RVIONICS S.O MRIN PROPULSION6.0 ORIENT CONTR SEP ULL
7.0 PRIME POWER SOURCE ?.0 ENVIRONMENT 4.0 POWER8.0 POWER CONV AND OISTR 8.0 OTHER ?.0 PRIME POWER SOURCE9.0 GUIORNCE RND HRV 9.0 GROWTH e.0 POWER CONV RND DISTR
18.8 INSTURMENTRT ION ORY MR_S 5.0 CONTROL
11.0 COMMUNICRT I ON 10.0 NON-CRRGO s.e RVIONICS12.0 ENV IRONMENTRL CONTR
|_0 CRRGO s.e GUIORNC£ RNO HRV13.0 RRMRMENT INERT MRSS 10.0 IHSTRUMENTRTION
11.0 COMMUNICRTIONIq,B PERSONNEL PROV 12.0 HON-PROPELLRNT ?.0 ENVIRONMENT15.0 CREW STR CONTR PRN 13.0 PROPELLRNT 12.o ENVIRONMENTRL CONTR
16.0 RRNGE SRFETY RNO RBORT GROSS MRS_W |_R. IJH|CH T GROWT H RLLOIJ 1%6 PERSONNEL PROVi 15.0 CREW STR CONTR PRN
o_ DRY MEIGHT o.e OTHER17.0 PERSONNEL _.0 LNCN RECOV RNO DOCK
18.0 CRRGO ts.s RRNGE SRFETY RNO RBORT
19.0 ORDNRNCE NOTE: 9.0 GROWTHISR. WEIGHT GROWTH RLLOW
20.0 BRLLRST THE JSC-23303 FUNCTIONFIL DRY MR8921.0 RESIO PROPELRND SERV SYSTEMS ARE R GROUPING i6.0 NON-CRRCO22.0 RESERV PROPEL RND SERV
INERT MEIGHT OF MIL-M-38310B FUNCTIONRL 19,17"00 ORONRNcEPERSONNEL
23.8 INFLICHT LOSSES SYSTEMS, 20.0 BRLLRST21.0 RESID PROPEL RND SERV
24.0 THRUST DECRY PROPEL 2E.0 RESERV PROPEL RNO SERV25.0 FULL THRUST PROPEL tI.e CRRO0
26.0 THRUST PROPEL BUILDUP 18.0 CRRGO
_?Te PRE-ZC_IT_O_ LOSSES INERT MRSSGROSSMEIGHT Ie.e NON-PROPELLRNTP3.0 INFLIGHT LOSSES
_?.6PRE-ICNITIONLOSSES13.0 PROPELLRNT
23.0, Eq.D, 2(;.0, RNO 27.0
I 25,8 FULL THRyST PROPELGROS8 11888 ,..,
FORMRTe2 CCSD IJH 1H DEC 98 _Jo
oc,
JSC -26098
APPENDIX CDATA FACTORS AND PLOTS
Data Item Page
Table C-1 - Mission Mass Parameters .................................................. C-1
Table C-2 - Design Data, Propulsion Vehicles ........................................ C-2
Table C-3 - Design Data, Saturn V/Apollo ll ......................................... C-4
Figure C-4 - Payload and Payload Bay Sizing ........................................ C-5
References - Propulsion Vehicles ....................................................... C°6
TABLE C-1
M SSXON PARAMETERSNORMALIZED DATA POINT VALUES
DATa POINT 1B 2R 3B 3E 6A 4F
MERCURY GEMINI RPOLLO APOLLO SHUTTLE SKYLRBVEHICLE REENTRY REENTRY COMMRND LUNAR ORBITER ORTITBL
MODULE MODULE MODULE MODULE CABIN WORKSHOP
2724 49H8 13856 10571 23H7H 78195_ROSS MASS, POUNDS, Mot
i _ESS PROTECTION SYSTEMS -488 -729 -3738 -364 -t282
i LEss PROPELLANT -55 -72 -209 -549H -IN65
i _ESS MAIN PROPULSION SYSTEM -469
i PLUS EXPENDABLES IN SERVICE MOD 316 221
i PLUS CREW 620 2170 SSOi ! (NOTE: R CONSTANT 910 LB PER
! i CREW MEMBER, SEAT AND MISCLi i IS USED TO SIMPLIFY RECORDING.)
I _ROSS MASS, POUNDS, MG2 2189 HH63 9398 4864 2564H 76378
i _ODY STRUCTURE, Mb 377 1074 1820 1026 6639 20311
i ISYSTEMS, Msu s (WITHOUT CREW) 1486 2H07 6313 3082 15791 43145
INERT MASS, M I (WITHOUT CREW) 1863 3481 8133 H108 22430 63H56_REN 310 620 930 620 2170 930
i iEXPENDRBLES aND CONSUMABLES 16 362 275 136 1044 11992
GROSS MASS, POUNDS, MG2 2189 4463 9338 4864 256H4 76378
NUMBER OF CREW, N 1 2 3 2 7 3 L
bOMBER c• . OF DBYS, N d 3 IN 1 1 •3 2 i0 28+56+56 oI_OLUME PRESSUR, CU FT, V 50 80 366 283 26H0 10500pr#i I N , CU FT PER CREW 50 NO 122 IH2 377 3500 o! pir c
ESTFOR31 CCSD NH 31 RUG 93
TABLE C-2
DESXGH DRTPIPROPULSION VFEHXCLES
DATA POINT I 2 3 4 5 6
VEHICLE CENTAUR S-IVB S-II S-IC ATLAS ATLAS SHUTTLE
BOOSTER SUSTAINER ET (REF)
ENGINES, TYPE RLIOA-3-S J-2S J-2S F-I MR-5 SSME 3
ENGINES, NUMBER 1 I 5 5 2 I 3
ENGINES, THRUST EACH, LB 32800 2H1000 2H0052 1522000 377000 60000 H70000ALTITUDE ALT, NOM ALT, NOM SL SL ALT RLT(RATED)
SPECIFIC IMPULSE, Isp , SEC 446 H33.5 431.5 26H.0 258.98 218.48 453.5
OXIOIZER, 0 L02 L02 L02 L02 L02 L02 L02
FUEL, F LH2 LH2 LH2 RP-I RP-I RP-I LH2MIXTURE RATIO, O/F 5.00 5.00 5.00 2.27 2.25 2,22 6.00 #DENSITY O, PCF 68.60 68.601 68.60 I 69.402 69.40 69.40 71.134
. ° 4.201 49.8] 2 49.81 H9.81 H.4194ot DENSITY F, PCF 4 20 H._O tm BULK DENSITY, PCF 19.29 19.29 19.29 61.95 61.98 61.85 22.53
PROPELLANT MASS, Mp ,LB 29848 22H510 960110 H563HYH 300893 1599789(USABLE MAIN-IMPULSE)
GROSS STAGE MASS, MGt ,LB 34620 266172 1056856 4936991 317434(FLIGHT CONOITION)
MASS RATIO, Mp/MGI 0.862 0.843 0.908 0.924 0.9N8
GROSS STAGE MASS, MC2 ,LB 38735 273898 1066919 5025001 320858 16707H6(GROUND CONDITION)
MASS RATIO, Mp/MG2 0.771 0.820 0.900 0.908 0.938 0.958
0I
I. RSSUMEB SAME AS CENTAUR; 2. RSSUMEO SAME AS ATLAS; £. ON SHUTTLE ORBITER; 4. PRESSEB 0
_ PROPDEBI CCSO WH 31 RUG 83
TABLE C-2 (CONTINUED)
DIESXGNPROPULgXON VEH CLE@
DATA POINT 7 8 9 10 11 12 t9
VEHICLE APOLLO 5 APOLLO 5 APOLLO 5_ TITQN IV TITAN IV TITAN IV STSLM( A ) LM( O ) SM STEP 2 STEP I STEP O SRB 8
ENGINES, TYPE LR87-AJ-tl LR8?-AJ-IIENGINES, NUMBER I I 1 1 2 2 (2 SRB) 2 (2 SRB)
ENGINES, THRUST EACH, LB 3500 10000 21500 103500 273800 1665830 3300000MAX NOM VAC NOM VRC MAX RT 19S INITIAL
SPECIFIC IMPULSE, Isp , SEC S09.3 306.6 309.0 916.45 301.45 271.30 266.40
OXIDIZER, 0 N204 N20H N20H N204 N204FUEL, F UDMHIN2H4 UOMHIN2H4 UDMHIN2H4 UDMHIN2H4 UDMHIN2H4
MIXTURE RATIO, O/F 1.6 1.6 1.6 1.775 1.910
DENSITY 0, PCF 89.21 89.21 89.21 89.21 89.21
DENSITY F, PCF 55 84 55 9H 55.9H 55.9H 55.94I " "
_ BULK DENSITY, PCF 72.60 72.60 72.60 73.46 74.07
PROPELLANT MASS, Mp ,LB 5099 17517 95311 76843 340734 5908009 1107720 ((USABLE MAIN-IMPULSE)
GROSS STAGE MASS, Mot ,LB(FLIGHT CONDITION)
MASS RATIO, Mp/MG1
GROSS STAGE MASS, MG2 ,LB 107776 22893 ? H9860 86274 369029 6958659 I000812"(GROUNO CONDITION)
MASS RATIO, Mp/MG2 0.468 0.765 0.708 0.891 0.923 0.849 0.852
I
5. APOLLO 11MISSION_ G. LUNAR SURFACE" T. IGNITION; 8. POST 51L; 9. FOR ONE SR8 0,
PROPDE02 CCSD NH 31 AUG 93 m
TRBLE C-3
BESXGH BATRSATURH V / nPOLLG
(REF: SRTURN V LRUNCH VEHICLE FLIGHT EVRLURTION REPORT-RS-506, RPOLLO 11
MISSION, MPR-SRT-FE-G9-9, MSFC, SEPTEMBER 20, 19G9)
NOTE: RLL MRSS IS IN POUNDS. STRGE
S-26 S-II S-IVB
FLIGHT CONDITION (NO INTERSTRGES RND NOTHRUST BUILD-UP PROPELLRNT)
GROSS MRSS OF STRGE (REF DRTR) 5023648 1058140 262613
INSTRUMENT UNIT 42?5
THRUST BUILD-UP PROPELLRNT -86657 -1284 -Tt8
GROSS MRSS OF STRGE, MGI 4936991 1056856 266172
0 MRINSTRGE PROPELLRNT, M 4563474 960110 224510I p
Mp/MGi 0.924 0.908 0.8_3
GROUNB CONBITZON (INCLUDING INTERSTRGESaND THRUST BUILD-UP PROPELLRNT)
GROSS MRSS OF STRGE (REF DRTR) 5023648 10581H0 262613
INSTRUMENT UNIT 4275
INTERSTRCE 1353 8779 7010
GROSS MRSS OF STRGE, MG2 5025001 1066919 2?3898
MRINSTRGE PROPELLRNT, M 4563HTH 960110 224510 oP i
Mp/MG2 0.908 0.900 0.820 _0
_ SATUDE01 CCSD WH 31 RUG 93
FIGURE C-4
PAYLOAD oo_PAYLORD BAY SXZXNG16 _ ..................
[ I .,°°, ""PRYLORD t4 _'"'i ........: ...... "......._........!
....!........._........_........!........_........._........!........................._.................12RVERRGE
OENS,T_,oF_-!: ......il-t .......i........i........i.........i........i........i
cubicFoot_ F _ _ _ 130K_O_--" _L.._--"-_ i i i .....i-___:_
4 F": .........!........i.......i'20Ki$ i i _ ! ! i2 ....ii}i!_ili_ii........................................................................................F,,,I,,,,I,,,,I,,,,I,,,,I,,,,I,,,,I,,,,I,,,,I,,,,I,,,,I,,,,I
ql_. 2 4 6 8 tO 12
_ D_ARllRCIALI_:__CARGO VOLUME, THOUSRNDS OF CU FT
Z .............. . ................ :STUDY PRYLORO BRYS !
-'* ........BRSED OH CURVE A ........_........ii
60 ..... _................. >........
mRSS ....i........._........_........!........!.........!........................!" 'T................14
THOUSRNDS 40 .... :........ _........ _........ I........ (......... :...... _............. _........ ! ...... ! I_
OF I0
POUNDS20
ill I .... I,,,,I,,,,I,l,,I,,i,l,,,,I,,llll,,,I,l,,l ....I,,,,I
t0 20 30 40 50 60
LENGTH OF PRYLORD BRY IN FEET
PAYLOADI CCSD WH 31 AUG 93
JSC - 26098
REFERENCES
(Propulsion Vehicles)
1. Titan IV Launch Vehicle Simulation Data Book, MCR-85-2517, Revision 3, Martin
Marietta, April 1988.
2. Shuttle Storable Stage, 1987 JANNAF Propulsion Meeting, (Boyd, Brasher, Mallini, all of
JSC), December, 1987.
3. Shuttle External Tank (ET) Mass Properties Stares Report, MMC-ET-SE02-97, Martin
Marietta Michoud Aerospace, New Orleans, Louisiana, June 15, 1987.
4. Atlas/Centaur Configuration, Performance, and Weight Status Report No. GDC-63-0495-
116, Contract NAS3-22914, September 1982.
5. Saturn V Launch Vehicle Flight Evaluation Report-AS-506, Apollo 11 Mission, MPR-
SAT-FE-69-9, NASA MSFC, September 20, 1969.
6. Apollo 11 Mission Report, MSC-00171, NASA, Manned Spacecraft Center, Houston,
Texas, November 1969.
C-6
JSC - 26098APPENDIX D
DATA BASE AND DATA POINTS
Data Item Page
Mass Data and Design Data Key ........................................................ D-1
Summary of Data ......................................................................... D-2
Mercury Spacecraft Design Mass Summary ........................................... D-3
Mercury Launch Escape System Mass Summary ..................................... D-4
Mercury Launch Escape System Design Mass Summary (JSC Format) ........... D-5
Mercury Reentry Module Mass Summary ............................................. D-6
Mercury Reentry Module Design Mass Summary (JSC Format) ................... I)-7
Mercury Retrograde & Posigrade Design Mass Summary (JSC Format) .......... D-12
Mercury Adapter Design Mass Summary (JSC Format) ............................. D-13
Mercury Spacecraft (dimensioned drawing) ........................................... D-14
Gemini Spacecraft Design Mass Summary ............................................ D-15
Gemini Reentry Module Mass Summary .............................................. D-16
Gemini Reentry Module Design Mass Summary (JSC Format) .................... D-17
Gemini Adapter Section Mass Summary ............................................... D-23
Gemini Adapter Section Design Mass Summary (JSC Format) ..................... D-24
Gemini Spacecraft (dimensioned drawing) ............................................ I)-27
Apollo Spacecraft Design Mass Summary ............................................. D-28
Apollo Launch Escape System Mass Summary ....................................... 1)-29
Apollo Launch Escape System Design Mass Summary (JSC Format) ............. I3-30
Apollo Command Module Mass Summary ............................................ D-32
Apollo Command Module Design Mass Summary (JSC Format) .................. D-33
Apollo Service Module Mass Summary ................................................ D-40
Apollo Service Module Design Mass Summary (JSC Format) ..................... D-41
Apollo Spacecraft/Lunar Module Adapter Mass Summary .......................... D-46
Apollo Adapter Design Mass Summary (JSC Format) ............................... D-47
Apollo Lunar Module Design Mass Summary ........................................ D-48
Apollo Lunar Module-Ascent Stage Mass Summary ................................. D-49
Apollo Lunar Module-Ascent Stage Design Mass Summary (JSC Format) ....... D-50
Apollo Lunar Module-Descent Stage Mass Summary ................................ I)-55
Apollo Lunar Module-Descent Stage Design Mass Summary (JSC Format) ...... D-56
Apollo Spacecraft (dimensioned drawing) ............................................. 13-61
Apollo Lunar Module (dimensioned drawing) ........................................ D-62
Apollo Spacecraft-(1961 comparison to 1968 & 1971 drawing) .................... D-63
JSC - 26098APPENDIX D
DATA BASE AND DATA POINTS(continued)
Data Item Page
ApoUo Saturn V (dimensioned drawing in stages) .................................... D-64
Apollo SaturnV, S-IC Engine Installation (dimensioned drawing) ................ D-65
Skylab Spacecraft Design Mass Summary ............................................. D-66
Skylab Payload Shroud Mass Summary ............................................... D-68
Skylab Apollo Telescope Mount Mass Summary..................................... 1)-69
Skylab Multiple Docking AdapterMass Summary ................................... D-70
Skylab Airlock Module Mass Summary ............................................... D-71
Skylab Insmmaent Unit Mass Summary ............................................... D-72
Skylab Orbital Workshop Mass Summary ............................................. D-73
Skylab Spacecraft (dimensioned drawing, launch configuration) ................... D-74
Skylab Modules (dimensioned drawing, launch configuration) ..................... D-75
Skylab Orbital Workshop (dimensioned drawing, launch configuration) .......... D-76
Skylab Spacecraft (dimensioned drawing, orbit configuration) ..................... D-77
Apollo-Soyuz Test Project Design Mass Summary ................................... D-78
Apollo-Soyuz Test Project (dimensioned drawing) ................................... D-79
Space Shuttle Vehicle Design Mass Summary ........................................ D-80
Space Shuttle Discovery (OV-103, flight 10) Mass Summary ...................... D-81
Space Shuttle Orbiter Design Mass Summary (JSC Format) ........................ D-82
Space Shuttle F.xtemal Tank (LWT-001) Mass Summary ........................... D-88
Space Shuttle External Tank Design Mass Summary (JSC Format) ................ I)-89
Space Shuttle Solid Rocket Boostex Mass Summary ................................. D-92
Space Shuttle Solid Rocket Booster Design Mass Summary (JSC Format) ....... D-93
Space Shuttle Vehicle (configuration drawing) ........................................ D-99
Space Shuttle Vehicle (design geometry) .............................................. D-100
Space Shuttle Orbiter (configuration drawing) ........................................ D-101
Space Shuttle Orbiter (design geometry) ............................................. ..D-102
Space Shuttle Vehicle Orbiter (side view dimensioned drawing) ................... D-103
Space Shuttle Vehicle External Tank (dimensioned drawing) ....................... D-104
Space Shuttle Vehicle Solid Rocket Booster (dimensioned drawing) .............. D-105
JSC Spacecraft (scaled drawings launch vehicle configuration) .................... D-106
JSC Spacecraft (scaled drawings launch configuration) ............................. D- 107
JSC Spacecraft (scaled drawings orbit configuration) ................................ D-108
JSC - 26098Mass Data and Design Data Key
Definition of Data Points Used Throughout This Document
1. PRO_CT MERCURY1A. Launch Escape System (LES)
lB. Reentry Module (RM)1C. Rctro Pack (RP)
1D. Adapter Section (AS)
2. QEMINI PROGRAM
2A. Reentry Module (RM)2B. Adapter Section (AS)
3. APOLLO PROGRAM
3A. Launch Escape System (LES)3B. Command Module (CM)3C. Service Module (SM)
3D. Spacecraft Lunar Module Adapter (SLA)3E. Apollo Lunar Module Ascent Stage (AS)3F. ApoUo Lunar Module Descent Stage (DS)
3J. Saturn/Apollo S-IVB Stage3K. Saturn/Apollo S-ll Stage3L. Saturn/Apollo S-I Stage
4. SKYLAB PROGRAM
4A. Payload Shroud (PS)4B. Apollo Telescope Mount (ATM)4C. Multiple Docking Adapter (MDA)4D. AirlockModule (AM)4E. Instrument Unit 0U)
4F. OrbitaIWorkshop (OWS)
5. APOLLO-SOYUZ TEST PROJECT (ASTP)
5A. Apollo Command and Service Module (CSM)5B. Docking Module (DM)5C. Soyuz Spacecraft
6. SPACE SHUTILE VEHICLE (SSV)6A. Orbiter6B. External Tank (ET)6C. Solid Rocket Booster (SRB)
7. CENTAUR8.9.
D-1
NOTE: RLL MRSS DRTR_POINT DE_ H_S_ _UH_Yis IN POUNOS.
MERCURY SPRCECRRFT (20 FEB G2)
FUNCTXOHRLSYSTEH CODE I=1 B C D
REFERENCE: PROJECT MERCURY ACTURL
........................................................................................................................... WEIGHT REPORT, CRPSULE HO, 16 (MR-e),
...I..L...S.TR..U...CT..U.R.E. .......................... k.6H ........... _._."_ ............ ._._ .......... _'.8.0. rlCOONHELL RIRCRRFT, REPORT 91"1,PRGE 3, 8 OCT 1962.
.............................................................. 2_ ......... _SQ .............. T ................. - .... G9,85gD
........................................................................................................................... 74. 500 --_ _.
,..3._..,.p.R.qP..UL.S.f.gN......................_.5_...........1.5_.............6.H............ - .... _ 32.Do _ ..............."_7
..........................-.............................................................................. * .... - "_ ; "_ ._ ico. OL ............-.................-.................:...............-...."--ad-l-....... ........7.............;..........q 7-• , __, i
"i_Trivi6i_ics............................................................................................_ _5.99_ -,- _.._. • _ t ......J.............................................................. T. .............. 3..], _ ............ - ................. - .... < LAUNCH ESCRPE ....
...........................................................................................................................?. EHVIRONMENT :341 i SYSTEM __--5_.75--).............................................................. --. ................................... -- ................. 7: .... --_ 24.0 _58.3B!22.75 ATLAS
................................................................... I,,,I,,,I,,,I • i 10.832.________ _ AORPTER
...8.._...O.J[.I__:..R....................................2.3H..........._,.O.B.............2.o................5.. e 20 4o 68 REENTRY MODULEINCHES (Se CU FT PRESSURIZED)
0 ................................................. 4.................. • ................. ,................. _ .................
I 9. GROQTH z208.57 z94.238.............................................................. 77................ 7:................. T ................. 7_....
............... I I • 336 • 741
DRY HRSS ......... _._8. 2393 125 190 Z389.43 MERCURYSPACECRFIFT Z52.6891
........................................................................................................................... NOTE: ALL DIMENSIONS
10_ _IOI_-_.RI_.GO...........................- ........... ZH4..............= ................- .... FIRE IN INCHES.
MERCORO1 CCSO WH 14 RUG 89
.!..I....CRRGO ......................-.................:-.................-................-...NOTE °=............ I !
..............!HE_.T...H_!S!_................7.9_......_._7_...........i._5. 190. .A. LAUNCH ,.ES_:.RP.E..S.y_S.T.E._I.(..LE.S._................................................................
...........................................................................B REENTRY MODULE .(.RM)....................................
..2.L..I_.O.N.-.P.,R.O.I_.E._.I_B.N.T...............-................32.......7 .......-.......c .......RE.T.I_.O...P..8I_K...E.RE.)................................................................................................
..................................................................................... P..........R.D.QP.T.ER..,SEC.T.[.Ott..(._.S.)..............................................
.._._....PR.p.PE.I=L...FI.N.T.......................2.9._............_ .........._,.44 - RM FI$
.................. DESIGN-E.I_WELPPE.YQLPI:!E_ _t_l_ ( CU FT ) ....I,!..0...........]...!.!_.....
.............. !;.RO..SS. !_R.S S............. Lo.9._........ ;_725_.......... 26.9 ......... k_.O....... I_IRE S.SUR..I..z.E.B..v o.L U.ME.: .. Y.p.p.. (..CU E! ) ..................................... 50 ............. o .......... _)
................... _;._f27t_ ) .............................................................................. O.ES,!_;.H-E.I_VE.L_.I_E....$.LU_F. FIR.E!9: .l_ d _..(S.Q. ET) ............ L1 39 ........... 80 ....
...................................................................................................................................6EsiGNMTs_ToN......_fiFiVSMFiXiERELioFoNE..............................................o................................................................................................................................................................"sioEwFii2o_iL_................
MERCMPO1 CCSO WH 19 BUG 93
NOTE: ALL MASS H_ _UHHARY DATA POINT
IS IN POUNDS. MERCURY LAUNCH ESCAPE SYSTEM (2@ FEB 62) Q
...................................................................... q
I. STRUCTURE w IG4.1_ ..................................................................................................................................................................................................IRU_ .............................................._........1.LB.,..ZB............_.I.RC.U.I.IR_..................................................................... 8ERP.QZS.a_.I.C...._P.I.KE..............._..........aS.,.]._..........RI.U_$ ...................................................................................... LB_N.CB..E$.C_._E...$_...$.ER..i............1..,._.i .........BaLL_.S.I................................................ I.B_.,.L2................_J.!_.U...RLH_ ....................................L!.,..3e .... ES¢.RP.E..RqC._g.!...g.!.R_ .................... !.,.!Z ..........e_._Q._..._.E!.!.!._.QN...RQ.CKE!................e_.,.ZR................_.EP.SRaI.I.QR..R.I.U_...SU.Q....._........._._.,._.Q ...............E_kQU...QEI.I.I._O.U...EtRE.....[ ..........._.,.Z_ .................................................................................................................C._ER ........................................................................ ELEC.IRI_BL...IU_NEL_ ........................ 8.,.1._ ............................................................................................
ELECTRICR_ IHSTRLLRTIO_ 9.06 ..........................................................................................;..........................................................................................,.........................................
i 9. GROHTH................................................................................................................................................................._.......................DRY _RSS 798.4..................................................................................................................................................................}..................................................................................................................
................................................................................................................................................................_...........2......._i__NON_'_'gR'_6....................................i..........._........5. CONTROL
I................................................................................................................................................................._........................:x'-'"'aa':-aax'a>::x:v .............................................
...................................................................._......3_'_-_'_'_..............................................,......................._..................................................................................................................3. PROPULSION
.........._P.I_R..._.8_.E .................................i......._.6.,.3_ ...................................................................... ,..................................................................................................................@
?. EHVIROHMEHT
(
7;7_777;7;17;77;7;7;77777;i:_7 7......................................................................i.......................7777777 7777;77777777i;777777
......................................................................_.....................ill!ii)iiiiliiiiillliii!iiiili.........................................iiiiiilli i1o_._,_.................................................................................................................................... GR088 _RS8 (• (
I
MERCMP02 CCSD NH _ HOV 92
JSC-2S09SMERCURY LAUNCH ESCAPE SYSTEM
DESIGN MASS SUMMARY (JSC FORMAT)ALL MASS IN POUNDS
i. STRUCTURE
TRUSS 118.76
TOTAL FOR TRUSS ( 118.76)ATTACH RING 11.32
SEPARATION RING & COVER 34.09
TOTAL FOR RINGS ( 45.41)
TOTAL FOR STRUCTURE ( 164.17)
2. PROTECTION
HEAT PROTECTION 22.39
TOTAL FOR HEAT PROTECTION ( 22.39)
TOTAL FOR PROTECTION ( 22.39)
3. PROPULSION
MOTOR CASE 356.3
TOTAL FOR MOTOR CASE ( 356.3)
TOTAL FOR PROPULSION ( 356.3)
4. POWER
LAUNCH ESCAPE SYSTEM SEPARATIO 1.82ESCAPE ROCKET FIRE 1.17
PYLON JETTISON FIRE 0.76
TOTAL FOR CIRCUITRY ( 3.75)ELECTRICAL TUNNELS 9.14
TOTAL FOR ELECTRICAL TUNNELS ( 9.14)ELECTRICAL INSULATION 9.06
TOTAL FOR ELECTRICAL INSULATIO ( 9.06)
TOTAL FOR POWER ( 21.95)
8. OTHER
AERODYNAMIC SPIKE 25.7
TOTAL FOR AERODYNAMIC SPIKE ( 25.7)BALLAST 185.17
TOTAL FOR BALLAST ( 185.17)PYLON JETTISON ROCKET 22.73
TOTAL FOR PYLON JETTISON ROCKE ( 22.73)
TOTAL FOR OTHER ( 233.6)
13. PROPELLANT
PROPELLANT 293.2
TOTAL FOR PROPELLANT ( 293.2)
TOTAL FOR PROPELLANT ( 293.2)
GROSS VEHICLE WEIGHT 1091.61
D-5
NOTE: RLL .ASS Hn$$ SUHHI_I_Y OnTAPOINtIS IN POUNDS. MERCURY REENTRY MODULE (28 FEB 62) (_
.....i`T..../._._._;_._._.._..L./....................;/.1........................._......................_._._....._........_.._........E._._._....../......................../.........................................................K............._/....._._._..................................................................................................8:__ .............................................._..........._8.........P.REE_UR.I._E.B..B.O_X.................................._I................EE.I._B.RY...BBII...K._._................._.............1._e.............&H.UI.E...EY$...K._._......................................I,_.%...
..........LRR_E...BULK_E.eD......................................_%..............._.Q_B..,BBI%.._._.._ ...................................... 3._...............I._._.I..._._S ............................................. l._E..SMALL B_LKH_RO lS , MISC_ BRTT 10 CHUTE, IMPACT SYS WIR 21
........._._ .............................................................._._...............O._...EO_.E_..._.I.EI._....................................1,5..........R£_E_...E_ .........................................._5...
..........B.I_QBB.S...BB_...F.RB._£.............................._ ................_E._O._E.R..$._E_EU...................................._ ............ELO_._.QH..BRLL_ _ ....ffl............._._L.._G_ ........................................_ ........................................................................._................................R_.U_._L_H_RD_T .......i..............!-8
............W I.R.I.U.G............................................................................. _._EB_.._E._.(....$.EB._...BE_._ ................. _... ½_ S. GROWTHOOORS..........................._._.... _._c_......................................................._.......................DRY,,..M.R.SS...................................e_,_3....PBRBC_E STRUCT PR_V 36 MOUNTING 12 ...................................................................... :.......................
.. _..B_._£._..._._U_ .......... i .............. _ ....... _.L..._ ONTROL ........................................... c-. 18. NON-CARGO ........................ _5
...........B_H.e ........................................................_? .........................................................................................................R_S _O_ _R_E_ .........................5.......RNTE_..._._C_ ..........................................._...............................................................................................CREW (I) 180
......._._L.............................................._.............._.._..............................................................................................._._._._._._.._1_.._._.1_._..._..._._.._...._._._._._................../._...._...........i..........................._._................................................................................................... SURVIy.RL..._._ .................................._ ....
.....................................................................;...................... ............BB._._ ..........................................................)....K..........._i_""'2:'"'PR'OTEC'T'iON .............................._'"_..........._'B_.... 6":"RqiONICS ...................................... 11. CARGO
..........U._..._P_..._.I.H_._.............i...........U._ ..........._u.H.I._._._P._....................................U._...I
m ..........B.E_...$.EI.EL.B..B.BLBZ_.YE........_..........._._B............ BI._.I.I.UP.E..G.qH._..._._ ..............................................................................................................................: RUTOMRTIC CONTR 81 i_. NOH-PROPELLRNT 3_
: .................................._E_ _ES$ _H¢.,. _,_..I.b.._ .................._....
..................................................................:............................................................................................................................._.__.E_.._._.QO.L.I.H.G)..................................._._....3. PROPULSION ( 15_ OXYGEN (CREW) 8
.........._ES.._.U_._ER.$.........................i.............._L..........................................................................................................._X.ER....(_RE_._............................................B....
..........._.C_._O_R_LLE.R_.....................L.............._._.............................................................................................................................................................................................RCS M.q_NTI_G ! .........._.I........................................................................
;.L.._._Lb._E_._.__E...2..../........i.............._.o........_.,...._._o_._._..............................F..........._._..._._._......._._._._._._._._.................................................................C...L........._._.//........_C$ _E._.U_IZO._.LQN...SY.$..i...............i._...............E_._P.NUE._._L..._O._2E..$.Y_............I._._...............R,C$...RE._O._I.QE..._$._B.LE........................_5..............._C_._R._LLRN._..._S ............................_ ........ PANELS, MISC.L........................j 6S i ............_E_O _k_G ............................_ .........._B ..............$.E_ ................................................................_._......................................................................._................................._._E._E._...$.L_ ........................................_._................SE.ET...I_.E_L..................................!...............)._.......................................................................! ......................................................................................... ; ...................... RTTITUDE CONTR SYS ..................................................................... i .....................
......................................... m
; ............U.8._U.BL...._O,_.R........................................._$ ........................................................................ _........................................................................................._................................I._E._.I.Q_....L.I.G_._,_...................................._.. m......................................................................)....................... DISPLRYS q8 GRO_8 hRS9 z?2_
MERCMP03 CCSO WH 9 NOV 9_
dSC-26098MERCURY REENTRY MODULE
DESIGN MASS SUMMARY (JSC FORMAT)ALL MASS IN POUNDS
i. STRUCTURE
HATCH (ENTRANCE) 16.06PERISCOPE 9.48
SNORKEL AIR INLET 3.6
MISCELLANEOUS 1.44
TOTAL FOR ACCESS DOORS ( 30.58)HOIST SUPPORT STRUCT 3.86
TOTAL FOR HOIST SUPPORT STRUCT ( 3.86)LARGE (AFT) BULKHEAD 46.89
TOTAL FOR LARGE (AFT) BULKHEAD ( 46.89)STRUCTURE 37.31
BICONE ANTENNA 26.67
CIRCUITRY 0.91
EJECTOR 5.53
CLAMP RING ATTACH 1.07
TOTAL FOR NOSE ANTENNA (71.49001)PAINT 5.
TOTAL FOR PAINT ( 5.)PARACHUTE STRUC PROV 35.85
TOTAL FOR PARACHUTE STRUC PROV ( 35.85)SKIN 30.98
LONGITUDINAL STIFFENERS 39.77
TOTAL FOR PRESS BODY (SIDE) ( 70.75)SHEAR WEBS,SEAT BEAMS&SUPPORTS 27.52
TOTAL FOR SHEAR WEBS ( 27.52)SMALL (FWD) BULKHEAD 16.44
TOTAL FOR SMALL (FWD) BULKHEAD ( 16.44)CONTOUR BREAK (STA 164) 5.33
HEAT SHIELD ATTACH (STA 104) 17.74
SEPARATION (STA 184) 5.57
SPLICE FITTING (STA 164) 6.22
TOTAL FOR SPECIAL RINGS ( 34.86)VIBRAT TEST MISC FIX 1.83
TOTAL FOR VIBRAT TEST MISC FIX ( 1.83)WINDOW POLE 0.59
TOTAL FOR WINDOW POLE ( 0.59)WINDOWS & FRAMES 29.82
TOTAL FOR WINDOWS & FRAMES ( 29.82)
TOTAL FOR STRUCTURE ( 375.48)
2. PROTECTION
HEAT PROTEC SHINGLES 113.78
TOTAL FOR HEAT PROTEC SHINGLES ( 113.78)INSERTS 1.3
ABLATION ASSEMBLY 297.59
ABLATED MATERIAL 6.5
RING, BALLAST MOUNTING 2.2
TOTAL FOR HEAT SHIELD ( 307.59)INSULATION 57.6
TOTAL FOR INSULATION ( 57.6)TOTAL FOR PROTECTION ( 478.97)
3. PROPULSION
PRESSURE SYSTEM BOTTLE-MANUAL 5.35
PRESSURE SYSTEM VALVING-MANUAL 3.23
D_7
JSC-26098
PROPELLANT SYSTEM TANK-MANUAL 8.65
PROPELLANT SYS TANK MOUNT-MAN 1.78PROPELLANT SYSTEM TUBING-MANUA 7.03
PROPELLANT SYSTEM VALVING-MAN 5.61
THRUST SYSTEM THRUSTERS-MANUAL 5.66
CNTRL SYSTEM PUSH-PULL-MANUAL 1.26CNTRL SYSTEM CIRCUITRY-MANUAL 1.16
MAN CNTRL SYS RATE STABIL SOLE 6.01INSTALL MOUNTING & SUPP-MAN 4.62
INSTALLATION INSULATION-MANUAL 2.89
PRESSURE SYSTEM BOTTLE-AUTO 5.35
PRESSURE SYSTEM VALVING-AUTO 3.2
PROPELLANT SYSTEM TANK-AUTO 11.16
PROPELLANT SYS TANK MOUNT-AUTO 2.21
PROPELLANT SYS TUBING&FTGS-AUT 4.07
PROPELLANT SYSTEM VALVING-AUTO 2.29
THRUST SYSTEM THRUSTERS&SOLEN 15.44
CNTRL SYSTEM PUSH-PULL-AUTO 3.06
CNTRL SYSTEM CIRCUITRY-AUTO 0.3
INSTALL MOUNTING & SUPP-AUTO 6.33
INSTALLATION INSULATION-AUTO 6.86INSTALLATION HEAT SINKS-AUTO 9.74
TOTAL FOR REACTION CONTR SYST ( 123.26)RETRO CIRCUITRY 28.34
TOTAL FOR RETRO CIRCUITRY ( 28.34)
TOTAL FOR PROPULSION ( 151.6)
4. POWER
PRIMARY BATTERIES 152.2
SQUIB BATTERIES 50.
BATTERY VENT SYSTEM 0.81
EXTERNAL POWER SUPPLY 2.95
DIODE PANEL 1.88
POWER RELAYS 3.99
DC POWER CIRCUITRY 14.12
AC POWER PRIMARY INVERTERS 15.52
AC POWER RESERVE INVERTER 9.38AC POWER CIRCUITRY 5.47
EXTERNAL POWER CIRCUITRY 0.77
GROUND TEST CIRCUITRY 11.38TOWER SEPARATION CIRCUITRY 4.74
ESCAPE ROCKET CIRCUITRY 3.64
PYLON JETTISON CIRCUITRY 1.2
ADAPTER SEPARATION CIRCUITRY 8.95
ABORT INITIATION CIRCUITRY 6.89
LAUNCH & ORBIT, MISCL CIRCUITR 6.56EMERGENCY HOLD CIRCUITRY 2.21
PIGTAILS 0.92
TERMINAL BLOCKS 4.74
MOUNTING & INSTALLATION 11.78
TOTAL FOR ELECTRICAL SYSTEM ( 320.1)
TOTAL FOR POWER ( 320.1)
6. AVIONICS
HORIZON SCANNER 7.87HORIZON SCANNER MOUNTING 0.51
HORIZON SCANNER CIRCUITRY 0.73
ATTITUDE GYROS (2) 14.78
RATE GYROS (3) 6.03
D-8
JSC-26098
CALIBRATOR 31.28
ACCELEROMETER 0.61
RATE DAMPER 5.25
MOUNTING 1.28
CIRCUITRY 13.04
TOTAL FOR ATTITUDE CONTROL SYS ( 81.38)BICONE ANTENNA 1.2
UHF DESCENT ANTENNA 0.81
HF VOICE UNIT 3.22
HF VOICE CIRCUITRY 1.93
UHF VOICE UNIT 3.55
UHF VOICE CIRCUITRY 2.1
MIKE/AUDIO CONTROL UNITS 3.25
MIKE/AUDIO CONTROL CIRCUITRY 3.58S BAND UNIT 12.2
S BAND CIRCUITRY 0.51
C BAND UNIT 11.8
C BAND CIRCUITRY 0.24
COMMAND RECEIVER / DECODER 9.5
COMMAND CIRCUITRY 3.56ANTENNA SWITCHING UNITS 10.3
ANTENNA SWITCHING CIRCUITRY 1.68
MISCL CONTROL CIRCUITRY I.ii
EQUIPMENT SHELVING 19.08
C&S BAND ANTENNA 6.15
ANTENNACIRCUITRY/COAXIAL CABLE 4.53
EQUIPMENT MOUNTING 12.6
TOTAL FOR COMMUNICATIONS ( 112.9)PERSONNEL ENVIRON SENSORS 3.46
BIO MED SENSORS 9.47
PILOT CAMERA 6.87
INSTRUMENT CAMERA 8.19
RECORDER 13.79INSTALLATION/CIRCUITRY 3.93
TRANSMITTER UNITS 2.78
TRANSMITTER POWER SUPPLY (2) 3.58TRANSMITTER PROGRAMMER 2.75
TRANSMITTER CIRCUITRY 9.6
COSMIC RAY DETECTOR 1.24
SIGNAL CONDITIONING PACKAGE C 5.92
CIRCUITRY, SENSOR CIRCUITS 14.31
OUTSIDE TEMP SENSORS 2.45
REACTION CONTROL SENSORS 1.9
SIGNAL CONDITIONING PACKAGE E 3.1
SIGNAL CONDITIONING MOUNTING 1.27
SIGNAL CONDITIONING PACKAGE A 14.78
SIGNAL CONDITIONING PACKAGE D 11.3
TOTAL FOR INSTRUMENTATION ( 120.69)
TOTAL FOR AVIONICS ( 314.97)
7. ENVIRONMENT
INDICATORS 30.89
CIRCUITRY, INSTALLATION 16.81
TOTAL FOR DISPLAYS ( 47.7)SUIT BOTTLE 9.21
SUIT VALVING 2.46
SUIT PRESSURE REGULATOR i. 5
SUIT CONTROLS 1.72
SUIT COMPRESSORS 3.8
D-S
JSC-2S0S8
SUIT C02 AND ODOR ABSORBER 13.13
SUIT HEAT EXCHANGER 2.87
SEPARATOR, SUIT WATER 3.97
SUIT COOLANT QUANTITY INDICATO 2.36
SUIT COOLING WATER TANK 5.7
SUIT CONDENSATE TANK 1.31
SUIT VALVES AND CONTROLS 5.58
SUIT DUCTS 3.62
SUIT SOLIDS TRAP i.i
EMERGENCY BREATHING BOTTLE 9.21
EMERGENCY BREATHING VALVING 1.61
EMERGENCY BREATHING CONTROLS 0.93
EQUIPMENT COOLING BLOWER 0.74
EQUIPMENT COOLING HEAT EXCHANG 2.2
EQUIPMENT COOLING VALVING 3.88
CABIN PRESSURE RELIEF 5.05
POST LANDING VALVES 8.38
POST LANDING CONTROLS 0.69
POST LANDING DUCTS 1.76
POST LANDING BELLOWS MOTOR 1.05
INSTALLATION PARTS 17.59
CIRCUITRY 5.62
INVERTER COOLING FIX 10.36
TOTAL FOR ENVIRON CONTROL SYST ( 127.4)INTERIOR LIGHTS 3.82
TOTAL FOR INTERIOR LIGHTS ( 3.82)FLY-BY-WIRE CIRCUITRY 2.2EMERGENCY MANUAL RELEASE 5.21
ABORT HANDLE ASSEMBLY 1.69
HAND CONTROLLER 2.78
RODS AND BELLCRANKS 9.83
SUPPORT BRACKETRY 3.84
TOTAL FOR MANUAL CONTROL SYST ( 25.55)MAPS, CHARTBOARD 1.78
PANEL, CONSOLES 16.91PERISCOPE 45.26
PERISCOPE CIRCUITRY 2.29
TOTAL FOR PANELS, MISC ( 66.24)BULKHEAD WEB, LEG SUPPORT 5.55COUCH 53.7
RESTRAINT 10.82
TOTAL FOR SEAT ( 70.07)
TOTAL FOR ENVIRONMENT ( 340.78)
8. OTHER
ACTUAL WEIGHT ADJUST 18.
TOTAL FOR ACTUAL WEIGHT ADJUST ( 18.)FLOTATION BALLAST 41.
TOTAL FOR FLOTATION BALLAST ( 41.)DROGUE CHUTE 11.51
RESERVE CHUTE 67.11CHUTE SYSTEM CONTROLS 4.12
CHUTE SYSTEM MOUNTINGS 2.32IMPACT SKIRT 23.67
PILOT CHUTE 4.32
MAIN CHUTE 67.86
IMPACT STRAPS AND SPRINGS 10.47
IMPACT FIBERGLASS SHIELD 26.6
IMPACT MISCL SKIRT INSTALLATIO 17.29
0-10
JSC-26098IMPACT PNEUMATICS & MECHANISM 15.92
CIRCUITRY 21.39
IMPACT CAPSULE RING 14.39
IMPACT HEAT SHIELD RING 27.8
TOTAL FOR LANDING SYSTEM ( 314.77)RESCUE BEACON 7.4
WHIP ANTENNA 4.95
CIRCUITRY 3.85
SOFAR BOMBS 4.36
DYE MARKER 3.54
CHAFF 0.6
DISPLAY 1.4
RECOVERY VOICE 4.88
SUPER SARAH 3.81
TOTAL FOR RECOVERY SYSTEM ( 34.79)
TOTAL FOR OTHER ( 408.56)
i0. NON-CARGO
BALLAST I.
TOTAL FOR BALLAST ( i.)CREW (i) 180.
TOTAL FOR CREW (i) ( 180.)RCS PEROXIDE TRAPPED 5.
TOTAL FOR RCS PEROXIDE TRAPPED ( 5.)SUIT (i) 24.
TOTAL FOR SUIT (i) ( 24.)SURVIVAL KIT 34.
TOTAL FOR SURVIVAL KIT ( 34.)
TOTAL FOR NON-CARGO ( 244.)
12. NON-PROPELLANT
OXYGEN (CREW) 8.
TOTAL FOR OXYGEN (CREW) ( 8.)RCS PRESS (He,.5 LB) i.
TOTAL FOR RCS PRESS (He,.5 LB) ( i.)WATER (COOLING) 15.
TOTAL FOR WATER (COOLING) ( 15.)WATER (CREW) 8.
TOTAL FOR WATER (CREW) ( 8. )
TOTAL FOR NON-PROPELLANT ( 32.)
13. PROPELLANT
RCS PEROXIDE USABLE 55.
TOTAL FOR RCS PEROXIDE USABLE ( 55.)
TOTAL FOR PROPELLANT ( 55.)
GROSS VEHICLE WEIGHT 2721.46
O-'! 1
JSC-2G098MERCURY RETROGRADE&POSIGRADE SYST
DESIGN MASS SUMMARY (JSC FORMAT)ALL MASS IN POUNDS
i. STRUCTURESTRUCTURAL INSTALLATION 27.71
TOTAL FOR STRUCTURAL INSTALLAT ( 27.71)PAINT 0.27
TOTAL FOR PAINT ( 0.27)
TOTAL FOR STRUCTURE ( 27.98)
3. PROPULSION
CASE AND NOZZLE 57.18
IGNITERS 2.46
HEATERS 2.25
TOTAL FOR RETROGRADE SYSTEM ( 61.89)RETENTION STRAPS 2.17
TOTAL FOR RETENTION STRAPS ( 2.17)
TOTAL FOR PROPULSION ( 64.06)
4. POWER
RETRO PACKAGE CIRCUITRY 10.21
CIRCUITRY SHIELDING 2.89
TOTAL FOR CIRCUITRY ( 13.1)
TOTAL FOR POWER ( 13.1)
8. OTHER
POSIGRADE ROCKETS 16.05
TOTAL FOR POSIGRADE ROCKETS ( 16.05)
RETRO SYS ACT WT ADJ 0.16
TOTAL FOR RETRO SYS ACT WT ADJ ( 0.16)TOTAL ACTUAL WEIGHT ADJUSTMENT 4.
TOTAL FOR ACTUAL WEIGHT ADJUST ( 4.)
TOTAL FOR OTHER ( 20.21)
13. PROPELLANT
PROPELLANT 144.74
TOTAL FOR PROPELLANT ( 144.74)
TOTAL FOR PROPELLANT ( 144.74)
GROSS VEHICLE WEIGHT 270.09
D-12
MERCURY ADAPTER J S C - 2 S O S 8
DESIGN MASS SUMMARY (JSC FORMAT)ALL MASS IN POUNDS
i. STRUCTURE
SKINS 68.
TOTAL FOR SKINS ( 68.)TOP SEPARATION 8.64BOTTOM BOOSTER ATTACH 7.85
INTERMEDIATE,MA-4 BEEF-UP 24.61
ATTACHMENTS, BOOSTER/ADAPTER 1.74
TOTAL FOR RINGS ( 42.84)ACCESS DOORS 17.51
TOTAL FOR ACCESS DOORS ( 17.51)STRETCH FITTINGS 2.84
TOTAL FOR STRETCH FITTINGS ( 2.84)SEPARATION RING 48.81
TOTAL FOR SEPARATION RING ( 48.81)
TOTAL FOR STRUCTURE ( 180.)
4. POWER
ABORT CIRCUITRY 1.36
CAPSULE SEPARATION CIRCUITRY 2.42
EMERGENCY HOLD CIRCUITRY 0.09
INSTALLATION CIRCUITRY 0.94
TOTAL FOR CIRCUITRY ( 4.81)
TOTAL FOR POWER ( 4.81)
8. OTHER
ACTUAL WEIGHT ADJUSTMENT 4.87
TOTAL FOR ACTUAL WEIGHT ADJUST ( 4.87)
TOTAL FOR OTHER ( 4.87)
GROSS VEHICLE WEIGHT 189.68
D-13
HERCURY SPACECRAFT
REFERENCE: PROJECT MERCURY ACTUAL
WEIGHT REPORT, CAPSULE NO. 16 (MR-B),
MCDONHELL AIRCRAFT, REPORT 9141,
PAGE 3, B OCT 1962.
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FUHCTIOHRLSYSTEH CODE R B C D
f-.-,,-- _DRPTER SECTION_
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GEMINI REENTRY MODULE JSC-26098
DESIGN MASS SUMMARY (JSC FORMAT)ALL MASS IN POUNDS
I. STRUCTURE
SIDE PANELS 44.47ECS BAY 37.67
MISCELLANEOUS PANELS 8.67
ECS DOOR 26.77
EQUIPMENT SUPPORTS,SIDE PANELS 8.54SEALANT 5.
TOTAL FOR PRESS BODY STRUCTURE ( 131.12), PANELS 18.14
STIFFENERS 44.41
INSTALLATION 16.17
TOTAL FOR LARGE BULKHEAD ( 78.72)PANELS 12.56
STIFFENERS 3.14
TOTAL FOR SMALL BULKHEAD ( 15.7)FIXED STRUCTURE, SILLS 57.84ACTUATOR 44.3
HINGE FITTING, DRIVE BEAM 37.BASIC SKIN 29.3STRUCTURE DETAILS 81.46
WINDOW 25.74HATCH MECHANISM 44.69
FLIPPER DOORS 10.86
FLOTATION CURTAINS 2.9
HATCH ATTACH BOLTS 4.63
TOTAL FOR CREW HATCH ( 338.72)SKIN PANELS, FORWARD SMALL BHD 14.96
PANELS, SMALL BULKHEAD 7.59
PANELS, OUTBOARD OF HATCHES 4.19
STRINGERS 27.5
STIFFENERS 2.25
RINGS 9.82
RING, HEAT SHIELD ATTACH 9.02
TENSION TIES 11.14
TOTAL FOR NON-PRESS STRUCTURE ( 86.47)MAIN LANDING GEAR FITTINGS 31.9
TOTAL FOR MAIN LNDG GEAR FTGS ( 31.9)LARGE BULKHEAD 25.15
TOP CENTER BEAM i0.01
FLOOR EXTENSION 8.24
EQUIPMENT SUPPORT BEAMS 24.65
TOTAL FOR SHEAR PANELS ( 68.05)DOOR, EQUIPMENT ACCESS 43.46
DOOR, MAIN LANDING GEAR 29.02
DOOR, UMBILICAL 2.33
DOOR, MISCELLANEOUS ACCESS 4.6
TOTAL FOR DOOR ( 79.41)MISCELLANEOUS STRUCTURE DETAIL 11.8
HORIZON SENSOR COVER 9.21
HOIST FITTINGS 8.12
FLOTATION MATERIAL 6.98
PAINT 6.7
REPAIRS 7.5
ATTACHING HARDWARE 20.88
TOTAL FOR MISCELLANEOUS ( 71.19)
D-17
JSC-26088
SKIN, STRINGERS 17.7RINGS 30.26MISCELLANEOUS STRUCTURE DETAIL 2.26
FLOTATION MATERIAL 19.19SEALANT 0.78
ATTACHING HARDWARE 7.91
TOTAL FOR RCS SECTION (FIXED) (78.09999)
SKIN, STRINGERS 25.79RINGS 18.54
SEPARATION RING 3.11
MISCELLANEOUS STRUCTURE DETAIL 7.74
EQUIPMENT MOUNTING 1.72NOSE FAIRING 26.4 _ATTACHING HARDWARE 11.61
TOTAL FOR RENDEZ&RECOVERY SECT ( 94.91)
TOTAL FOR STRUCTURE ( 1074.29)
2. PROTECTION
SHINGLES 31.58
INSULATION 18.51
TOTAL FOR CREW HATCH ( 50.09)SHINGLES 65.36
INSULATION 84.18
TOTAL FOR CABIN WALL ( 149.54)SHINGLES 38.19
INSULATION 24.23
TOTAL FOR RCS SECTION ( 62.42)SHINGLES 73.67
INSULATION 48.68
TOTAL FOR RENDEZ&RECOVERY SECT ( 122.35)ABLATIVE MATERIAL 187.06
EDGE RING 27.4
HONEYCOMB BACK-UP 103.93
RING, HEAT SHIELD ATTACH 12.05SPACERS, SHIELD BACK-UP 10.24MOUNTING DETAILS 3.66
ACTUAL WEIGHT 0.86
TOTAL FOR HEAT SHIELD ( 345.2)
TOTAL FOR PROTECTION ( 729.6)
3. PROPULSION
ENGINES 37.44
ENGINE MOUNTING 4.2PRESSURIZATION SYSTEM TANKS 4.32
PRESSURIZATION TANK MOUNTING 1.68
PRESSURIZATION SYSTEM VALVING 21.88
OXIDIZER TANK 7.67
OXIZIZER TANK MOUNTING 1.68
OXIDIZER VALVING 4.52
FUEL TANK 8.54
FUEL TANK MOUNTING 1.34FUEL VALVING 4.48
LINES, MISC. 8.41SHUT-OFF VALVES 8.88
VALVING, MISC. 6.07
MOUNTING DETAILS, MISC. 0.72HEATERS 3.76
CIRCUITRY 18.03
TOTAL FOR REACTION CONTROL SYS "( 143.62)
D-18
JSC-28098
TOTAL FOR PROPULSION ( 143.62)
4. POWER
BATTERIES 102.26
BATTERY MOUNTING 12.38
RELAY PANELS 13.62
DIODE PANEL 0.8
POWER/CONTROL CIRCUITRY 67.8NOSE FAIRING SEP CIRCUITRY 2.36
RENDEZVOUS & RECOVERY SEP CIRC 8.84
ADAPTER SEPARATION CIRCUITRY 17.32BOOSTER SEPARATION CIRCUITRY 2.8
MOUNTING & INSTALLATION, MISC 9.12
TOTAL FOR ELECTRICAL POWER SYS ( 237.3)
TOTAL FOR POWER ( 237.3)
6. AVIONICS
PACKAGE 17.42
INVERTER 6.58
RATE GYROS 8.54
TOTAL FOR ATTITUDE CNTRL ELECT ( 32.54)COMPUTER 58.89
PLATFORM 33.2PLATFORM ELECTRONICS 39.75
POWER SUPPLY 47.9
AUXILIARY POWER SUPPLY 3.9
COMPUTER COLDPLATE 7.21
DISPLAY I/O 4.1
TOTAL FOR INERTIAL GUIDANCE ( 194.95)HORIZON SENSORS 22.02
TOTAL FOR HORIZON SENSORS ( 22.02)MOUNTING & INSTALLATION 10.83
TOTAL FOR MOUNTING & INSTALLAT ( 10.83)CIRCUITRY 44.2
TOTAL FOR CIRCUITRY ( 44.2)TAPE RECORDER 13.83
CAMERAS 11.27
TAPE CARTRIDGES 4.74
TRANSMITTERS (2) 5.04
MULTIPLEXERS 5.79
PCM PROGRAMMER 20.06
POWER CONVERTER/REGULATOR 13.92
DATA COND INSTR PKGS 12.04
SENSORS 12.86
BIO-MEDICAL 10.06
MOUNTINGS 2.86
CIRCUITRY 75.44
TOTAL FOR INSTRUMENTATION ( 187.91)MULTIPLEXING/SWITCHING 4.72UHF VOICE 6.26
C-BAND BEACON 10.67
VOICE CONTROL CENTER 6.29
MOUNTING 0.63
ANTENNAS 2.61
CIRCUITRY 28.89
TOTAL FOR COMMUNICATION ( 60.07)
TOTAL FOR AVIONICS ( 552.52)
7. ENVIRONMENT
D-19
JSC-26098
ENVIRONMENT INDICATOS 5.39
CIRCUITRY 26.15
ELECTRICAL INDICATORS 1.98
PROPULSION INDICATORS 6.33
RENDEZVOUS INDICATORS 5.21
TIME REFERENCE INDICATORS 11.73
FLIGHT DIRECTOR(ATTITUDE CNTR) 24.17WARNING LIGHTS 6.12
PITOT STATIC SYSTEM 3.01
TOTAL FOR DISPLAYS ( 90.09)
EJECTION SEATS (2) 141.73EJECTION SEAT NON-PERSONAL KIT 103.58
EJECTION SEAT BACKBOARD 33.04
EJECTION SEAT BALLAST 34.43
EJECTION SEAT PYROTECHNICS 7.22
EJECTION SEAT CATAPULT 56.76
EGRESS KIT 50.3
SEAT BACKUP STRUCTURE 46.46
CIRCUITRY 3.26
CABIN INSULATION 13.63FOOD STORAGE 14.7
WATER MANAGEMENT 15.WASTE FACILITIES 10.6
CABIN LIGHTING 1.79
SUIT HOSE EXTENSION KIT 3.45
NAVIGATION AIDS 7.72EXTRA VEHICULARACTIVITY 61.67
TOTAL FOR CREW SYSTEMS (605.3399)PRESSURE BREATHING VALVING 7.47
COMPRESSORS 9.14
POWER SUPPLIES, COMPRESSOR 8.62CONTROLS 13.29
PRESS BREATHING MOUNTING/INSTA 7.12SOLIDS TRAP 1.08
CARBON DIOXIDE ABSORBER 54.71
RENOVATING SYSTEM VALVING 10.67
DUCTS 18.37
MOUNTING, CO2 ABSORBER 6.98CABIN HEAT EXCHANGER 12.85
SUIT HEAT EXCHANGER 18.82
CABIN FAN 1.35
HEAT EXCHANGER INSTL 0.73
COOLING FLUIDS 19.19COLD PLATES 27.68
FLUID LINES 13.36
COOLING SYSTEM VALVING 4.32
COOLING SYSTEM MOUNTING/INSTAL 1.5
POWER SUPPLIES, FAN 2.92SECONDARY OXYGEN SYSTEM TANKS 40.24
SECONDARY OXYGEN SYSTEM LINES 3.24
SECONDARY OXYGEN SYSTEM MOUNT 2.48
CIRCUITRY 13.85
TOTAL FOR ENVIRON CONTROL SYST ( 299.98)
SWITCHES 2.03
FUSES 10.51
CIRCUIT BREAKERS ii.58
PANELS & CONSOLES 36.86
TOTAL FOR PANELS & CONSOLES ( 60.98)
ABORT CONTROLS 1.67
0-20
JSC-26098
TOTAL FOR ABORT CONTROLS ( 1.67)MANUAL CONTROLS 5.29
TOTAL FOR MANUAL CONTROLS ( 5.29)LIGHTS 2.11
TOTAL FOR LIGHTS ( 2.11)
TOTAL FOR ENVIRONMENT ( 1065.46)
8. OTHER
RETROGRADE CIRCUITRY 6.86
TOTAL FOR RETROGRADE CIRcuITRY ( 6.86)MAIN CHUTE 111.94
MAIN BRIDLE 7.6
MAIN CONTAINER 10.7
MAIN STRUCTURAL RING/HUB 19.79
MAIN CIRCUITRY 6.86
PILOT CHUTE 13.19
PILOT CHUTE INSTALLATION 6.61
DROGUE CHUTE 13.54
DROGUE CHUTE INSTALLATION 7.67
PILOT/DROGUE CIRCUITRY 11.17
TOTAL FOR LANDING SYSTEM ( 209.07)RECOVERY LIGHT 3.05
HF VOICE 12.74
RESCUE BEACON 4.49DYE MARKER 1 25
STRUCTURAL MOUNTING 1 25
CIRCUITRY 6 55
TOTAL FOR RECOVERY SYSTEM ( 29 33)PROPULSION CIRCUITRY 6 15
DOCKING STRUCTURE/MECHANISM 14 32
DOCKING CONTROL 6.15
DOCKING CIRCUITRY 10.22
RADAR ELECTRONICS 74.31
ELECTRONIC CIRCUITRY 3.65
TOTAL FOR RENDEZVOUS ( i14.8)ACTUAL WTADJUSTMENT -7.
TOTAL FOR ACTUAL WT ADJUSTMENT ( -7.)
TOTAL FOR OTHER ( 353.06)
i0. NON-CARGO
CREW EQUIP STORAGE 5.
TOTAL FOR CREW EQUIP STORAGE ( 5.)CREW (2 IN SUITS) 416.
TOTAL FOR CREW (2 IN SUITS) ( 416.)BALLAST (CG OFFSET) 148.
TOTAL FOR BALLAST (CG OFFSET) ( 148.)
TOTAL FOR NON-CARGO ( 569. )
ii. CARGO
EXPERIMENTS 27.
TOTAL FOR EXPERIMENTS ( 27.)
TOTAL FOR CARGO ( 27.)
12. NON-PROPELLANT
FOOD 5.
TOTAL FOR FOOD ( 5.)WATER (CREW) 15.
TOTAL FOR WATER (CREW) ( 15.)OXYGEN (CREW-SECONDARY) 14.
D-21
JSC-26098
TOTAL FOR OXYGEN (CREW-SEC) ( 14.)
N2 GAS (RCS) 3.
TOTAL FOR N2 GAS (RCS) ( 3.)
TOTAL FOR NON-PROPELLANT ( 37.)
13. PROPELLANT
FUEL 32.
OXIDIZER 40.
TOTAL FOR RCS ( 72.)TOTAL FOR PROPELLANT ( 72.)
GROSS VEHICLE WEIGHT 4860.851
D-22
NOTE:ALL"ASS HA S UHHARY OAT POINTIS IN POUNDS. GEMINI ADAPTER SECTION (l dUN 65)
...._.,...._ff_._B_....................................._..........._e._.......%..._._E.R..............................................(..........._.Z....e_....g._ER.............................................(..........3.S8...
...........$._.I.B...R_I.RO...._ECI.I_B.............................I._..............BA.I.IE.RY......................................................_.5_...............RE._R.Q_R.ADE...5.E_.TE.U...............!............_6._...
..........._IB...EQU.I._E_...S.E.C..........................._._...............EUEL..._.EL.L......................................................_.............8.CT.UBL...W.E.LGU_...B.QJ.U._.......i................3....
...........S._._.EEE.NE._....R.E_.R_..............................29............RQH£R..._.LR_._.I.!_Y... 31.......... i ........
............S%IEEEB.EE._,....£gU.Lff..............................H._ ...........B.Q_P.IE.R..$.EP._B.TI.QH..._L_..i...............1.6........................................................................i......................
...........R.I_G_,...._.LI.EEEB.I.NG..............................@_..............BDO_.E_.._E._8.R_.I.Q._...C.I.R...................9........................................................................i.....................SP_Iq._.RI_S ..........................................._._..............E_E.R.LqL._.LGU._._......................................_..
...........$.E_B_B.II._..._R.Q_.....................L..............6.1..............BLB._I..._.UI.ELD..._Q.UHI..........................._..."....................................................................9, GROWTH _............._......
.........._P.O_._.,...._gU.L_...B.CC.E_S........................R._...............C._$.S...B_.A._.._S.S.¥.._Q.q_%...................._.e.......................BRY....h.R.SS..........................i........_!._B....
...........U._QL.._._U.G._............................>................_..............OE._.!._.._QU_._.............. Zl ,
.........._Q.U.I._E._I..._U_._ ....... i _Q 5. CONTROL - 18. NON-CARGO ( -
FRIRINGS
.....................................................................PAINT i.............. 3.?... .................................................................................................................................................................................................8.IIBgH...HB_D_B.RE.....................L................5.............................................................................................................................................................................................
:
THERMRL CURTAIN ! 11 _ COMMUNICATIONS 38 EXPERIMENTS 1_.!
.....................................................................i.................................._._._U._E._._._.tO_................................_._.e.........................!.NE.R.T....MRSS............................._._o.........................................................................i...............................................................................................................................................................................................................
................... 88.....................................................................i...................................................................................................................12...U._N_R.O_E_.eU._................................................................................................................_................................................................................................................................wB.!E.R..._..CR.E_...._R._.U._._._...................._.@...
...........Q_Y.GE.N...E._R.E_..._R._UA_._...................5H.......S_..._.Rq_.S.I.gN................................._..........._.e?..................................................................................................UF._.L_...G_.S...<.£_.M_..)............ 4.............[BRU.$.TE.RLAB.,...._ZG..._9...................I._.B...........................................................................................................{..Q@._....I,$...O.RBLT...BUD............................................_._EBA...S_S..._.BU.K......................._..............aZ.............................................................................................................UB._EU_E._.I.UG....S_.S.,..)...............i................................._E_.S..._._...YO.L_._.U_...............................!.5......................................................................................................................................................................................................g._.I.Q.I.Z_..._._...I@.B_.............................I._....?. ENVIRONMENT ( _ 13. PROPELLANT ( _8_......................................................................C.......................................................................................:...................
..........Q_.ID.IZE._..._$..._.BLY.I.B.G.......:................._..............ERE$._£...B_.UI._G .............i.............._.L...............Q._M.$..E.UE.L...................................i..........._.LB...
...........E._..._._..._.BHK.S......................._.............._.!................CQ.OLINGSYSTEM 192 ............OR MS...OX.I.D.I.Z.E.R.........................L...........3_._...
..........E_EL..._.$...Y_L_I._.................i................._..............B.L_.T..._BIELQ............................................1.6.........................................................................i......................
..........._._E.E..._B.L.YE._.......................L................?................C.I.R_PI_R_..... _9.........................................................................L....................LPROPEL QURNTITY SYS i 21 flOUNTING STRUCT i 17 ..................................................................... i ..................... _
...........C.I_UI.TR.Y....................................._.............._ ..............HB._.ER._B_K_E_ i........._....................................................................................................E$.LE._._RQU.[_$............................i................._ .............._E._..._Y.$._E._ ............................i.................6...
BLAST SHLD 29, BERM 15 _ HH STRUCT PROV, EVR i 2 GRO_ _ 289?
M_IINTING _N_ IN_TI : fil ,GEM MP03 CCSD WH 9 NOV 9_
JSC-£6098GEMINI ADAPTER MODULE
DESIGN MASS SUMMARY (JSC FORMAT)ALL MASS IN POUNDS
i. STRUCTURE
RETRO SECTION 18.68
EQUIPMENT SECTION 35.01
TOTAL FOR SKIN ( 53.69)PANELS/RADIATORS, RETRO 29.13
PANELS/RADIATORS, EQUIPMENT 46.32
TOTAL FOR STIFFENERS ( 75.45)RINGS, STIFFENING 62.92
TOTAL FOR RINGS, STIFFENING ( 62.92) ,RETRO TO EQUIPMENT SECTION 14.17
ADAPTER TO BOOSTER 21.7
REENTRY MODULE TO ADAPTER 6.96
TOTAL FOR RINGS, SPLICE ( 42.83)BOOSTER TO ADAPTER 18.26
RETRO TO EQUIP SECTION 19.6
REENTRY MODULE TO ADAPTER 21.05
SPRING CARTRIDGE 2.01
TOTAL FOR SEPARATION PROVISION ( 60.92)DOORS, EQUIP ACCESS 27.42
TOTAL FOR DOORS, EQUIP ACCESS ( 27.42)MISCL STRUCT DETAILS 4.58
TOTAL FOR MISCL STRUCT DETAILS ( 4.58)EQUIPMENT SUPPORTS 20.
TOTAL FOR EQUIPMENT SUPPORTS ( 20.)FAIRINGS 17.05
TOTAL FOR FAIRINGS ( 17.05)PAINT 36.56
TOTAL FOR PAINT ( 36.56)ATTACHING HARDWARE 5.24
TOTAL FOR ATTACHING HARDWARE ( 5.24)
TOTAL FOR STRUCTURE ( 406.66)
2. PROTECTION
THERMAL CURTAIN 10.8
TOTAL FOR THERMAL CURTAIN ( 10.8)
TOTAL FOR PROTECTION ( 10.8)
3. PROPULSION
THRUSTERS 98.56
THRUSTER MOUNTING 49.33
PRESSURE TANK 37.12
PRESSURE VALVING 15.04
OXIDIZER TANKS 18.48
OXIDIZER VALVES 2.25
FUEL TANKS 21.26
FUEL VALVES 2.23
SHUTOFF VALVES 7.24
PROPEL QUANTITY SYSTEM 21.06CICUITRY 23.08
OAMS ELECTRONICS 7.4
BLAST SHIELD 28.99
CROSS BEAM 14.73
MOUNTING & INSTALLATION 60.85
TOTAL FOR ORBIT ATT & MANEUVER ( 407.62)TOTAL FOR PROPULSION ( 407.62)
D-24
JSC-260984. POWER
BATTERY 351.93
FUEL CELL 0.74
POWER CIRCUITRY 31.02
ADAPTER SEPARATION CIRCUITRY 16.06
BOOSTER SEPARATION CIRCUITRY 4.2
EXTERIOR LIGHTS 1.82
BLAST SHIELD 25.11
CROSS BEAM ASSEMBLY 20.08
DETAILS 20.55
TOTAL FOR ELECTRICAL POWER SYS ( 471.51)
TOTAL FOR POWER ( 471.51)
6. AVIONICS
HF VOICE 7.3
C BAND BEACON 10.66ACQUISITION AID TRANSMITTER 1.02
MULTIPLEXING/SWITCHING 0.49UHF EXTENDABLE ANTENNA 0.8
MOUNTING 2.62
CIRCUITRY 7.12
TOTAL FOR COMMUNICATIONS ( 30.01)TRANSMITTER 2.52
MULTIPLEXING/SWITCHING 6.97COMMAND SYSTEM 21.97
INSTRUMENTATION PACKAGES 4.38
SENSORS 4.04
BLAST SHIELD 14.88STRUCTURAL MOUNTING 13.55
CIRCUITRY 39.7
TOTAL FOR INSTRUMENTATION ( 108.01)
TOTAL FOR AVIONICS ( 138.02)
7. ENVIRONMENT
PRESSURE BREATHING BOTTLE 42.19
PRESSURE BREATHING VALVING 2.79
PRESS BREATHING LINES/DUCTING 5.85HEAT EXCHANGERS 34.6
COOLING FLUID 38.36
LAUNCH COOLANT WATER 7.
PUMPS 49.22
COLD PLATES 14.6
LINES AND CLAMPS 22.47
VALVING 10.26
COOLANT RESERVOIR 12.34
INSTALLATION DETAILS 2.91
BLAST SHIELD 16.39CICUITRY 13.63
STRUCTURAL MOUNTING 17.34
TOTAL FOR ENVIRON CONTROL SYS ( 289.95)WATER TANK (CREW) 7.29WATER MANAGEMENT SYSTEM 6.07
EVA STRUCTURAL PROVISIONS 2.01
TOTAL FOR CREW SYSTEMS ( 15.37)
TOTAL FOR ENVIRONMENT ( 305.32)
8. OTHER
CASE 43.84
D-25
JSC-£6098PROPELLANT 222,48IGNITORS 3.28
TRUSS 27.89ATTACH FITTINGS 9.93
CIRCUITRY 11.67
BLAST SHIELD 28.81
MISCL ATTACHMENTS 3.85
SHRAPNEL PROTECTION 13.25
TOTAL FOR RETROGRADE SYSTEM ( 365.)ACTUAL WT ADJUSTMENT 3.39
TOTAL FOR ACTUAL WT ADJUSTMENT ( 3.39)
TOTAL FOR OTHER ( 368.39)
Ii. CARGO
EXPERIMENTS 12.
TOTAL FOR EXPERIMENTS ( 12.)
TOTAL FOR CARGO ( 12.)
12. NON-PROPELLANT
WATER (CREW PRIMARY) 30.
TOTAL FOR WATER (CREW PRIMARY) ( 30.)OXYGEN(CREW PRIMARY) 54.
TOTAL FOR OXYGEN(CREW PRIMARY) ( 54.)HELIUM GAS (OAMS) 4.
TOTAL FOR HELIUM GAS (OAMS) ( 4.)
TOTAL FOR NON-PROPELLANT ( 88.)
13. PROPELLANT
OAMS FUEL 310.
TOTAL FOR OAMS FUEL ( 310.)OAMS OXIDIZER 379.
TOTAL FOR OAMS OXIDIZER ( 379.)
TOTAL FOR PROPELLANT ( 689.)
GROSS VEHICLE WEIGHT 2897.32
D-26
CENXN_ SPACECRAFT
<-_--- ADAPTER_ SECTION<< REENTRY MODULE
RENDEZVOUS e--- --9 RETRO- _----EQUIPMENT q_ RORPTER
AND < CRBIN ) GRROE I SECTION MATING
RECOVERY (8eCUPTPRESSURIZEO) SECTION SECTIONSECTION 90.000
/_RCS \ 120.000
0 _ SECTION _I
O0 144.46R|
II
N IDO ,I REFERENCE:I ! PROJECTO0 l
I GEMIMI
J k I ACTUAL
!/ WEIGHTl
/ REPORT,<----37.71 9.5@ / SPACECRAFT
LL_ NO. ll,I
I I i AIRCRAFT,MCDONNELL
INCHES B909-11,
< 134 68 < 35.26 =< 53.20--_| PAGE 3,• 29 APR 1966.
•< 169 94 _ 2. o
< 225.74 mm
z 238.18 I NOTE•" ALL DIMENSIONS RRE IN INCHES. z13.44 m°I GEMIDROl CCSO WH 24 RUG 93
NOTE:riLLMRSS DATA. POI,T OESIGH HnSS SUHH RYIS IN POUNDS. _ APOLLO SPACECRAFT (I MAR 71 ) SPACECRAFT I18, MISSION J1
FUHCTIOHRLSYSTEH CODE R B C D P.IMBR_ REFERENCE: RPOLLO FIGURE 2-3, APOLLO SPACECRAFT
SPACECRAFT OPERATIONAL REFERENCE DIMENSIONS,
DRTR BOOK, SNR-B-D-B2?(I), IS APRIL 1971.
, !,.....S.T...R..U..CT.U.R.E........................L:_!6........!e_ ........3_:_ .......:_i_ REVIS,O,3. AME,OMENTE,,
400.7 _ _ 2"t8. S"-------_
,.._..:...P.I_..O.!.EC.T.._.O.I_. ................... ],._0.6 ........ 37.:_{_ ........... 5.ui'.. I_. ......... _.5_. ' LRUNCH ESCRPE SYSTEM SERVICE MOOULE I(LES) (SM)....................................................................' .................' .................................... I * 336.0
. .3..:....p.R...Q.P.U.L..S...[.ON........... _.;_?.e.........._.95....... 3_._ ........._....... ! I33.s :: _ _.ls4.e0 BPACECRAFT
.......................................................................................................................... COMMRND_.MODULE .._ LUNAR MODULE ADAPTER.L4. POIJER 6? 1414 ...... _{_4.._.: _} ..........
..................................................................................6. RVIONICS - ....... 93_ 4_.8 .......... - ....... --+--
................................................. i ............................ "'_. I ( Ltl ).................................... _ o 00 _"_ ' DES [ GN :
:................................................. °.................. _................. ' ................................... _ "-7 XS200.0.8..-...'.0.T..H..E..1_............... _,_2.5 ....... _-,_,92........... 95.9 .......... 5._8,. e lee XR1133.S
INCHES XC133.5 _-_l S_. O--a................................................o..................o .................i....................................
,..9.......G.IRO.W.l"N , - , - ............ - -:I_ i NOTE: ALL DIMENSIONS XR1000o0
..............D.R.Y,..fffi.SS....................5.97.6.....1.1.2.3_......1.060._.........40.66.. _E _N_NCHES. xce.e ' _.e'¢- 98_.2 )
.I._ .L,. N Q.._.-.,.C .O.R G.g ..........................- ..............!._.54 ...........93.3 ...........F ....... XA]484,e APOLLO SPACECRAFT XA502.0
RPOLDReI CCSO WH 14 AUG 8S................................................. 0.................. t ......................................................
!..L.....C.B..R...Gg....................................-.................3e5............._. -HOT.E:.
.............. 597G. 'I" I "I'INE_.T.._S_ .....................!.z.7._.9......!.I.5.ge........H.oG.G. A. LAUNCH ESCAPE SYSTEM (LES)B. COMMAND MODULE ( CM )
.1.2.,...._.0.U.-.E.R.p.EE._.kA.U.T.............-.................._._.........9.99...........-=..............c.,......sE.R.Y.!.C.E....M...O.P..U._.E..._..__.._........................................................................................O. SPACECRRFT LUNAR MODULE ADAPTER (SLR)
.!.3.,....PR.p.pE.L.L.R.N.T...................._.!.9_..........._0.9....._.!9.!0..........-........................£DE..S..I.G.HEq...T.O.Cg.U.TR.I.U...L.U.HA.R...M.qD.ULE...(.._M.).)
............. ,...... CM SM SLR
................_R.O.SS..HR.S.S..............9.L?..3.....I..9.056......5.4.H.99........._.06.6............_.E.S.I._.H-.E..N._.EL.Q.P..E..V.Q_.U.ME._...V_._.(.c.u...E.T..>........................55_....1.S._O.6.5H.0_(80?94) , _ PRESSURIZED VOLUME Vp_(CU FT) o366.......................................................................................................................................................................................................................................... 0 ..........
............LM........3._.23.6.......................................................................................OES.!G.t4=E.t_YEL_E_.._._R.E...f3RES..,Rao(.S.q..ET)...............377.....6t3 15L5 mmI 1.?..0_.e .......................................................................a o
DESIGN MISSION, 11 DAYS MAX_ CREW OF THREE. SIDEWALL OHLY. O0APOLMPO1 CCSD WH 20 RUG 93
NOTE: ALL MASS HA_ _U_H_RY DRTR POIHT
SPACECRAFT 112IS IN POUNDS. APOLLO LAUNCH ESCAPE SYSTEM (LES), I MAR ?1 MISSION Jl
I. STRUCTURE ( ....|.3.I.G.._....4._...._._.R.............................................._............_..: .....................................................................(........1"225"'_......................................................................"......................_............................................................................................_ 8. OTHER
CANARD SECT FIXED STR ...........5_ ELEC_|_L "B_O_R_ ............._ .............Q...B._L.L.........................................................._5....CANARD FITTINGS . ..............................................................................................PYRO INITIATORS !SKIRT ...........B._L.LB._.T..................................................LI._5..................................................................I._B.................................................................................................SKIRT FITTINGS ...........................................................................................
TOWER STRUCTURE eOG .................................................................................................................................................................._............./................T'OWER"'F'I'TTING'S.............................................. 9. GROWTH
MISCL ATTACH 21 DRY _fl$S i 597GSECONDARY STRUCTURE .............._.9......................................................................................................................................................................k...................Z......................................................................5. CONTROL 10, NON-CARGD {..............................k B_...........................................................................................
CANARD ACTUATOR MECHN 8_
_:.._.V_;._._._._._:9.._._._.:_.._._...:_.:.._.._;:._._........_....;_..._.._.._...._._._.o_e..._._.....................................................................(.............z........iiT_A_g6.............................................._............._........e.AV.!._N.[_.......................................................................................................................................................o ...........kN._.AZkO._.....................................................................................................................................................
SK._R!................... _e .......................................................................................! NER.T....MRS6 _i _sze..'..TOWER ............i._._...
COMMAND MODULE 889 12_....U.q_._._._U._ ....................................._.....
................___T_R_T__ .............i.......................'.'..".".'.'.'".'.".".'.'...'..'.."."Z......'..'.'.'.".'.".".'..Z.i...."._".".".............................................................................................
......................................................................!z....................I ............................................................................................
3. PROPULSION 2e78 ......................................................................................................................................................................................
• PITCH MOTOR EXPEND.E _..........._I ........................................................................................................................................................................................JETTISOH MOTOR . _B .............................................................................................ESCAPE MOTOR EXPENDED IS?9 ......................................................
........................................................................._';'"'_fi_'i'R_'_'_.............................._............_......_ _P_LC_T _ _is_......................................................................................................R.I.T.CH..._P.ZP.R...............................................E.
....................................................................................................................................................................................................E._EQP.E..U.QI.Q_..........................._........_1._&..
.....................................................................:............................................................................................i...........................................................................................!....................: i I
.....................................................................r.........................................................................................._............................................................................................_...................
: : GROSS _RSS : S173 o..............................................................._..........................................................................................:............................................................................................!....................
APOLMP02 CCSD NH 9 NOV 92
APOLLO LAUNCH ESCAPE SYSTEM JSC-26098
DESIGN MASS SUMMARY (JSC FORMAT)ALL MASS IN POUNDS
i. STRUCTURE
FITTINGS AND ATTACH PARTS 4.2
CANARD SURFACES 239.6
CANARD SECTION-FIXED STRUCTURE 525.6
TOTAL FOR BASIC BODY STRUC-FWD ( 769.4)FITTINGS AND ATTACH PARTS 0.5
TOTAL FOR BASIC BODY STRUC-CTR ( 0.5)FITTINGS AND ATTACH PARTS 13.
ESCAPE MOTOR SKIRT-SKINS 49.5
ESCAPE MOTOR SKIRT-FRAMES 146.8
ESCAPE MOTOR SKIRT-FITTINGS 12.TOWER STRUCTURE 206.
TOWER FITTINGS 69.8
MISC AND ATTACH 21.1
TOTAL FOR BASIC BODY STRUC-AFT ( 518.2)BALLAST INSTALLATION PROVISION 29.2
TOTAL FOR SECONDARY STRUCTURE ( 29.2)
TOTAL FOR STRUCTURE ( 1317.3)
2. PROTECTION
ESCAPE MOTOR SKIRT INSULATION 9.5
TOWER INSULATION 106.6
C/M BOOST PROTECTION COVER INS 889.6TOTAL FOR INSULATION ( 1005.7)
TOTAL FOR PROTECTION ( 1005.7)
3. PROPULSION
PITCH MOTOR EXPENDED 40.6
JETTISON MOTOR 557.8
ESCAPE MOTOR EXPENDED 1678.5
TOTAL FOR ENGINE SYSTEM ( 2276.9)
TOTAL FOR PROPULSION ( 2276.9)
4. POWER
ELECTRICAL TRANSMISSION 43.4
INSTALLATION HARDWARE 23.6
TOTAL FOR ELECTRICAL POWER SYS ( 67.)
TOTAL FOR POWER ( 67.)
5. CONTROL
CANARD ACTUATING MECHANISM 83.7
TOTAL FOR SYSTEM ACTUATION ( 83.7)
TOTAL FOR CONTROL ( 83.7)
8. OTHER
TOWER-COMMAND MODULE SEPARATIO 4.
PYROTECHNICS 40.
TOTAL FOR ORDNANCE & SEPAR SYS ( 44.)
Q-BALL 25.PYROTECHNIC INITIATORS I.
TOTAL FOR GOV FURNISHED EQUIP ( 26.)
BALLAST 1155.
TOTAL FOR BALLAST ( 1155.)
TOTAL FOR OTHER ( 1225.)
D-30
JSC-26098
13. PROPELLANTPITCH MOTOR 9.ESCAPE MOTOR 3188.
TOTAL FOR PROPELLANT - SOLID ( 3197.)TOTAL FOR PROPELLANT ( 3197.)
GROSS VEHICLE WEIGHT 9172.601
D-31
NOTE:ALLMASS HNS_ _UHHnRY D_nK._PO_N_SPACECRAFTlieIS IN POUNDS. RPOLLO COMMAND MODULE (CM), ] MAR 7] _ MISSION J1
.....................................................................1. STRUCTURE (.........i8_g"-q'/FSfi_ .............................................( .........i'qi_' ......................................................................8. OTHER (............. _e_
..........e._.t,_R._..._.D_..._._................................................._.E.C_.R...e_LS.X_..._.._._._...............1._.!._......................._.i.._._._......._.{;......._._._._......_._......_..i.._._..........=_.3.FORWARD SECTION i 245 BALLAST i 163CENTER SECTION i 735 ................................................. ORDINRNCE RNO SEPRRR : 35AFT SECTION i 287 DOCKING PROV . 29B
..................................................................... '............................................................................................................................ EARTH"iMPACYAN6RE'c'6v{ ............ 2{_ISECONDARY BODY STRU i 62B ..........................................:
ALEM STRUCT DELTA : 7 EARTH LANDING SYST _ 679..................................................................... ;........................................................................................... !...................... S, GROWTH......................................................................_................................................................................................................. DRY MflSS i 1123_
..........................................................................................."....................'Te;NBN:__co...................................._.........i_sq..................................................................... 5 CONTROL 7
.7.............................7......_........._....._................................._._....._. _. .__. .. . . ..... ..........7..."...........!. . cRE. _oCREW EQUIP _SH
...................................................................... _............................................................................................ :...................... MISCL EQ 11_ RLEM 69 80i ...........................................................................................
..................................................................... _............................................................................................ :....................... ECS RESIDUALS 169
.....................................................................!............................................................................................;......................RCS RESIDUALS 37
...................................................................._.............3738 '......................................................................................................................................6. AViBNI_S _ 93q 11. CARGO (RETURN) '.....................3052, PROTECTION ....................................................................,..............................................................................................................
HEAT SHIELD SUBSTRUC , STABILIZATION AND CONT_ 202I FORWARD SECTION 177 INSTRUMENTRTION 3? INERT _RSS 12793
CENTER SECTION 1131 COMMUNICATIONS 302 ...... Z ......................._.............'--"5_m ...................................................................................................................................................................:........................ie_NBH_'RS_ELC_N_ ;AFT SECTION 787 ......................i.............5_..RBLRTOR MATERIAL IH?2 GUID, NRV, RND CONTR 393 WATER (OSRBL_)
INSULRTION _ ...................................................................... ,..................................................................................................................
.............................................................................................!ill...........i_E¥"E__Ti"'s'_'{2_gTI.....egs .........
: ?. ENVIRONMENT 17_9 ..................................................................... _.....................
.........._....''....'...'.........._......'...._......'._..'...'....................................'._'''._'._.'..._..'.........i._....._.'.............................CREW SYSTEMS 9_8 19. PROPELLANT _ _0_ENVIRON CONTR SYS (ECS 5?3 RCS
...................................................................... :...................... 289 USABLE.................................................................................................................................CREW COUCH _OB........................................................................r.....................(UNITIZED_ RTTENUR- UNUSABLE 0
TION 111 LB IS IN L
CODE 8.B (ERRTHIMPACT SYSTEM.) i I
LIGHTING , 21 :CONTROLS AND PANELS : 363 GROS_ hR_S 1305G 0
....................................................................!............................................................................................_................................................iDISPLRYS , 55
RPOLMP03 CCSO WH 9 NOV 92
APOLLO COMMAND MODULE JSC-26098
DESIGN MASS SUMMARY (JSC FORMAT)ALL MASS IN POUNDS
i. STRUCTURE
HONEYCOMB PANELS 60.4
LONGERONS 2.4
FRAMES AND RINGS 64.7
WINDOWS,HATCHES,ACC DOORS&FRAM 0.9MECHANISMS 33.3
BODY TO HEAT SHIELD ATTACH 0.5
FITTINGS AND ATTACH PARTS 82.6
TOTAL FOR BASIC BODY STRUC-FWD ( 244.8)HONEYCOMB PANELS 259.1LONGERONS 112.4
FRAMES AND RINGS 150.2
WINDOWS,HATCHES,ACC DOORS&FRAM 96.3
BODY TO HEAT SHIELD ATTACH 54.2
FITTINGS AND ATTACH PARTS 63.
TOTAL FOR BASIC BODY STRUC-CTR ( 735.2)HONEYCOMB PANELS 126.
FRAMES AND RINGS 77.9
BODY TO HEAT SHIELD ATTACH 2.6
FITTINGS AND ATTACH PARTS 0.I
TOTAL FOR BASIC BODY STRUC-AFT ( 206.6)RH EQUIPMENT BAY 130.9
LH EQUIPMENT BAY 131.6
FORWARD LH EQUIPMENT BAY 25.1
FORWARD RH EQUIPMENT BAY 41.9
MAIN DISPLAY PANEL 37.4
LOWER EQUIPMENT BAY 184.7
FORWARD COMPARTMENTAREA 5.
AFT EQUIPMENT BAY 22.5AFT COMPT AREA WIRE SUPPORTS 7.9
AFT COMPT AREA EQUIP SUPPORTS 39.
TOTAL FOR SECONDARY STRUCTURE ( 626.)ALEM STRUCTURE PROVISIONS DELT 6.8
TOTAL FOR ALEM STRUCTURES DELT ( 6.8)
TOTAL FOR STRUCTURE ( 1819.4)
2. PROTECTION
HONEYCOMB PANELS 67.7
FRAMES AND RINGS 27.9
ACCESS DOORS 0.i
FITTINGS AND ATTACH PARTS 42.6
WINDOWS AND MATCH COVERS 37.9
CLOSEOUTS 0.8
TOTAL FOR HEAT SHIELD SUB-FWD ( 177.)HONEYCOMB PANELS 243.8
FRAMES AND RINGS 124.1
ACCESS DOORS 340.6
BODY STRUCTURE TO HS ATTACH 120.7FITTINGS AND ATTACH PARTS 97.8
WINDOWS AND HATCH COVERS 64.8
MECHANISMS 91.
CLOSEOUTS 20.9
AIR VENT 27.7
TOTAL FOR HEAT SHIELD SUB-CTR ( 1131.4)HONEYCOMB PANELS 556.6
D-33
JSC-£6098
FRAMES AND RINGS 55.8BODY STRUCTURE TO HS ATTACH 50.4
FITTINGS AND ATTACH PARTS 66.
WINDOWS AND HATCH COVERS 0.3
CLOSEOUTS 7.1
TOROIDAL ASSEMBLY 50.6
TOTAL FOR HEAT SHIELD SUB-AFT (786.7999)FORWARD SECTION ABLATOR 135.3
CENTER SECTION ABLATOR 407.5
AFT SECTION ABLATOR 929.6
TOTAL FOR ABLATORMATERIAL ( 1472.4)FORWARD SECTION INSULATION 17.6
CENTER SECTION INSULATION 83.
AFT SECTION INSULATION 62.8
TOTAL FOR INSULATION ( 163.4)
TOTAL FOR PROTECTION ( 3731.)
3. PROPULSION
TANKS AND EXPULSION FUEL 13.4
PLUMBING AND FITTINGS FUEL 19.6
VALVES AND REGULATORS FUEL 10.5SUPPORTS FUEL 5.6
TANKS AND EXPULSION OXID 14.8
PLUMBING AND FITTINGS OXID 20.
VALVES AND REGULATORS OXID 10.5
SUPPORTS OXID 7.7
TANKS PRESS 10.2
PLUMBING AND FITTINGS PRESS 7.5
VALVES AND REGULATORS PRESS 22.4
SUPPORTS PRESS 7.1
ENGINES 97.2
ENGINE SUPPORTS 1.3
ENGINE NOZZLE INSERTS 47.
TOTAL FOR REACTION CONTROL SYS ( 294.8)
TOTAL FOR PROPULSION ( 294.8)
4. POWERBATTERY-ENTRY ENERGY SOURCE 56.6
BATTERY-POST LAND ENERGY SOURC 28.3
BATTERY-PYROTECH ENERGY SOURCE 5.2
PLUMBING-ENERGY SOURCE 1.6
EQUIPMENT SUPPORTS i.INVERTERS-POWER CONVERSION 157.5
BATTERY CHARGER-POWER CONVERS 4.6
DC POWER PANEL 8.6
AC POWER BOX i0.BATTERY CIRCUIT BREAKER PANEL 4.7
ELECTRICAL POWER CIRC BKR PNL 3.2UPRIGHTING SYSTEM 9.5
TERMINAL DISTRIBUTION PANELS 18.6
SUPPORTS AND INSTALLATION PROV 1.5
ELECTRICAL HARNESS INST 729.7
LOWER EQUIP BAY MOTOR SWITCHES 6.8CIRCUIT INTERRUPTORS 30.5
RCS CONTROLLER 26.4
SUPPORTS AND INSTALLATION PROV 131.1
JUNCTION BOX ASSEMBLY 7.8
MASTER EVENT SEQUENCE CONTROL 113.4PYRO CONTINUITY BOX 10.8
D-34
JSC,26098SUPPORTS AND HARDWARE 3.5CONTROLLER-POST LANDING VENT 3.5
ALEM EPS DELTA 39.3
TOTAL FOR ELECTRICAL POWER SYS ( 1413.7)
TOTAL FOR POWER ( 1413.7)
6. AVIONICS
GYRO PACKAGE 45.
CONTROL ELECTRONICS 16.5
SERVO AMPLIFIER 12.4
DISPLAY ELECTRONICS 24.8
SOLENOID DRIVER AMPLIFIER 20.6
GYRO DISPLAY COUPLER 24.7
GYRO PACKAGE MOUNTING PLATE 4.6
DISPLAY AND CONTROLS 53.2
TOTAL FOR STABILIZATION&CONTRO ( 201.8)SIGNAL CONDITIONERS 7.7
ACCELEROMETERS 1.2
MISCELLANEOUS INSTRUMENTATION 14.8
TV CAMERA & LENS 0.3
IFTS & GSE ELECTRICAL PROVISIO 4.5
DATA DISTRIBUTION PANEL 3.4
INSTRUMENTATION SUPPORTS 4.9
TOTAL FOR INSTRUMENTATION ( 36.8)UNIFIED S-BAND 31.7
S-BAND POWER AMPLIFIER 31.7MULTIPLEXER 6.1
SIGNAL CONDITIONER 34.2
RECORDER 39.6
AUDIO CENTER 7.6
PREMODULATOR PROCESSOR 11.5
CENTRAL TIMER 6.6
UP DATA LINK 21.
VHF-AM TRANSMITTER-RECEIVER 13.5
RECOVERY BEACON 2.5
TRIPLEXER 1.6
PCM 42.1
HF/VHF RECOVERY ANT TRNSM LINE 11.4
2KMC HIGH GAIN ANT TRANS LINE 0.4
VHF OMNI ANT TRANS LINES&SW 2.8
2KMC OMNI ANT & TRANS LINES 28.1
VIDEO COAX & CONNECTORS 1.6
COMMUNICATIONS SUPPORTS i.
ALEM COMMUNICATIONS DELTA 7.3
TOTAL FOR COMMUNICATIONS ( 302.3)PIPA ELECTRONICS ASSY 8.5
SIGNAL CONDITIONER ASSY 5.8
COMPUTER KEYBOARD 36.
INDICATOR CONTROL PANEL 14.4BELLOWS ASSY 10.7
OPTICAL SUSBSYSTEM 60.7
OPTICAL SHROUD 3.4
OPTICAL EYEPIECE STORAGE ASSY 9.
ELECTRICAL PROVISIONS 25.4
NAVIGATION BASE 17.4
POWER SERVO ASSY 49.2
INERTIAL MEASUREMENT UNIT 45.2APOLLO GUIDANCE COMPUTER 70.7
COUPLING DATA UNIT 36.5
D-35
JSC-£6098TOTAL FOR GN&C ( 392.9)
TOTAL FOR AVIONICS (933.8001)
7. ENVIRONMENT
MASTER CAUTION LIGHTS 13.9
CAUTION AND WARNING SYSTEM 6.5
ENTRY MONITOR DISPLAY 21.3
G-METER 0.9
LAUNCH VEHICLE EDS 0.9
CAUTION & ABORT LT 0.5
BAROMETRIC INDICATOR 1.5
EVENT TIMER 1.5
SPS CHAMBER PRESS&ANGLE OF ATT 0.7
REACTION CONTROL DISPLAY 6.1
GMT READOUT i.I
TOTAL FOR DISPLAYS ( 54.9)
RESTRAINTASSY-REST STATION,CRE 10.3
DELIVERY ASSY-WATER,PERSONAL 5.LINES AND FITTINGS 5.5
WASTE BAGS 7.2WIRING-COMMON UTILITY 0.8
SUPPORTS 3.4
UMBILICAL-CREWMAN 28.2
ELECTRICAL UMBILICAL-PGA 16.6
MISCELLANEOUS 29.3
BODY MOUNTED MIRRORS 3.8
OPTICAL DOCKING AID 3.3
REMOVABLE ITEMS 200.8PERMANENT ITEMS 29.6
ALEM CREW SYSTEMS DELTA 104.2
TOTAL FOR CREW SYSTEMS ( 448.)
PRESSURE SUIT CIRCUIT CONTROLS 1.9
PRESSURE SUIT CIRC CO2 SENSOR 2.7
PRESSURE SUIT DUCTING,FITTINGS 9.4WATER GLYCOL CIRCUIT CONTROLS 1.7
WATER GLYCOL CIRCUIT PLUMBING 35.5
WATER GLYCOL 48.9
WATER GLYCOL CIRCUIT COLDPLATE 46.9
WATER GLYCOL SUPPORTS&HARDWARE 2.8
PRESS AND TEMPVALVES 4.3
PRESS AND TEMP DUCTING 1.8
PRESS AND TEMP PLUMBING 0.6
PRESS AND TEMP SUPPORTS&HARDWA 7.OXYGEN SUPPLY VALVES®ULATOR 3.
OXYGEN SUPPLY CONTROLS 1.4
OXYGEN SURGE TANK 8.9
OXYGEN SUPPLY EMERGENCY TANKS 12.6
OXYGEN SUPPLY PLUMBING 10.6
OXYGEN SUPPLY SUPPORTS&HARDWAR 16.1
WATER SUPPLY SYSTEM VALVES 0.3
WATER SUPPLY POTABLE WATER TNK 7.8WATER SUPPLY WASTE WATER TANK 10.9
WATER SUPPLY SYSTEM PLUMBING 6.8
WATER SUPPLY SUPPORTS&ATTCH 1.7
COMMON ITEMS LEM PRESS SYSTEM 6.5
COMMON ITEMS SUPPORTS 0.2WASTE MANAGEMENT WASTE DISPOSA 6.2
WASTE MANAGEMENT VALVES 3.4
WASTE MANAGEMENT LINES&FITTING 2.8
D-36
JSC-£6098WASTE MANAGEMENT LINES&FITTING 18.4
WASTE MGMT PLUMB INST HDWR 5.8
POST LAND VENTILATION SYSTEM 8.1
ENVIRONMENTAL CONTROL UNIT 170.6
OXYGEN CONTROL PANEL 14.3
WATER CONTROL PANEL 2.6
END ITEMS 81.2
ALEM ECS DELTA 9.4
TOTAL FOR ENVIRON CONTROL SYS ( 573.1)CREW COUCH UNITIZED 286.8
MANUAL CONTROLS AIR PRESS REG 2.9
TOTAL FOR MECHANICAL SUBSYSTEM ( 289.7)MODE SELECT FUNCTION-SWITCHES 3.1
CREW SAFETY CONTROLS 3.9
CONTROL STATION MOUNTING PANEL 26.8
CONTROL STATION MISC SWITCHES 2.7ECS GASES 7 CONTROL 8.4
HIGH GAIN ANTENNA CONTROL 1.8
CRYOGENIC CONTROLS 6.6
CENTER STATION MOUNTING PANEL 45.3
CENTER STATION MISC SWITCHES 5.
COMMUNICATIONS CONTROLS 6.6
POWER DISTRIBUTION CONTROLS 2.2
FUEL CELL CONTROLS 6.7
SERVICE PROPULSION CONTROLS 9.8
SYS MGMT STA MOUNTING PANEL 28.6
SYS MGMT STA MISC SWITCHES 0.i
RH CONSOLE BUS SWITCHES 2.4
RH CONSOLE AUDIO PANEL 2.5RH CONSOLE LIGHTING CONTROL 2.6
RH CONSOLE CIRCUIT BREAKERS 9.4
RH CONSOLE MOUNTING PANELS 14.5
MISSION SEQUENCE CONTROLS 2.
LH CONSOLE LIGHTING CONTROLS 4.3
LH CONSOLE AUDIO PANEL 3.2
SCS POWER CONTROL 3.4
LH CONSOLE CIRCUIT BREAKERS 7.2
LH CONSOLE MOUNTING PANEL 14.7
LH CONSOLE MISC SWITCHES 0.3
LOWER EQUIP BAY LIGHTING CONTR 5.8
TIMERS 2.4NAV AUDIO CONTROL 1.8
RCS 3.4
LOWER EQUIP BAY PANELS 11.3
LH FWD EQUIP BAY PANEL 0.3
CIRCUIT BREAKERS-PANEL Ii 3.7
CIRCUIT BREAKERS-PANEL 13 4.5
RH FWD EQUIP BAY PANELS 14.5
INSTR DATA DISTR PANEL 2.4
PANEL WIRING & CONNECTORS 68.5
ALEM CONTROLS & DISPLAYS DELTA 20.3
TOTAL FOR CONTROLS ( 363.)WINDOW SHADES 6.6
INTERNAL LIGHTING 14.6
TOTAL FOR LIGHTING ( 21.2)
TOTAL FOR ENVIRONMENT ( 1749.9)
8. OTHER
AFT H/S - C/M BALLAST 162.6
D-37
JSC-£6098
TOTAL FOR BALLAST ( 162.6)MANUFACTURING VARIATIONS -130.
TOTAL FOR MANUFACTURING VARIA ( -130.)EVA HAND HOLDS 27.1
TOTAL FOR EVA HAND HOLDS ( 27.1)PYROTECHNICS 11.
CM-LES ATTACH 3.7
CM-SM ATTACH 17.1
PYROTECHNIC INITIATORS 3.3
TOTAL FOR ORDNANCE&SEP PROVIS ( . 35.1)DOCKING PROVISIONS - LM 247.5
TOTAL FOR DOCKING PROVISIONS ( 247.5)CRUSHABLE RIBS 45.8
CREW COUCH ATTENUATION 110.9
SINGLE POINT FLOTATION SYSTEM 62.9
SEA PICK-UP HOOK 15. -
PARACHUTE ATTACH FITTINGS 31.6
RECOVERY AIDS 4.3
TOTAL FOR EARTH IMPACT AND REC ( 270.5)DROGUE CHUTE SYSTEM 97.8
PILOT CHUTE SYSTEM 28.9MAIN CHUTE CLUSTER 432.
DISCONNECT MAIN CLUSTER 30.
PARACHUTE SEQUENCE CONTROL 0.7
PARACHUTE ATTACH PROVISIONS 5.2DYE MAR/{ER 1.9
FLASHING LIGHT AND COMPONENT 4.2
HS EJECTOR 36.8
HS PLUMBING 5.1
HS BREECH 18.6HS ATTACH PROVISIONS 18.3
TOTAL FOR EARTH LANDING SYSTEM ( 679.5)
TOTAL FOR OTHER ( 1292.3)
i0. NON-CARGO
COMMANDER - LH COUCH 183.
CM PILOT - CTR COUCH 159.
LM PILOT - RH COUCH 162.
TOTAL FOR CREW ( 504.)FLIGHT CREW SUPPORT 76.2
CREW SYSTEMS 289.8
MED RESEARCH OPERATIONS 73.9
SPACE PHYSICS 2.8
TELECOMMUNICATIONS SYSTEM 18.9
GUIDANCE AND CONTROL 2.3
TOTAL FOR CREW EQUIPMENT ( 463.9)ORDEAL 6.9
VAN ALLEN BELT DOSIMETER 3.3
MISCELLANEOUS 0.7
TOTAL FOR MISCELLANEOUS EQUIP ( 10.9)CREW SYSTEMS ALEM 16.
MED RESEARCH OPERATIONS ALEM 50.
ADVANCED SYSTEM 2.9
TOTAL FOR ALEM CREW EQUIP ( 68.9)FUEL RESIDUALS 13.3
OXIDIZER RESIDUALS 23.1
HELIUM-PRESSURIZATION i.
TOTAL FOR RCS RESIDUALS ( 37.4)SURGE TANK 3.7
D-38
JSC-26098REPRESSURIZATION TANKS 3.
LIOH CARTRIGE 100.
POTABLE WATER i.
WASTE WATER i.
ALEM ECS NON EXPENDABLE DELTA 60.
TOTAL FOR ECS RESIDUALS ( 168.7)
TOTAL FOR NON-CARGO ( 1253.8)
ii. CARGO
RETURNED CARGO 305.
TOTAL FOR RETURNED CARGO ( 305.)
TOTAL FOR CARGO ( 305.)
12. NON-PROPELLANT
POTABLE WATER 36.
WASTE WATER 18.
TOTAL FOR WATER (USABLE) ( 54.)
TOTAL FOR NON-PROPELLANT ( 54.)
13. PROPELLANT
RCS FUEL 75.1
RCS OXIDIZER 133.5
TOTAL FOR RCS PROPELLANT ( 208.6)
TOTAL FOR PROPELLANT ( 208.6)
GROSS VEHICLE WEIGHT 13056.3
D-39
NOTE: ALL MASS _A_ _U_H_Y DATA POINT SPACECRAFT 112
IS IN POUNDS. APOLLO SERVICE MODULE ( SM ), I MAR T l @ MISSION Ol
....i'_'"S'T'RUEi'URE....................................(.........322? ........................................................................4. POWER _........20"42........8":6THgR .............................................._....................953
...........B._ ......................................................._g_R1_ ........................................................."..........6RbiN_E/"_/_ ....................._
...............EE!._._EX..............................................!._._ ...................g_F._..._wE..F.QU.!.P............................!.z_._.............._._U.UF._._£_E[_...YaR.........................=._._.&...............g._.g_._E._g._._._U_...................................................Ng_....!._._£_................ s57 ............._O._...K_N_...Eg._.!.P.................................1.e.?_...
SECONDRRY 518 SEQUENTIAL CONTR 14 ...........................................................................................
..........E_.[_I.UC..._M/_......................................I_ .................._..._g_£_..........................................!1_.........................................................................................................._.!.S_._............................................................._ ........................................................................,.................................................................................................................
APOLLO LUNAR EXTENDED _88 : _. GROWTH
MISSION (ALEM) PROV i DRY .flSS IOBO?
;2122;.;........ . . " " _;._fi_g_.".. T2T2TK2ii.22ji_;0__2T2 22 22111T;_RCS RESIDUALS 32
ELEC PNR RESIO l?ECS RESIDUALS
.............................................................................................MAIN PROPUL RESID 878
e. PROTECTION 544 B. AVIONICS ( 428 II. CARGO ( 58
..........AFT..HE.AT...S.H.I.E.Lp.....................................84 ...............I_.S._R._,_._.A_._N.................................2._ ..............._.EM SCIENTIFIC EQUIP 50...........I.N.SpL.A£10N.............................................._e.e............_.q_M_.[_._!.I_S..................................!_ .........................!NERT..MBSS............................!!_e
le. NON-PROPELLANT 999....................................................................._...................... ELEC PNR EXPENDABLES 778
ECS EXPENDABLES 221
3. PROPULSION 3192
MAIN ............................................._............. _._..__._.._....__._.____...__...._______..____..___._.__.._.._.._......_._.__..__.__....__...__...__...__._.__._.__.._._.__._..__._.____.__.___..__..__.._ENGINE 8_9 .'. " ".'......'..i'..'..'.'."" "."" " " "J" " ".'..........................................................................F ......................
FUEL SYS 5S2OXIDIZER SYS _09 ?. ENVIRONMENT ( _21 19. PROPELLANT { 41918
PRESS SYS 729 ENVIRON CONTR SYS eel RCS :.........................................................................................................................................................................................|.....................................................................:
RCS USABLE i 131B................_'_'i_....................................._.............._g..............................................................................................................O_b_C_ ..................................i.................e
OXIDIZER SYS 103 .....................................................................i......................USABLE (MAX) 40594................_____s ............................................ii_ ................... __aeL'i ..................................................e
ELEC PROV : 31
....................................................................._.......................,.....................................................................i....................GROSS pBSS...........................s.4_9
' APOLMPOY CCSD WH 9 NOV 92 m
APOLLO SERVICE MODULE JSC-26098
DESIGN MASS SUMMARY (JSC FORMAT)ALL MASS IN POUNDS
i. STRUCTURE
HONEYCOMB PANELS 391.7
WINDOWS,HATCHES,ACC DOORS,FRAM 6.8FITTINGS AND ATTACH PARTS 64.2
RADIAL BEAMS 364.
INTERNAL PARTITIONS 7.6
FORWARD BULKHEAD 127.2
AFT BULKHEAD 309.8
RCS PANELS 272.5
TOTAL FOR BASIC BODY STRUC-CTR ( 1543.8)SPS ENGINE SUPPORT STRUCTURE 60.2
HYDROGEN TANK SUPPORTS & SHELF 16.8
OXYGEN TANK SUPPORTS & SHELF 32.9
FUEL CELL SUPPORTS & SHELF 36.9EPS MOUNTING PROVISIONS 103.3
ECS MOUNTING PROVISIONS 14.8
INSTRUMENTATION MOUNTING PROVI 6.2
COMMUNICATIONS MOUNTING PROVIS 2.5
R/R ANTENNA & EQUIPMENT SUPPOR 1.4HI GAIN ANTENNA SUPPORTS 29.1
SPS FUEL SYSTEM SUPPORTS 11.2
SPS OXIDIZER SYSTEM SUPPORTS 14.7
SPS PRESSURE SYSTEM SUPPORTS i0.
RCS FUEL SYSTEM SUPPORTS 49.6
RCS OXIDIZER SYSTEM SUPPORTS 51.4
RCS PRESSURE SYSTEM SUPPORTS 10.6
RCS ENGINE SUPPORTS 43.6
C/M-S/M UMBILICAL PROVISIONS 16.7FLYAWAY&CARRY ON UMBIL. PROVIS 6.7
TOTAL FOR SECONDARY STRUCTURE ( 518.6)HONEYCOMB PANELS - SHELL 71.7
UMBILICAL FAIRING 0.7
SPLICES 8.1
FIBERGLAS SANDWICH & C/M CLOSE 33.4FITTINGS & ATTACH PARTS 7.6
TOTAL FOR FAIRING-C/M TO S/M ( 121.5)PAINT & FINISHES 40.
NITROGEN PURGE 4.2
TOTAL FOR MISCELLANEOUS ( 44.2)ALEM STRUCTURE PROVISION DELTA 998.4
TOTAL FOR ALEM STRUCTURE DELTA ( 998.4)
TOTAL FOR STRUCTURE ( 3226.5)
2. PROTECTIONAFT HEAT SHIELD 84.1
TOTAL FOR AFT HEAT SHIELD ( 84.1)FORWARD SECTION 4.CENTER SECTION 107.9
FAIRING 14.4
AFT HEAT SHIELD 108.1
MOUNTING PROVISIONS 57.2
SPS TANKS 36.3BULKHEADS 16.7
BOOST PROTECT&RCS PLUME SHIELD 77.8
SPS ENGINE CLOSEOUT 37.7
D-41
JSC-26098TOTAL FOR INSULATION ( 460.1)
TOTAL FOR PROTECTION ( 544.2)
3. PROPULSION
ENGINES 821.1DRAINS 2.7
TEMPERATURE CONTROLS 5.
FLIGHT COMBUSTION STABILITY MO 0.3
TANKS 385.2
LOWER SKIRTS & RINGS 33.4
UPPER SKIRTS, RINGS & SUPPORTS 6.5INTERNAL SUPPORTS 7.5
TANKS & DOORS 16.8
PLUMBING & FITTINGS 27.3VALVES & REGULATORS 2.2
QUANTITY INDICATION 37.2TEMPERATURE CONTROL 1.5
SUPPORTS 2.6
ZERO G CONTROLS & BAFFLES 71.6
TANKS 385.2
LOWER SKIRTS & RINGS 33.4
UPPER SKIRTS, RINGS & SUPPORTS 6.5INTERNAL SUPPORTS 7.5
TANKS & DOORS 20.4PLUMBING & FITTINGS 23.4
VALVES & REGULATORS 2.1
QUANTITY INDICATION 37.MIXTURE RATIO CONTROLS 18.3
TEMPERATURE CONTROL 1.9
SUPPORTS 2.2
ZERO G CONTROLS & BAFFLES 71.5
TANKS 636.
TANK SUPPORTS 2.4
PLUMBING & FITTINGS 31.2
VALVES & REGULATORS 36.4
HEAT EXCHANGER 16.7
SUPPORTS 6.7
TOTAL FOR MAIN PROPULSION ( 2759.7)ENGINES 82.4
TEMPERATURE CONTROL 1.2
SUPPORTS i.
TANKS & EXPULSION 56.4
PLUMBING & FITTINGS 8.2
VALVES & REGULATORS 27.6
TEMPERATURE CONTROL 0.4
SUPPORTS 9.8
TANKS & EXPULSION 62.4
PLUMBING & FITTINGS 11.8
VALVES & REGULATORS 19.6
TEMPERATURE CONTROL 0.4
SUPPORTS 9.2
TANKS 46.PLUMBING & FITTINGS 13.2
VALVES & REGULATORS 50.4
SUPPORTS 2.
SUPPORTS, CONDUITS, ETC 2.9WIRING-COMMON UTILITY 28.
TOTAL FOR RCS PROPULSION ( 432.9)
TOTAL FOR PROPULSION (3192.599)
D-42
JSC-£60984. POWER
LIGHTING 21.7
H2 SYSTEM SUBCONTRACTOR ITEMS 151.6
H2 SYSTEM PLUMBING 5.6H2 SYSTEM VALVES 11.5
H2 SYSTEM SUPPORTS 2.7
02 SYSTEM SUBCONTRACTOR ITEMS 175.1
02 SYSTEM PLUMBING 6.1
02 SYSTEM VALVES 23.1
02 SYSTEM SUPPORTS 2.5
FUEL CELL SYS CONTRACTOR ITEMS 711.
FUEL CELL SYS PLUMBING 16.8
FUEL CELL SYS SUPPORTS 17.4FUEL CELL SYS WATER GLYCOL 24.4
FUEL CELL SYS SPACE RADIATORS 29.6
FUEL CELL SYS KOH i0.
POWER DISTRIBUTION BOX 42.6
CRYO ELEC CONTROL BOX 11.5
TERMINAL DISTRIBUTION PANELS 7.5SUPPORTS & INSTALLATION PROV 7.1
SPS CONTROL BOX 16.5
TOTAL FOR ELECTRICAL PWR EQUIP ( 1294.3)ELECTRICAL HARNESS INSTALLATIO 486.3
CIRCUIT INTERRUPTERS 8.6
SUPPORTS & INSTALLATION PROVIS 62.5
TOTAL FOR ELECTRICAL INSTALL ( 557.4)SM JETTISON CONTROLLER 13.6
SUPPORTS & HARDWARE 0.I
TOTAL FOR SEQUENTL EVENTS CONT ( 13.7)ALEM EPS DELTA 177.3
TOTAL FOR ALEM EPS DELTA ( 177.3)
TOTAL FOR POWER ( 2042.7)
6. AVIONICS
SIGNAL CONDITIONERS 16.7
TRANSDUCERS 33.1
MISCELLANEOUS 13.8
RADIATION DETECTION 8.SENSOR ELECTRICAL PROVISION 0.2
WIRING-COMMON UTILITY 1.8
SPS FUEL GAUGING PROVISION 1.8
SUPPORTS 13.
ALEM INSTRUMENTATION DELTA 205.3
TOTAL FOR INSTRUMENTATION ( 293.7)2KMC HIGH GAIN ANT TRANS LINES 4.2
HIGH GAIN ANTENNA 93.9
VHF OMNI ANT TRANS LINES 34.7
SUPPORTS 0.8
TOTAL FOR COMMUNICATIONS ( 133.6)
TOTAL FOR AVIONICS ( 427.3)
7. ENVIRONMENT
WGC VALVES 9.8
WGC CONTROLS 21.9
WGC PLUMBING%SID 15.8WGC SPACE RADIATOR%SID 102.4
WGC SUPPORTS & HARDWARE 15.7
WSS PLUMBING%SID 0.6
D-43
JSC-£6098WSS SUPPORT & ATTACH PARTS 0.3
HTS PLUMBING & FITTINGS 9.1
HTS SUPPORTS 6.9
HTS HEAT TRANSFER FLUID 30.7
HTS MISCELLANEOUS COMPONENTS 2.9
HTS INSTALLATION HARDWARE 4.9
TOTAL FOR ENVIRON CONTROL SYS ( 221.)
TOTAL FOR ENVIRONMENT ( 221.)
8. OTHER
PYROTECHNICS i.
C/M-S/M TENSION TIE 18.5
TOTAL FOR ORDNANCE & SEP PROV ( 19.5)MANUFACTURING VARIATIONS -I00.
TOTAL FOR MANUFACTURING VARIA ( -I00.)TRANSPONDER 14.8
WAVEGUIDE 1.5
ANTENNA KIT 0.6
MISCELLANEOUS 0.6
PYROTECHNIC INITIATORS 0.4
MISCELLANEOUS 135.
ALEM GFE DELTA 879.9
TOTAL FOR GOV FURNISHED EQUIP ( 1032.8)
TOTAL FOR OTHER ( 952.3)
I0. NON-CARGO
FUEL 8.4OXIDIZER 18.
HELIUM-PRESSURIZATION 6.
TOTAL FOR RCS RESIDUALS ( 32.4)HYDROGEN - EPS 2.4
OXYGEN - EPS 9.2
ALEM EPS NON EXPENDABLE DELTA 5.8
TOTAL FOR ELECTRCL PWR NON-EXP ( 17.4)OXYGEN - ECS 4.
ALEM ECS NON EXPENDABLE DELTA 2.
TOTAL FOR ECS NON-EXPENDABLE ( 6.)STORAGE BOTTLES 87.6
PROPELLANT TANKS 5.4
NITROGEN 1.3ENGINE-OUTSIDE TANK OXID 47.4
FEED LINE-OUTSIDE TANK OXID 44.7
TRANSFER LINE-OUTSIDE TNK OXID 31.6
RESIDUAL OXIDIZER 382.1
ENGINE-OUTSIDE TANK FUEL 29.6
FEED LINE-OUTSIDE TANK FUEL 29.5
TRANSFER LINE-OUTSIDE TNK FUEL 19.5
RESIDUAL FUEL 199.
TOTAL FOR MAIN PROPUL RESIDUAL ( 877.7)
TOTAL FOR NON-CARGO ( 933.5)
ii. CARGO
ALEM SCIENTIFIC EQUIPMENT 50.
TOTAL FOR ALEM SCIENTIFIC EQUI ( 50.)
TOTAL FOR CARGO ( 50.)
12. NON-PROPELLANTHYDROGEN EPS 53.
OXYGEN EPS 472.8D-44
JSC-26098ALEM EPS EXPENDABLE DELTA 252.1
TOTAL FOR EPS EXPENDABLES ( 777.9)OXYGEN ECS 147.
ALEM ECS EXPENDABLE DELTA 73.5
TOTAL FOR ECS EXPENDABLES ( 220.5)
TOTAL FOR NON-PROPELLANT ( 998.4)
13. PROPELLANT
RCS FUEL USABLE 432.4
TOTAL FOR RCS FUEL USABLE ( 432.4)RCS OXIDIZER USABLE 883.6
TOTAL FOR RCS OXIDIZER USABLE ( 883.6)RCS UNUSABLE 0.
TOTAL FOR RCS UNUSABLE ( 0.)MAIN USABLE 40594.
TOTAL FOR MAIN USABLE ( 40594.)MAIN UNUSABLE 0.
TOTAL FOR MAIN UNUSABLE ( 0.)
TOTAL FOR PROPELLANT ( 41910.)
GROSS VEHICLE WEIGHT 54498.5
D-45
.OTE:.LL .ASS MAB_ SUMMARY OAT.POI.TSPACECRAFT iIS IN POUNDS, APOLLO SPACECRAFT/LUNAR MODULE ADAPTER (SLA), I MAR 71 MISSION Jl
.....................................................................(........__iB=_i"_6__ ............................................._.............__8/oi_g_ ..............................................(...........g_E...1._.. STRUCTURE .................................................................................................................................................................................................................PRIMRRY BODY STRUCT . 387S WIRING GO PYROTECHNICS GG
SEPARATION PROV 472
SECONDARY BODY STRUCT ..................................................................................................................................................................i.....................LM SUPPORT 92
................_S..._.T_..._Rq_......................................_._...........................................................................:...........................................................................................).....................UMBIL PROV • S ......................................................................_..........................................................................................._............._.....
...................................................................... 9. GROWTHMISCL _Z
................................... _ .............................................................................................DRY BflSS i 40GS...................................................................................................................................................................................... i
.....................................................................5. CONTROL _ 10. NON-CARGO
I ...................................................................!......................
......................................................................_6 s. AvioNICS2. PROTECTION ......................................................................_............_.....II. CARGO (LM, ALEM 36000
...................................................................... LB, REF MISSION Ji)IHSULRTION 250
....................................................................._.........................................................................................."......................INERT MRSS 40ssI
.....................................................................:...................... 12. NON-PROPELLANT
....................................................................._ PPnPHIRInN _............._'""' ....................................................................i....................................................................................................................................................................................................................................
....................................................................._..........................?':'"'EN'V'i'RON'ME'HT _ : 19, PROPELLANT { -
...................................................................... r ............................................................................................. ' .................................................................................................................
..................................................................... I ...................................................................................................................
...................................................................... :............................................................................................ !...............................................................................................................
."".".".i.."i.".";"""."."".""""."Z.."."."."."";'.'.';.'i;.".......................................................................................................................................i_........................................................................................................................................._.o_ ._ .oss' RPOLMP05 CCSD NH 9 NOV 92 m
JSC-£6098APOLLO ADAPTER
DESIGN MASS SUMMARY (JSC FORMAT)ALL MASS IN POUNDS
i. STRUCTURE
HONEYCOMB PANELS 1736.3
LONGERONS 48.2
FRAMES & RINGS 56.
WNDOWS,HATCHES,ACC DOORS&FRAME 84.2FITTINGS & ATTACH PARTS 105.1
TOTAL FOR BASIC BODY STRUC-FWD ( 2029.8)HONEYCOMB PANELS 760.6
LONGERONS 5.2
FRAMES & RINGS 222.6
WNDOWS,HATCHES,ACC DOORS&FRAME 16.8FITTINGS & ATTACH PARTS 40.4
TOTAL FOR BASIC BODY STRUC-AFT ( 1045.6)LEM SUPPORT 92.4
EPS MOUNTING PROVISIONS 14.1
FLYAWAY&CARRY ON UMBIL.PROV 8.5
TOTAL FOR SECONDARY STRUCTURE ( 115.)SERVICING PLATFORM PROVISIONS 27.2
TOTAL FOR MISCELLANEOUS ( 27.2)
TOTAL FOR STRUCTURE ( 3217.6)
2. PROTECTION
INSULATION 250.1
TOTAL FOR INSULATION ( 250.1)
TOTAL FOR PROTECTION ( 250.1)
4. POWER
WIRING-COMMON UTILITY 59.9
TOTAL FOR ELECTRICAL POWER SYS ( 59.9)
TOTAL FOR POWER ( 59.9)
8. OTHER
PYROTECHNICS & INITIATORS 65.5
PANEL EJECTION SYSTEM 182.7
DEBRIS CATCHER 178.6
FITTINGS & ATTACH PARTS 34.5
LEM PROVISIONS 23.3
S/M-SLAUMBILICAL 11.7SLA-LEMUMBILICAL 41.5
TOTAL FOR ORDNANCE & SEP PROV ( 537.8)
TOTAL FOR OTHER ( 537.8)
GROSS VEHICLE WEIGHT 4065.4
D-47
NOTE:RLLMnSS OATAPOINT DESIGN HnSS SUHNARYIS IN POUNDS, (_ APOLLO LUNAR MODULE (LM), 26 JUL 71 LM 10, MISSION al
FUHCTIOHflLSYSTEH CODE E F _ H
.....................................................................................................1, STRUCTURE , 18261 1015 :.................. oLLLLLLJse I RRENOTE:INRLLINcHEs.DIMENSIONS
""'2"_'"'P R6'Y E'ET'Y'6 h...................... 36'q," 4S3 , INCHES _ I XE512.25.................................................,......................................................................._ _
.3._..._R_Uk_.!.gN......................................................_.L1..........._89!................................... _ '-_
.,.oo._ \L/ .S EN,,,.GE.................................................................................................................... TO BOTTON
..._m...p.OWE.R.................................... ?.35. ?86! 117"100! / _ OF ENGINE.................................................i....................................'................._ ................. NOZZLE
...5_...C.ON T.R O.L _ - .................................. 1_.291
_. _VIONICS , 399 63 239,40! _ __'_F_ / _ ASCENT
.......................................................................................................................... , STRDE
.................................................................. L................. i .................. • .................
7. ENVIRONMENT 681 427 se.es eASE
..................................................................................................................... 11s.el4 DESCENT
.................. _................. , .................. t ................. STAGE
.B._...OT_ER...................................S.51...........s.el ...................................... '
9. GROWTH - - _ _ I E:_ _/7-•-- _ XE72,849
..............DRy..HB.SS...................If.sAT........._.ffs ..................................... I ,;._ (REF_ I _._ (REF) _ GROUND LINE
Le,..Ng_CAR_O ................"........3_ff.........._83 ..................................................................................................... _ ................. _.................. r ................. RPOLDROS CCSD WH _8 RUG B9
II. CARGO - 1099H.O.TE._.............................................................................................................................................
............. ]HE_T...H_$S ...... 4941 8388, , E. ASCENT STRGE (ASPF. DESCENT STAGE (DS)
!2.,..._gN_.Rp_E.kkR_............13_..........SSB................................................................................................................................................................................................
13, PROPELLANT 549H 18799, , RS DS.........PE_LGN_EH_.kP._E.yP._PME_YdJ_P _ ..........................7so.......................
............. _ROS_ _SS 10571 25SG5 PRESSURIZED VOLUME, V (CU FT) 283
...................................................(36236) I ................. 1.................................... _................................................................DESIGN-ENVELOPE SURFACE P............................................................AREA, A. (SQ FT) i"''" """"""" _
.................................................. .......pESLGN_Lss!pH, ....................................................................
RPOLMP06 CCSD WH 20 RUG _3
MA_ SUHHARY DATA_POI,_L, lONOTE: ALL MASSMISSION dl
IS IN POUNDS. APOLLO LUNAR MODULE (LM), ASCENT STAGE (AS), 26 JUL T1
•i;___ ....................................(.........i._._6..._......._..;......._._._.E.........;.....................................................T..L..................[................_._._..........................................................................(...........__F_.............................................................................................. _....9.Z_E_......................................................CABIN FRONT F.RC.E..............................i._.I.... BATTERIES 247 ELEC EXPLOSIVE DEVICES 29CABIN BARREL i 203 INVERTER, CONTROL, ETC 151 EARTH LAUNCH GFE G82
.........._.k_c.z.[.gU..............................................5_ ..............._,_._g.s_...._.s_._...................ZB?............_N.qK_!_.!NG..,Y_.R!.RLkg._..........._.Ge....• AFT ENp..BqDY ............................ _Q ............_.H_L_A_I.PH._HB .............................._ ........................................................................,......................
..................................................................... , ........................................................................................... } ........................................................................................... ,= .................... :9. GROWTH
......................................................................................................................................................................................... DRY ffRSS _567
................................................................................................................................................................. _..........._.......= 10. NON-CARGO 3T_5, CONTROL ................................................................................................................................................................................................................................................................................... UNUSABLE MAIN PROPEL 252
: UNUSABLE RCS PROPEL 122
2: _i_._../../.LI / _.........._._.."B. AVIONICS _S ,_I. CARGO , =o WINDOW SHIELDING 2 STABILITY AND CONTROL ?9
CABIN FRONT FACE B_ NAVIGATION , GUID 78 INERT _RSS _9_1CABIN BARREL ............_._ .... INSTRUMENTATION 129
AND MIDSECTION COMMUNICATIONS 113 12. NON-PROPELLANT ( 13G
. AFT END BODY ................. _ ......................................................................................................_.I.g.q.!.P_..._U.E..EA_.E.S..............................I._6.,.
...........................................................................................3, PROPULSION 711 _.._;_.-_-._._-_.._-_._._-`.._`_._-.._._._.._-._._-_.`_-_.._`_._....i_.._._`_.._._._._._._._._._`._`.._._.._-_.-_.-_`_.-_.-..._._..._-_-._..`.`_2_-_-..-_`_._-_._`.-_`..._._.._-_._-._._._._._._._._._._..-_.-_.._._._._._._
ASCENT PROPUL SYS 9B_ ..................................................................................................................................................................;......................(ENGINE 173) , .....................................................................,.....................
REACTION CONTR SYS 2½2 ......................................................................;.....................,...........................................................................................:?. ENVIRONMENT GB1 13. PROPELLANT ( 5_9_
CONTROLS 185 MAIN PROPEL (DELTA V) ½985
............................................................................................CREN PROVISIONS 152 RCS PROPEL (DELTA V) 509
ENVIRON CONTR SYS 29G ................................................................................................................................................................. !...................... OISPLRYS _8
......................................................................_......................................................................................................................................................................................... i..................... I
: GROSS _RSS ! 10571 m
RPOLMP07 CCSD WH 9 NOV 92
JSC-26098APOLLO LUNAR MODULE-ASCENT STAGE
DESIGN MASS SUMMARY (JSC FORMAT)ALL MASS IN POUNDS
i. STRUCTURE
FRONT FACE SKINS 46.2
BEAMS VERTICAL 22.8
CAPS FF BEAMS 2.2
STIFFENERS SKIN 19.4
FRONT FACE WINDOW FRAMES 14.2
INTERSTAGE MTS EXT 13.3EVA HANDRAIL INSTL 6.5
CABIN 340 SUPPORTS 2.1
CABIN SUPPORTS 0.2
CABIN EPS SUPPORTS 2.7
CABIN COMM SUPPORTS 0.7
FRONT FACE WINDOWS 24.1
FRONT FACE HATCH 13.
FRONT FACE JSF 13.6
TOTAL FOR FRONT FACE TOTAL ( 181.)CABIN SKINS 29.9
CABIN IMU BEAMS 18.7
CABIN LONGERONS 21.2
FRAMES CABIN SKINS 16.8
FRAMES UPR DOCKING WINDOW 5.9CABIN 340 SUPPORTS 38.
ECS SUPPORTS 3.5
EPS SUPPORTS 3.3
RCS SUPPORTS 7.4
CONSOLE SUPPORTS 2.
CABIN DECK 24.3
CABIN WINDOW 4.
CABIN JSF 27.5
TOTAL FOR CABIN TOTAL ( 202.5)TUNNEL SKINS 15.5
MIDSECTION SKINS 22.9
MIDSECTION BULKHEADS 97.4
BEAMS Y22 16.6
BEAMS YI7 12.
BEAMS Y37 4.1BEAMS ENGINE 15.
BEAMS BULKHEADS 21.5
MIDSECTION LONGERONS 9.4
MIDSECTION STIFFENERS 32.
MIDSECTION FRAMES 23.2
MIDSECTION INTERSTAGE MTS 21.8
MIDSECTION s&C SUPPORTS 0.8
MIDSECTION N&G SUPPORTS 0.8
MIDSECTION 340 SUPPORTS 54.7
MIDSECTION ECS SUPPORTS 17.1
MIDSECTION INST SUPPORTS i.
MIDSECTION EPS SUPPORTS 12.2MIDSECTION PROP SUPPORTS 30.2
MIDSECTION RCS SUPPORTS 49.9
MIDSECTION COMM SUPPORTS 13.9
MIDSECTION GFE SUPPORTS 3.2
MS DECK X2335 14.2
MS DECK X2535 18.4
MS DECK X277 7.7
D-50
JSC-26098MS DECK X294 22.1
MS DECK X310 1.9MIDSECTION HATCH 10.9
MIDSECTION JSF 21.5
TOTAL FOR MIDSECTION TOTAL ( 571.9)AEB RACKS-WO-CP 16.3
AEB HORIZONTAL BEAMS 9.8
AEB COLD-PLATE ASY 18.7AEB FTG&TRUSSES 6.2
AEB ECS SUPPTS I.
AEB INST SUPPTS 0.2
AEB EPS SUPPTS 5.3
AEB PROP SUPPTS 1.2
AEB RCS SUPPTS 9.7
AEB ANTENNA SUPPTS 0.5
AEB JSF 1.4
TOTAL FOR AEB TOTAL ( 70.3)ASCENT LCD TOTAL 0.i
ASCENT MISCL/LCD 0.2
TOTAL FOR ASCENT MISCL/LCD ( 0.3)
TOTAL FOR STRUCTURE ( 1026.)
2. PROTECTION
WINDOW SHIELDING 1.6
TOTAL FOR FRONT FACE THER PROT ( 1.6)WINDOW SHIELDING 0.7
TOTAL FOR CABIN THERM PROTECT ( 0.7)FRONT FACE CABIN SHIELDING 39.1
FRONT FACE CABIN INSULATION 27.5
FRONT FACE CABIN JSF 12.6FRONT FACE CABIN SUPPTS 4.2
MIDSECTION SHIELD 58.5
MIDSECTION INSUL 55.2
MIDSECTION JSF 5.2
MIDSECTION SHIELD SUPPORTS 107.6
AEB SHIELDING 19.5
AEB INSULATION 16.2
AEB JSF 2.9
AEB SUPPTS 13.1
TOTAL FOR A/S THERMO PROTECT ( 361.6)
TOTAL FOR PROTECTION ( 363.9)
3. PROPULSION
PROPELLANT TANK INST 130.7
PROPELLANT QUANTITY SENSORS 1.8
PROPELLANT PLUMBING 23.
HELIUM TANKS 107.8
PRESSURIZATION PLUMBING 26.6PRESSURIZATION SYS 4.5
ASCENT ENGINE 172.7
ENGINE & MISC 2.4
TOTAL FOR ASCENT PROPULSION SY ( 469.5)FUEL TANKS 17.6
OXIDIZER TANKS 21.ASCENT PROP TIE-IN 13.4
FUEL SYSTEM 22.1
OXIDIZER SYSTEM 22.
PROP FILTER & ISO VALVE 3.9
HELIUM TANKS 16.6D-51
JSC-£6098PLUMBING-PRESS SYS A 11.9
PLUMBING-PRESS SYS B 11.7THRUST CHAMBER ASSY 82.5
HARDWARE CLUSTER 1 4.9HARDWARE CLUSTER 2 4.8
HARDWARE CLUSTER 3 4.8
HARDWARE CLUSTER 4 4.7
TOTAL FOR REACTION CONTROL SYS ( 241.9)
TOTAL FOR PROPULSION ( 711.4)
4. POWER
BATTERY ASCENT 247.3
ELECT CONT ASSY 21.
INVERTER ASCENT 30.8
ELECTRONIC UNIT 20.1
PANEL ii ASCENT 42.5
PANEL 16 ASCENT 36.4
GN&C HARNESS ASSY 5.1
S&C HARNESS ASSY 0.i
ECS HARNESS ASSY 12.1
INSTR HARNESS ASSY 1.8EPS HARNESS ASSY 13.3
PROP HARNESS ASSY 3.1
RCS HARNESS ASSY 1.2
COMM HARNESS ASSY 4.4
EDS HARNESS ASSY 6.
MULTI-SUBSYS HARNESS 229.3
MISC HARNESS ASSY 3.
INSTALLATION HARDWARE 49.2
DELTA WEIGHT CHANGES 0.9
WIRE ADJUSTMENT 7.2
TOTAL FOR ELECTRICAL POWER SYS ( 734.8)
TOTAL FOR POWER ( 734.8)
6. AVIONICS
ATCA 23.7
RATE GYRO ASSY 2.
ABORT GUIDANCE SYSTEM 53.3
TOTAL FOR STABILITY & CONTROL ( 79.)REN RADAR SECT 78.1
TOTAL FOR NAVIGATION&GUIDANCE ( 78.1)SIGNAL CONDITIONER 70.9
PCMTEA 22.6DATA STORAGE UNIT 2.5
CAUTION & WARNING 18.3
AEB JSF O.2
ECS SENSORS 5.9PROP SENSORS 3.6
RCS SENSORS 4.9
TOTAL FOR INSTRUMENTATION ( 128.9)VHF XCEIVER & DIPLEXER 13.1
SIG PROCESSOR ASSY 10.4
VHF IN-FLIGHT ANTENNA 4.8
UHF RANGING SYS 2.6
EVA ANTENNA ASSY 2.
S-BAND TRANSCEIVER 20.
POWER AMPL & DIPLEX 18.7
IN-FLIGHT ANTENNAS 0.8
STEERABLE ANTENNA 27.5
D-52
JSC-26088MISCELLANEOUS 13.3
TOTAL FOR COMMUNICATIONS ( 113.2)
TOTAL FOR AVIONICS ( 399.2)
7. ENVIRONMENT
PANEL 1 DISPLAYS & INDICATORS 16.7
PANEL 2 DISPLAYS & INDICATORS 18.1
PANEL 3 DISPLAYS & INDICATORS 1.4
PANEL 6 DISPLAYS & INDICATORS 7.4
PANEL 8 DISPLAYS & INDICATORS 0.4
PANEL 12 DISPLAYS & INDICATORS 1.9
PANEL 14 DISPLAYS & INDICATORS 2.1
TOTAL FOR DISPLAYS (48.00001)SUPPORT STRUCTURE 32.5
PANEL 1 32.8
PANEL 2 24.4
PANEL 3 18.3
PANEL 4A 0.9
PANEL 4B 0.9
PANEL 5 5.3PANEL 6 1.9
PANEL 8 i0.PANEL 12 16.
PANEL 14 7.
NON-PANEL ITEMS 35.
MISCELLANEOUS 0.2
TOTAL FOR CONTROLS ( 185.2)FURNISHINGS 71.5
OUTER LIGHTING 26.4
INNER LIGHTING 4.4
MISCELLANEOUS 8.6
WASTE MANAGEMENT 3.9
PAINT 6.CREW PROVISIONS 31.3
TOTAL FOR CREW PROVISIONS ( 152.1)HAM STD 190 PKG 101.8
190 PKG HDW I0.
02+H20 COOLANT ASSY 36.1
ATMOS REVIT SECTION 2.8
-290 SUBTOTAL 7.9
HTS PRI LOOP 24.9
HTS SECONDARY LOOP 8.
TOTAL GOX TANKS I0.i
390 OX MODULE 8.9
390 PKG-HDW 7.7
PLSS 02 RECHARGE 3.5
TOTAL H20 TANKS 10.7
490 H20 MODULE 5.7
490 PKG-HDW 4.9PLUMBING GAEC 28.7
COLD PLATES R&D 2.9
TOTAL PRIMARY CP 2.6
LIOH CARTRIDGE 18.2
TOTAL FOR ECS ( 295.4)
TOTAL FOR ENVIRONMENT (680.7001)
8. OTHER
EXPLOSIVE DEVICES 19.
EXPLOSIVE STRUCTURE 9.7
D-53
JSC-28098
TOTAL FOR ELEC EXPLOSIVE DEVIC ( 28.7)DROGUE 21.4
BPA INSTALLED HARDWARE 1.3
PRIMARY GN&C SYS 258.4
ORDEAL 6.9
CREW PROVISIONS 376.9
INSTRUMENT SCIENCE EQUIPMENT 15.7
ELECTRICAL ASCENT 1.7
TOTAL FOR EARTH LAUNCH GFE ( 682.3)
MFG VAR AT WHG -70.4
VARIOUS UPDATES 10.6
TOTAL FOR MANUFACTURING VARIA ( -59.8)
TOTAL FOR OTHER ( 651.2)
i0. NON-CARGO
TRAPPED APS 14.2
UNUSED APS PROP 47.7
DISP & MALFUNCTION 140.3
UNUSABLE PROPELLANT 49.9
TOTAL FOR UNUSABLE PROP-MAIN ( 252.1)
UNUSABLE PROP-RCS 121.7
TOTAL FOR UNUSABLE PROP-RCS ( 121.7)
TOTAL FOR NON-CARGO ( 373.8)
12. NON-PROPELLANT
TOTAL COOLANT 24.6
TANKED GOX 4.8
WATER-RESIDUAL i.i
WATER TANKED 90.
NITROGEN ASC H20 TNK 0.i
HELIUM-ASCENT-APS 13.
HELIUM-ASCENT-RCS 2.1
TOTAL FOR LIQUIDS & GASSES ( 135.7)
TOTAL FOR NON-PROPELLANT ( 135.7)
13. PROPELLANTDELTA-V PROPELLANT 4984.9
TOTAL FOR MAIN PROPELLANT ( 4984.9)
RCS PROPELLANT DELTA-V 509.5
TOTAL FOR RCS PROPELLANT ( 509.5)
TOTAL FOR PROPELLANT ( 5494.4)
GROSS VEHICLE WEIGHT 10571.1
D-54
1 I f
NOTE: ALL MASS H_ _UHHARY DATA_POINT LM 10
IS IN POUNDS. APOLLO LUNAR MOOULE (LM), OESCENT STG (DS), 26 JUL 71 _ MISSION 61
1. STRUCTURE ( 1015 ......................................................................4. POWER _ ......... ?8G .... 8, OTHER ( G81FORWARD SECTION 220 BATTERIES 670 LANDING GEAR INSTL ; HAG
CENTER SECTION LEFT 154 , ELEC CONTR ASSY, MISCL 43 ELEC EXPLOSIVE DEVICES! 24MIO-CENTER SECTION 112 HARNESS ASSY 48 EARTH LAUNCH GFE ! 115
CENTER SECTION RIGHT 167 INSTALLATION HDWR 12 MANUFACTURING VARIATION -24
...........R._.._E._J._._,N..........................................._8 .............._LSC_ ..........................................................13 ................A.NDMISCL .....................................................
..........._._..._._._....._._..._._ ........................_._.........................................................................._......................ALSEP REMOTE DEPLOY 31 DRY MASS 4446
5. CONTROL _ - 10. NON-CARGO 763TRAPPED PROPEL ?S
UNUSED PROPEL 349.....................................................................i.............................................................................................................................._'i's__gi_"_ND......................i..........._g8....
MALFUNCTION PROPEL ,:
: .............................................................................................. "..jj.`..jj.jjj``._`.jj...j_.j°.'j.jjjjj_'°.j._j°_.j...jj.jj.°.jjj._.jj..jjjj'`..`.`j._.....°°.`...j._''
o THERMAL PROT AFT I STABILITY AND CONTROL ; 13 SCIENCE EQUIPMENT 1099
.......... _.Sg..._g._!..._H.I.E._D .................................... 1.... NAVIG AND GUID 43 INERT hRSS 83o9
._...._.g_=_R.g_._.kAN._......................(..........5._8-..COOLANT 3
............................................................................................. GOX 94
3. PROPULSION 1091 NATER 408
PROPEL TANK INSTL 499 NITROGEN I
.......... P.ROPEL...FD...D.[S.CN....I.N.ST.L ...................... G................................................................................................. HELIUM 52
..........._B.g_.g_...eg.gMB.!.E_..................................._ ..........................................................................,......................'...................................................................._................................U._k_M...!.!_._...........................................!..!._........7.,....g._._g_._N._ .........................................._2._... 13:PRO_E_LANT.................................{"_B7'99 ....
PRESSURIZ PLUMBING 68 DISPLAYS AND CONTROLS 3 MAIN PROPEL (DELTA V) ! IB799
ENGINE AND MISCL 368 CRE_ PROVISIONS 228 ......................................................................;.....................
ENVIRON CONTR SYS 19G .....................................................................i.....................
-..]S.S.........).).>-.)..)i...........])..i.................),/.........>/ ........i...............).i..............i)]-)))->i...........i.......i........i........................D.))-I.........).]-oI..................................................................... i............................................................................................ i ............................................ _RO_S _R_ : 25GG5"................................................................................................................................... 0
RPOLMP08 CCSD _H 9 NOV 92
APOLLO LUNAR MODULE-DESCENT STAG JSC-260S8
DESIGN MASS SUMMARY (JSC FORMAT)ALL MASS IN POUNDS
i. STRUCTURE
WEB FWD END CLOSURE 6.
UPPER CAP FWD CLOSURE 1.2
LOWER CAP FWD CLOSURE 1.7
POST-LEFT FWD CLOSURE 6.5POST-RIGHT FWD CLOSURE 6.5
STIFFENERS FWD CLOSURE 5.1
LG FITTINGS FWD CLOSURE 2.
JSF FWD CLOSURE 3.1
FORWA/_D LEFT-PANEL 20.4
FORWARD RIGHT-PANEL 23.2
FORWARD UPPER DECK 16.
FORWARD LOWER DECK 11.8
FWD EQUIPMENT BAY LEFT 11.8
FWD EQUIPMENT BAY RIGHT i0.iFWD INTERSTAGE MOUNT 4.5FWD INTERSTAGE MT COL 2.9
FWD LG SUPPT TRUSS 15.3
FWD OXID TANK SUPPORT 33.
FWD TRUSS & SUPPORTS 20.8S-IV-B ATTACH FTG 7.7
FWD EGRESS PLATFORM 8.6
EQUIPMENT SUPPT FWD SECTION 1.3
TOTAL FOR FORWARD SECTION ( 219.5)WEB CENTER LFT CLO 5.4
UPR CAP CEN-LEFT CLOSURE I.i
LWR CAP CEN-LEFT CLOSURE 1.7
POST AFT LEFT CLOSURE 6.5
POST FWD LEFT CLOSURE 6.7
STIF CENTER-LEFT CLOSURE 4.2
LG FTG CENTER-LEFT CLOSURE 2.2
JSF CENTER-LEFT CLOSURE 2.4
FWD PAN CENTER-LEFT 18.5
AFT PAN CENTER-LEFT 22.5
UPR DECK CENTER-LEFT 16.5
LWR DECK CENTER-LEFT 11.3
TRUSS & SUPPT CENTER-LEFT 46.7
S-IV-B ATTACH FTG 7.7
TOTAL FOR CENTER SECTION LEFT ( 153.4) 7
LF PAN MID-CENTER 14.1
RT PAN MID-CENTER 14.
FWD PAN MID-CENTER 14.8AFT PAN MID-CENTER 13.9
ENG ACT SUPPT M-C-S 6.2
ENG TRUS SUPPT COL 7.9
ENG SUPPT TRUSSES 10.6
BLAST DEFLECTOR 8.5
JSF CRUCIFORMS ETC 4.9
EQUIPMENT SUPPORT CENTER-MID 17.1
TOTAL FOR MID-CENTER SECTION ( 112.)WEB CENTER-RT CLOSURE 5.8
UPPER CAP CENTER-RT CLOSURE i.i
LWR CAP CENTER-RT CLOSURE 1.7
POST FWD RT CLOSURE 6.6
POST AFT RT CLOSURE 6.5D-56
JSC-HS0S8
STIF CENTER-RT CLOSURE 5.
LG FTG CENTER-RT CLOSURE 2.
END CLOSURE CENTER-RT 4.4
FWD PAN CENTER-RT 21.5
AFT PAN CENTER-RT 20.1
UPPER DECK CENTER-RT 16.1
LOWER DECK CENTER-RT 12.1
TRUSS & SUPPORT CENTER-RT 51.5S-IV-B ATTACH FTG 7.6
COLD PLATE & RAILS 0.5
EQUIPMENT SUPPRT CENTER-RT 4.8
TOTAL FOR CENTER SECTION RIGHT ( 167.3)
WEB AFT END CLOSURE 6.6UPPER CAP AFT CLOSURE 1.2
LOWER CAP AFT CLOSURE 1.7
POST LEFT AFT CLOSURE 7.
POST RIGHT AFT CLOSURE 7.1
STIFFENERS AFT CLOSURE 2.7
LG FTG AFT CLOSURE 2.
JSF AFT END CLOSURE 4.6
AFT LEFT PANEL 21.2
AFT RIGHT PANEL 19.9
AFT UPPER DECK 15.1
AFT LOWER DECK 11.8
SCIENCE EQUIP BAY LOWER DECK 19.7
SCIENCE EQUIP BAY UPPER DECK 7.9
SCIENCE EQUIP BAY DIAG CAP 11.5
SCIENCE EQUIP BAY RT CLOSURE 1.8SCIENCE EQUIP BAY CEN-PAN 2.1
SCIENCE EQUIP BAY LT CLOSURE 1.8
SCIENCE EQUIP BAY INB-PAN 3.3
EQUIP BAY RIGHT 38.8AFT LG SUPPORT TRUSS 15.2
AFT OXID TANK SUPPORT 33.
MISC TANK SUPPORTS 19.5
AFT TRUSS & SUPPTS I.
S-IV-B ATTACH FTG 7.6
EQUIPMENT SUPPT AFT SECTION 34.
TOTAL FOR AFT SECTION ( 298.1)LAND GEAR CHOCKS 3.2MISCELLANEOUS 5.4
TOTAL FOR MISCELLANEOUS ( 8.6)MESS STOW & REL STRU 23.2
TOTAL FOR MESS STOW & REL STRU ( 23.2)ALSEP REMOTE DEPLOY 31.4
TOTAL FOR ALSEP REMOTE DEPLOY ( 31.4)DESCENT STUCTURE 1.3
TOTAL FOR DESCENT STUCTURE ( 1.3)TOTAL FOR STRUCTURE ( 1014.8)
2. PROTECTIONTHERMAL PROTECT AFT 1.3
TOTAL FOR THERMAL PROTECT AFT ( 1.3)BASE HEAT SHIELD 0.6
TOTAL FOR BASE HEAT SHIELD ( 0.6)UPPER SHIELDING 56.4
UPPER INSULATION 27.6
UPPER JSF 0.4
UPPER SUPPORTS 4.4D-57
JSC-26098SIDE SHIELDING 25.9
SIDE INSULATION 88.1
SIDE JSF 3.6
SIDE SUPPORTS 4.9
LOWER SHIELDING 17.3
LOWER INSULATION 30.4
LOWER JSF i.
LOWER SUPPORTS 4.7
RBHS SHIELDING 30.9RBHS INSULATION 66.3
RBHS JSF 6.8
RBHS SUPPORTS 60.1
OUTRIG SHIELDING 11.6
OUTRIG INSULATION 9.8
THERMAL PROTECTION 10.6
TOTAL FOR THERMAL PROTECTION ( 460.8)
TOTAL FOR PROTECTION ( 462.7)
3. PROPULSION
PROP TANK INSTAL 488.8
PROP FD DISCONNECT INSTAL 5.7
PROPELLANT PLUMBING 45.8
HELIUM TANK 113.9
PRESSURIZATION PLUMBING 68.1
ENGINE & MISC 368.7
TOTAL FOR DESCENT PROP SYST ( 1091.)
TOTAL FOR PROPULSION ( 1091.)
4. POWER
BATTERY DESCENT 670.3
ELECT CONTROL ASSY 39.5
ELECTRONIC UNIT 3.2
GN&C HARNESS ASSY 2.3
ECS HARNESS ASSY 0.i
INSTR HARNESS ASSY 0.7
EPS HARNESS ASSY 1.6
PROP HARNESS ASSY 4.6
EDS HARNESS ASSY 6.9
MULTI-SUBSYS HARNESS 31.3
EPS INSTAL HARDWARE 12.3
DELTA WEIGHT CHANGES 5.
EPS DESCENT STAGE 8.6
TOTAL FOR ELECT POWER SYST (786.3999) _
TOTAL FOR POWER (786.3999)
6. AVIONICS _DECA 13.1
TOTAL FOR STABILITY & CONTROL ( 13.1)LAND RADAR SECT 43.2
TOTAL FOR NAVIGATION&GUIDANCE ( 43.2)ECS SENSORS 1.8
PROP SENSORS 2.7
MECH DES SENSOR 1.9INSTRUMENTATION SENSORS 0.3
TOTAL FOR INSTRUMENTATION ( 6.7)
TOTAL FOR AVIONICS ( 63.)
7. ENVIRONMENTDISPLAYS & CONTROLS 3.3
D-58
JSC-2GO£8
TOTAL FOR DISPLAYS & CONTROLS ( 3.3)DESCENT 61.1
MESA MODULE 166.9
TOTAL FOR CREW PROVISIONS ( 228.)INERT DESCENT STAGE LM 92.7
02 SYSTEM 60.
H20 SYSTEM 22.6
GLYCOL SYSTEM 3.
PLSS 02 RECHARGE 8.2
LIOH CARTRIDGES 9.1
TOTAL FOR ECS ( 195.6)
TOTAL FOR ENVIRONMENT ( 426.9)
8. OTHER
INNER CYL ASSYS 97.4
OUTER CYL ASSYS 88.7
CARTRIDGE ASSYS 24.5
JSF PRIMARY STRUT 4.8
INNER CYL ASSYS 15.2
OUTER CYL ASSYS 14.5
CARTRIDGE ASSYS 37.6
HONEYCOMB PANEL AS 40.
BUMPER ASSEMBLY 1.2
HUB ASSEMBLY 5.
JSF LANDING PAD ASSY 0.7CROSS MEMBER TUBE ASSY 27.1
SIDE BRACE TUBE ASSY 41.
MISC DEPLOY COMPS 8.4
JSF DEPLOY TRUSS ASSY 5.9
DEPLOYMENT SPRING 3.2
LOCK SPRING ASSY 1.4
DOWN LOCK LATCH ASSY 2.8
CRANK CAM IDLER 2.1
SURFACE PROBE MECH 7.2
JSF MECHANISMS 0.2
THERMAL INSUL LAND GEAR 46.3
EGRESS LADDER 6.7
JSF EGRESS LADDER 0.4
JSF INSTAL PRIMARY STRUT 1.5
JSF INSTAL SECONDARY STRUT 0.3JSF INSTAL LANDING PAD 1.8
JSF DEPLOY TRUSS 0.3
JSF LG INSTAL 0.2
TOTAL FOR LANDING GEAR INSTALL ( 486.4)DESCENT EXPLOSIVE DEVICE 14.2DESCENT STRUCTURE 10.4
TOTAL FOR ELECT EXPLOSI DEVICE ( 24.6)PLSS BATTERIES 33.6BPS INSTALLED HARDWARE 2.3
CREW PROVISIONS 78.9
TOTAL FOR EARTH LAUNCH GFE ( 114.8)VARIOUS UPDATES -14.8
MFG VARIATION AT WHG -9.6
TOTAL FOR MFG VARIATION BY VEH ( -24.4)
TOTAL FOR OTHER (601.4001)
i0. NON-CARGO
UNUSED DPS PROP 348.9
TRAPPED DPS 76.3D-59
JSC-2G098
DISP & MALFUNCTION 337.7
TOTAL FOR UNUSABLE PROPEL MAIN ( 762.9)
TOTAL FOR NON-CARGO ( 762.9)
ii. CARGO
SCIENCE EQUIP 1099.1
TOTAL FOR EARTH LAUNCH GFE ( 1099.1)TOTAL FOR CARGO _ 1099.1)
12. NON-PROPELLANT
COOLANT 2.6
GOX 93.8
RESIDUAL WATER 0.4
TANKED WATER 408.
NITROGEN DSC H20 TANK i.
HELIUM DPS 52.2 -
TOTAL FOR LIQUIDS & GASSES ( 558.)
TOTAL FOR NON-PROPELLANT ( 558.)
13. PROPELLANT
MAIN DELTA-V PROP 18798.6
TOTAL FOR MAIN DELTA-V PROP ( 18798.6)
TOTAL FOR PROPELLANT ( 18798.6)
GROSS VEHICLE WEIGHT 25664.8
D-60
APOLLO SPACECRAFTPRIMARY REFERENCE: APOLLO
SPACECRAFT OPERATIONAL
DATA BOOK, SNA-B-D-027( I ),
REVISION 3, AMENDMENT GN,
FIGURE 2-3, APOLLO SPACECRAFT
REFERENCE DIMENSIONS,
< 408. ? > < 278. 6 _ 16 APRIL 1971.LAUNCH ESCAPE SYSTEM SERVICE MODULE I(LES) (SM)
< 338.0 1R 15H'00 SPACECRAFT133.5 _"_ > \ I LUNRRMODULEADAPTER/COMMAND MODULE(cM)
(SLA ) --(3GG CU FT PRESSURIZED) i
ESCAPE _11_.7
MOTOR I "TOWER i Ie8 00
JETTISON / "_'"
I _±_ kl Ji.......x_ _ ha''- i' ILUNARMOOULEIo_ 0 II "'_. ii (LM) I
26. eD I _ /! ' II "'"" ,_ DESIGN I_)
! I< i' I ENVELOPE I
' ' ' ' J ' -- xs280.O ] Lxs83.,4 _ ,0 188 XAlt33.5XS195.2 8 ° 58
INCHES XC133.5 <----162 04 ENGINE
• -I GIMBAL
STATION
NOTE: ALL DIMENSIONS XA1000. 0
ARE IN INCHES. XCO. 0 '< 83S. 0
! co< 982.2 >i o
I
XA1H8H 2 APOLLO SPACECRAFT X8502.0 ro• (D0
8POLOROI CCSO WH 2LI AUG 93 o_I
APOLLO LUNA_ HODULE
NOTE:riLLO_MENSIONSIIIIIII aeEIN INCHES.I
0 20 40 60 I
, XE512.25
- TI
wlNoow -- RSCENT STAGETO BOTTOM
lit 001 OF ENGINE
NOZZLE
12.291 L, _ _-_ , XE200. 0?
' _L-T___yB8"8G_L/___?l' ' I\'\, ,116.01_1__ _i.,.,...,...t_;......._., __a/'_'_X DESCENTSTAGE/ XETB.8_gBRSE
I l?.as (REF) I, 8.751 (REF) I /--GROUNO LINE o
167.570 > mo¢D
RPOLDR06 CCSD WH 23 RUG 93 co
NPOLLO SPACECRAFT(i _"I_ I ( 1861 )
REFERENCE: NASA PROJECT APOLLO WORKING PAPER NO. 1031
ces RPOLLO SPRCECRRFT WEIGHTS RS OF OCTOBER 2, 1961 228"O
150" DCM 116"0
SM (+ ..... F---i....'<
,, '\I '.
ADAPTER I , , , , I _"_-.Z ....._/'ILEM 0 100
_ INCHES
-- 170"0
,c G½1" >
TOTAL LAUNCH WEIGHT = 58220 POUNDS
7_POLLO SPnCgC_NFT
( 1968 AND 1971 )
q_
I ;
....... _ " P--_-_F_'IF ..... *:
I ,,INCHES
154"D t l C_260"0 CO
< 982.2" oI
TOTAL LAUNCH WEIGHT = 108992 POUNDS (1968) ro
116265 POUNDS ( 1971 > 0CO
RPOLOR00 CCSD WH 25 RUG 93 o_
APOLLO SATUI H VS-IC ENGINE INSTRLLRTION
396.00 OD
S --STA 357.88
BHD TAN
FRIRING (4)---_ /(TYPICAL) //
/ SCALED 18.00I f
i
STA 216.687 --_-- STR 225.00
L 15° 112.00
UA 55.00 STA 100.o0
STR 81.277 ___ GIMBRL-- STA 48.50
103.00
0 --STA -I15.494 r._.CO
INCHES (3140. OOO I
F-I ENGS (5) , , , , , , ro(1)8 180 o
INCHES (D(3O
IFIPOLOR25 CCSO WH 25 RUG 93
NOTE:riLL.ASS OATRPOINT DESXGHHBSS SUHHnRY .E,:Eo-2_-,5,5..oG_. ,_.SKYLBB PROGRAM PRYLORD INTEG
IS IN POUNDS. (l_l_ SKYLAB SPRCECRFT SKYLRB WEIGHT GROWTH STUDY
FUNCTIOHRLSYSTEH CODE I:1 B C D
SKYLAB SPACECRAFT( LRUNCH CONF [DURRT ION )
..._......s_..R.u_.T.u.R_.....................I 2_5_GIs_981.......__98I'__ '_ ..._'_......LEGENO:2. PROTECTION 67 1005 137 489 """
........................................................................................................................... PS IS PRYLOBO SHROUDi.-" im m iii
..........................................................................................................................._':'18 B"_I_-'_-''-'--ii-'''-I_' .TM IS BPOLLO TELESCOPE MOUNT
,.,._..;....P.R,.,O.p,.UL...S.,I...OU........................- ................._" ................_ ................._" ..... ""- MOB IS MULTIPLE DOCKING MODULE
.......................................................................................................................... RN IS BIRLOCK MODULE
4. POWER 10 10505 166B 4504 OWS IS ORBITRL WORKSHOP
..........................................................................................................................• "'"''"_.,... IU IS INSTRUMENT UNIT (OF BOOSTER)
....................................................................- - - I"-_T" --'i_---.O._.L----------_ o.s ,_
5. CONTROL - [.....;s"'_....H- .... -.""I"_2g_iOi/_iS/,ihE_ii.....................C................2'2}........i'N_'i......2__9_
..B.......qT..H..E..R......................................e.3e.............9..?..s...............07............33.8
_, ...9..:....GR.OWT.H...................................-.................-.................-.................T......
...........................................................................................................................DRY HI=ISS 25473 2191 8541 41735 3 1184._ XLV2746.5kl......................................................................................•.................,................. I
10. NON-CRRGO _ -- -- -- NOTE:RREIN RLL DIMENSIONS I I .... I .... I APPRoxXLV2831"5"_...................................................................................... INCHES. 0 _88
INCHES
I_.....CA..R.._ q ..................................... _ .............. 2.'_..78. ........ 51.(_._ ........... 5.5.9. SKYLDRBI CCSD WH 29 JUL 91
NOTE:............. / i / i
..............IHER.T....HB.S.s............2s.__._......e4..s..97.......!.3._ft.5.......4..e.e.9_..........R........P.O.Y.L..o.AD...S.HR.OU.D...<..PS..)......................................................................................
..................................................................................................................................B.........F)._..O..IJ_.Q..._E.LES.C.(_R.E...t!g._J.N.!...K.@TM.._.................................................................
.I2...,,NO...N.-.PR..gP.E..L..L..RU.]T..............-................-.................-..............?.?..09..........C........M..U..LI.I.F_.LE....[_P._K._.NE ,F).D.F_P.IE.R..(.t!P.F))............................................................
.....................................................................................................................................D.........A.!.R.L.OC.K....M.O..D_.UE.../.F)..M.._........................................................................................
.L.3......P.R.qP..E_..L..O.U.T..........................-..... - - -
ZZZil.ceos.s........ss............25.4._."-"-_......2._._._'-"_......._.3._.'--'-_......
SKYLMPgl CCSD WH _0 BUG 93 oo
NOTE."aLL,RSS OATR_POZ.T DES[CH HR$S SUHHREY REF:EO_._-._,_ ,o_E,..,,,IS ]H POUHD$. (I.1,1 SI<YLRB SPRCECRFT SKYL_e PROGRRItPRYLORO[HTEGSKYLRB MEICHT CROMTH STUOV
FUNCTIOHflLSYSTEH CODE E F
SKYLFIB SPRCECRFIFT
...I f....S._..._.U,.C. _U,_,.E "......................... _,.,_,_, ...._e._ ].] "...................................... (ORBIT CONF|GURRT|ON)
NOTE: SOME OlMENS|ON$ MERE RCRLEO
""E:'"_'i_i'_Ti'_'fi.......................§'8'2.........i_'§'_'......................................,Fo_oCOH.HO ,,o...,..., o.,..,...o.,.................................................................................................................. ......... _lNO SERVICE O0_IE RI$1tLII;HHENT ItEOULT$ FO0 THE_OOULE (CSit) OOCKEO. I;PRCE-FR_IJORK BEI"UEEN THE L_JNCH
RTI1 SOLAR RRRRY AND THE ORBIT CONF|GURRTIONSo
/_ :)SO, N1 IO PBESSUR[ SKIN
::::l : : :l:::::: o,.. .,,.o:'"o...,:::.,o.,:::::::::::::::::::::::::::::::::::::::::::::i 2222222::22::2::2:22:::2:::::2:222 / /t.RRR*RR , ,B
r 1 I' P ,I • ' ' I
"_;_-R_Y_.......................I.........:] ........:.......!.................] ................. ....... _......_..........xvles._ (nlceon_t[o*olo/n_om?ORSXl. I i............. immmmmm m m i
X_I I IS, _ KXT[#OS I.oeo FROM OUT[R SURFRCI[ R ODRY HflSS ½399 53206 . o, ,Rm.HE SXI.,. XLV=?_S,.
10. NON-CFIRGO - 391e ,_--.-xvels.s I NOTE: RLL OU1ENSIONS .__j.......................................................................................................................... xazeoe.o I , , , , I , , , , IO INCHES _eO I RRE IN INCHES, HPPRox,XLVES31"5.............. , ................................... , ................. , .................. , ................. , .................
I _.,%.,C..,A.RG. q .................................... -, .............. _.._._ ..................................... SKYLORS9 CC$0 _4H 29 JUL 91
HOTE:............. m m m m
..............!.H.E._T....H._..S.S............_.3..9..s........6._..?..3...s......................................L........_.........LN..S.T...R.U._E._T...._N..LT....¢...L_.)......................................................................................
................................................................................................................................Z.........LH_..._.._.S._._._....F.._._..._...LH..R..O.U.G_....F.....__._....F.._._..e_.,.....L_...n__....]._..7._...........3. PROPELLRHT ...........-....... lqG5.........................................................................................................................T..HE..T.O.T._.L..._.F....I._.6_.A._...P..QU.HD._...C.O._..P..R.R.E.LT._..J._._._.7..._H..............
................. ...................k..._£.T.O.B.E.R....I._.6._......................................................................................................GROSS HflSS _.399 78195
( R+B+C
.................:...!..S.s._._..)..............................................................................................................................................................................................................................................
SKYLMPB;_ CCSD WH 2B RUG 93 _)Ch
oo
NOTE:ALLMRSS HnS_ SUHHnRY on_nK_POINTIS IN POUNDS. SKYLAB PAYLOAD SHROUD ( PS )
.....................................................................t _____' 4:_____............................................._.............i_ .._;..._.__...................."".,;...._...,..,..__,,..I. STRUCTURE ...............................................................................................................................PRIMRRY STRUCTURE _ 23853 ELECTRICAL WIRING : 18 SEPARATION SYSTEM : 898
..........._._qN_!..._!E_._._..........i.........._._._..........................................................................i............................................................................................_.....................EQUIPMENT SUPPORTS 31 .................................................................l............................................................................................,.....................
INSULRTION RND PRINT , 158 : ......................................................................!.....................
.............................................................................................................................................................................................................................................................i.....................
......................................................................:.............................................................................................i..........................................................................................._...........i.........: 9. GROWTH
.................................................................................................................................................................._.........................................ORY....MC.SS..........................i......_._Z3.....................................................................................................................................................................!...................... :
I ....................................................................I......................
................................................................................................................................................................_.........._........_ 10. NON-CRRGO ( -5. CONTROL ...........................................................................................
i ....................................................................} ..................................................................................................................
THERMAL CONTROL _ 67 INSTRUMENTRTION 2TN_T MRSS
: 12. NON-PROPELLRNT -
3. PROPULSION _ .........................................................................................................................................................................................
..................................................................................................................................................................._.........._.......'"i'3"_"_R6_CL'RN_............................................_.........?. ENVIRONMENT
.....................................................................f..............................................................................._.................................................................................................................
......................................................................i............................................................................................}...............................................................................................................I
......................................................................}..........................................................................................'......................GROSSflASS _ z5_73I
SKYLMP03 CCSD WH i_ NOV 92
NOTE:ALL.ASS Hn_ _UHHARY OATAPOINTIS [H POUNOS. SKYLRB APOLLO TELESCOPE MOUNT (RTM)
.................................................................................................................................................................................................................................................................(...........9_.3.......!._...._R_.T_B_....................................( ........_._.$8......._.,...._9_g.R.....................................................!.e._5 ..... _,....O.!_g_...................................................................PRIMARY STRUCTURE q169 ELECTRICAL EQUIPMENT 3239 ATM POINTING MECH 973
SECONORRY STRUCTURE 235 ELECTRICAL WIRING 3295......................................................................_ ..........................................................................................................................................................................................7.....................
EQUIPMENT MOUNTS 629 SOLAR ARRAYS 2765
..........._._&T.LqH...._.q..._fl_._ .................!.26.5................_9._E.._.RRA._..._.X ......................_._._...........................................................................i....................................................................................................................................................................................... } ........................................................................................... ;......................
9. GRONTH
...........................................................................................................................................................................................DRY MASS 21919
_._._._._i1i1_._._i_TZ.Z_..._._._._._Z.1._.1_._.._/_1._._Z1_...._Z_-_._._.._._._`_.._._./_.__._L__.._.._._._,__._.__._._._._._,_/Z_?_Z_L_._i_:__:_aR_a...................................i..........:........
................................................................................................................................................................ e ............................................................................................ : ......................
........................................................................................................2. PROTECTION t005 62 RViO'N'i'C'g ...................................... ( ....... 2"9"i'[ ................................................................................................11. CARGO 2778
ENVIRONMENTAL PROT 1085 INSTRUMENTATION, COMM 788 EXPERIMENTS AND INSTL 2?78
......................................................................................................_.q._.o.A..__................................................_1._.......................TN_M R.S.--.S..._.-- ...........2_...
..................................................................... :. ..................... . ................................................................................................................................................................ :......................
3 PROPULSION
......................................... _.........._._........................................................................................................................................................................................... ?. EHVIROHMiNT 1£. PROPELLANT -
..........._B.g._...Rg._._._.!.N_S................................._.27................................................................................................
..-...-',.-.".-'.'.-'.'...".-.'.'.-."-'.'.','.'-'.'.'"-'.'.'.'".".'.'.".'.".'.".".'.'""'.'.".'.'.'.'.'."."'.-'.'"'.",'.".'."" "_'..'_ I0
• " SKYLMPO_ CCSD _H 10 N V 92 m
NOTE: ALL MASS H_ _UHH_Y DATA_POINT
IS IN POUNDS. SKY LAB MULTIPLE DOCKING RDRPTER (MDR)
i_8 e_ 0_gR..............................................(.............8_'".................................................................................................1. STRUCTURE 4798 4"i'"'P'6W'ER ......................................................................PRIMRRY STRUCTURE 3G55 ELECTRICRL EQUIPMENT 1881 , DOCKING EQUIPMENT 87
..........._._g_._..._!R._._._ ........................_.e............._.g_.R.!_.A_..._-_.NC..........................._._ ...........................................................................................................---'---------^---_.U._._._4._L._V.<r.U_._>...... SSS ...................................................................................................................................................................................
INSULATION AND PRINT 390............,.........................................................F ..............................................................................................................................................................................................................
3. GROWTH
: DRY MRSS 85_1
................................................................................................................................................................._..........c.........._T_6__ .......................................................................................................................................................5.,...._.!_o_ ..........................................................................................................................................................
....................................................................._.........._g_......._2_ioffi_g ......................................_..........2§o.....iii__g_ .............................................(......._ig_ ......_...._._L_c._._.P._..................................................................................................................................................METEOROID PROTECTION 137 INSTURMENTRTION, COMM 238 EXPERIMENTS AND INSTL 518H
.....................................................................> ...................................................................................................................
INERT MRSS 13G_50
.....................................................................m..............................................................................................................................................................................................................
12. NON-PROPELLANT
3. PROPULSION
.............................................................................................7, ENVIRONMENT _ 1821 I_. PROPELL_NT _ -
ENVIRON CONTR SYS 8_H70CREN RESTRRINTS , ,
STOWRGE RND SPRRES 37?
CREN SYS CONTRINERS 20H
CREN SYS SUPPORTS 12G
.....................................................................t.................................................................................................................|....................................................................._ I
: :
• ...................................................................... i ...................... _ROSS MRSS i 13GH5 mi :
SKYLMP05 CCSD NH _0 NOV 92
NOTE:RLLMRSS SUHHRRY ORT.POI.TIS IN POUNDS, SKYLRB RIRLOCK NODULE (RM) @
PRIMRRY STRUCTURE 10101 ELECTRICRL EQUIPMENT 1904 , RTM DEPLOYMENT MECH 398
..........S._ER_._..._._R._._._........................8._.............._kg£_.R.!._L._.t_LN_........................_6.00...............................................................................................EQUIPMENT SUPPORTS 3G32
IHSULRTION RHD PRINT _00 ...................................................................... . .....................
.................................................................................................................................................................. } ..................................................................................................................
: 9. GROWTH
: DRY MRSS _i?s5
................................................................................................_7i6_R_C ........................................._..........: ..........iKN6_:___ .............................................: .........
..................................................................... : ...................... i ...................................................................... } ..................................................................................................................
....................................................................._..........qg9........_'2"'"_'i'6"fii'_'g......................................_.......i_9"i......_'i'Y"_'gg65............................................._..........599........Z,...._._._.:!._ .............................................................................................................................................................................................................................................METEOROID PROTECTIOH { _89 INSTRUMENTRTION, COMM 1½91 EXPERIMENTS RND INSTL 559
......................................................................_................................................................................................................ INERT .RSS _229_M
12. NON-PROPELLRNT 7709
..................................................................... i............................................................................................................................... E_Y.!.R.9._..._O._&..G.R_..............._........_.7_9....
:3.PROPULSIOH ...................................................................................................................................................................: ......................
=
...................... ,...................................................................... _........... _.........7. ENVIROHMEHT ( 28697 1_, PRDPELLRNT {
........................................................................................................_U._.T.Eou_.EU._O.q..._.qU.:R.O._...........!_e.5o................................................................................................
.................................................................................................._._W..._.ES.:._R.:U.:.S...............................!.7.O...............................................................................................STOWRGE AND SPRRES 504
CREW SYS CONTRINERS IHI
CREW SYS SUPPORTS 32
.....................................................................:.......................................................................................................................................................................................:...................I
: GR088 HRS8 : 5ooo3 m................................................................... I ........................................................................................... ; ...................... ) ..................................................................... I ................... 0
SKYLMPOG CCSO WH 10 NOV 92
NOTE:riLL.ASS URHnRY OATAPOI.TIS IN POUNDS. SKYLRB ORBITRL WORKSHOP (OWS) @
..........._._.!._B_..._J.R_!9.B_..................IB940 . ELECTRICAL EOUIPH.EHT ............28.38.................................SECONDARY STRUCTURE 4622 ELECTRICAL WIRING 3084
..........._g,U.I.P.Mg._..._Y.PP.qR._......................_.2_0................Sq_...AR.Rfly.S.....................................3._Z_........................................................................._......................
...........!._RZ._.q_..._q..._.NT................._._._................_h_R..._._.rA.Y...q_P_P._....................._._ ........................................................................._..........................................................................................:......................I......................................................................f......................| .....................................................................
8. GRONTH ( - 1
DRY HRSS _ 5320G........................................................................................... , ............................................................................................. • ..................................................................... I .....................
5. CONTROL _ - 10. NON-CARGO ( 3810FOOD ACCESSORIES 3810
........................................................................................................................................................................................................._."P..._P._T._._.n.ER.S...................................................................................................................................... I ........................................................................................................................................................................................
..................................................................................................................................................................._.......ig6g......Fi;6Ng6g......................................................_'gg2......._...._._qL_._.!._................................._.......!._......._.,...._._.!._I_........................................................................................................................................................o METEOROID PROTECTION 1282 INSTRUMENTATION, COMM _ 130S EXPERIMENTS AND INSTL 7622, : INERT MRS8 64738
..................................................................... i ............................................................................................. : ...............................................................................................................
......................................................................_..........................................................................................._........................l a_._9_.Rg.P_8_[ ..............................!.!._._.......................................................................,............................................................................................_.................................._.q_>._...._.u_.e..._._..._._._..................._._ ....
: FOOD 2402
.,._.:...._g._Y._._._.................................(......._._8.........................................................................._.................................._.qzA_._.E..._.!_R.................................._._ ....ATTITUOE CONTROL SYS 3?95
RTT CONTR SYS SUPPTS 1243
I
........................................................................................................._._.!.n...A._._9._._R.g...Sy.S................_!._._................._Z!._.!_.g..._O.U!R.%....S_._................!._._....
........................................................................................................P._!8_g.g...w.R_.g_..._Y._._ ................!.I.9.9....................PR.q_.g.Kg.A_._...8_D..._8_.............................WASTE MANAGEMENT 2254
: CREW RCCOMMOOATIONS 855
AND CONSTRAINTS
STOWAGE AND SPARES : 288?
: CREW SYS CONTRINERS 3135 :: CREW SYS SUPPORTS : 2070 GR088 HR88 _ 78_$5 m
SKYLMP08 CCSD WH I0 NOV 92 m
./.f .... (LRUNCH CONFIGURRTION)• i" _ LEGEND:
t -'I - PS IS PRYLORD SHROUD/
................................................ RTM IS RPOLLO TELESCOPE MOUNT
"'_- = MDR IS MULTIPLE DOCKING MODULE
_"_,. -. _- RM IS RIRLOCK MODULEONS IS ORBITRL WORKSHOP
<-_---1?8,0----e .... "_---.. [U IS INSTRUMENT UNIT (OF BOOSTER)
i _T_---fl_-----MO_ _ O_S
..........q..... ;;; --- , ,, [--z _ II II _
" "" " _ I I II II \ f_\
. \_l _ / I I i I i ,x ,II II
\ II II --II II
x II II
189,3 260.0D IXLV2746.5
×LVB899.3 118_,0 >
RRE IN INCHES 0 200 mINCHES o
SKYLDRO1 CCSD NH 25 RUG 93
@KYL_ HODULE@(LAUNCH CONFIGURATION)
< RTM 1< MDR ? RL >1-'I..........._i-E_E_G_T6 .......I.................................................II SHIELD EXTENDS OUT 3.e FROM II THE PRESSURE SKIN FOR R ITOTRL OF 12G.@O.
128.0D (SEE
NOTE RBOVE. )
I"-,4
(---------105•a-.--_ _---ATM PIVOT
e-------i17.0_ CENTER
IH3•I _ _._ ._c/_PRYLORD SHROUD (REF•)•
152.7 H7.0 .0 08.8
189.3 208.2-- 211.5
IIIII IIII NOTE: RLL DIMENSIONS RRE IN INCHES•
0 50 100 IN o
SKYLDRe? CCSD NH 25 RUG 93 m
SKYLNB SPACECRAFT(ORBIT CONFIGURATION) NOTE: SOME DIMENSIONS WERE SCALED
-- APOLLO COMMAND FROM REFERENCE DATA. THEREFORE,
AND SERVICE SOME MISALIGNMENT RESULTS FOR THE
MODULE (CSM) DOCKED. SPACE-FRAMEWORK BETWEEN THE LAUNCHBTM SOLAR ARRAY AND THE ORBIT CONFIGURATIONS.
j 260.000 ID PRESSURE SKINi (SKIN THICKNESS = 0.087)
- I FITM ROTATED 90 DEGREES MICROMETEOROID SKIN EXTENDS(FROM LAUNCH CONFIGURATION) APPROX 5.000 FROM PRESSURE
1 ! SKIN IN ORBIT (FROM B TO B).
Ii AL OUS >' -_ IU BG.O 575.0 --2G0. OD*
211.5 q
...-" SOLAR II
95.0 i _ /I ARRAY ARrl I' "xI I
l "" "- -- -- 13.84 11
"_ ' iN..... _- I -6B. 5S3
. ..'"" ] "XI_ I ARM r .... _,__-_1_2:t..... PIVOT
N_ II j..-'XLVB650.0 MOA iiXVI05.2 (MICROMETEOROID/RAOIATOR SKIN I I " "XAI 110.3 EXTENDS 3.000 FROM OUTER SURFACE A B
OF PRESSURE SKIN). XLV2THG.5
< 818.5 c_co
(------XV215.5 NOTE: ALL OIMENSIONS ' oI
XA1000.0 l,_,I,,_,I XLVe8BI.5- ro0 INCHES 200 ARE IN INCHES. APPROX. 0
_0-- K LD WH G AU co
NOTE: ALL MRSS ORTR POINT DES_GH HRSS SUHHR_Y1s IN POUHDS.
(_ RPOLLO-SOYUZ TEST PROJECT
FUNCTIONflLSYSTEH CODE A B C D RPOLLO-SOYUZ TEST PROJECT
........................................................................................................................... (DOCKED CONFIGURRTION)
...!._...._!.R_!_........................................Z.e@.9.......................................REFERENCE: RPOLLO-SOYUZ TEST PROGRSn, NOTE: SOftS OIflENSISNS HRVE SEEN SCRLEO
2. PROTECT I OH 233 SVSTE. DESCRIPTION flRNURL, CSfl ItI/ RNO RRE EST]flRTESo THESE OIflEHSIOHS................................................. •........................................................................ SOCKING "ODULE, SECT;OH 1, JSC, JRH IS?q. RRE FOLLO"ED BY (E).
RPOLL0-SOYUZ TEST PRSJECT, FRET SHEET,........................................................................................................................... RELEflSE NO. TS-S, leTS.
...S._...._._._.k_N........................................._............................................RPOLLO-SO_OZTESTRROJECT,I,,S,ST,O,FOR PRESS, 1975.
................................................. i ................. • .................. • ................. . ..................
...H._....PV.H.[R......................................................1._._........................................_o_sEo..R.o ooc,,No_RND SERVICE MODULE _MOSULE_I-.----SOYUZ SPRCECRflFT,_-b
.................................................. _................. •.................. • ................. _.................. (CSM) (OM)
....5._....C_.TR.q_.....................- ....................................
IS_.SO"'S'/"_'i_Nicg................................................8e.......................................I
I r°s"°Fss"°'E' 'E'...........................................................................................................................Ios.so--_ i?. ENVIRONMENT 967
-.................*-qi......-8-{-_E.R....................................................._'3......................................._..........................................................................................................................i _/ - _RRRRRR_
9. GROHTHI
Do ..............D_Y....HaSP.....................................H.!._.4.......................................TO_.SSS •
!._.,....NO.U_C.AR.GO............................................._............................................NOTE:,_O,,ERS,ONSI _'RRE IN INCHES. I
..........................................................................I I. C_RGO .... _.68 ..................................... RPSOOR_! CCSO WH _I _UG 9|
NOTE:.............. i
..............I.HE.R._...H.8.S.S.............................._ke .............................................._._....A_.L_.O...C._M.M_N._...n_..._.ER.V.I.C_...MO.O_.E..._.C.S_.?.........................................B. DOCKING MODULE (OM) (REF: ROCKWELL PRINTOUT, DOCKING
k._._...N.O_._R.O_E._._...............................I._._...........................................................M.qP._.b.....SK._...U..!._....k.5...M_._..._.9_._._.)..........................................................C. SOYUZ SPRCECRRFT
.L_._..._R_.E_._U._........................................_........................................................................................................................................................................................................
RPSOMPSI CCSO WH Z8 RUG 93 so
APOLLO =SOYUZ TEST PROJECT(DOCKED CONFIGURATION)
REFERENCE: APOLLO-SOYUZ TEST PROGRAM, NOTE: SOME DIMENSIONS HAVE BEEN SCALED
SYSTEM DESCRIPTION MANUAL, CSM Iiii AND ARE ESTIMATES. THESE DIMENSIONS
DOCKING MODULE, SECTION I, JSC, JAN 1974. ARE FOLLOUED BY (E).APOLLO-SOYUZ TEST PROJECT, FACT SHEET,
RELEASE NO. ?5-9, 19?5.
APOLLO-SOYUZ TEST PROJECT, INFORMATIONFOR PRESS, 1975.
APOLLO COMMAND DOCKING
' AND SERVICE MODULE _-, MODULE--_1 e--- SOYUZ SPACECRRFT----_
/(CSM ) (DM )
-- 154.00
I _ --86.00 (E)
- ._.__ ,..... .
V_ /" LRR RRRRY
_.--- 124.0 --_
988.8?4 _ _ 280.789
793. 583 (.-03("3
lull I ailll I
I 18 INCHES 100 r_
NOTE: ALL DIMENSIONS 03ARE IN INCHES. 0
to- APSOOROI CCSO WH IT RUG 93 co
NOTE: RLL "aSS ORTR POINT DESIGH HASS SUHHA_Y REFERENCE: 0V-183, FLT 10
IS IN POUNDS, (_ SPACE SHUTTLE VEHICLE (SSV)21 FEB 90
FUHCTIONflLSYSTEN CODE R B C D
"'i'2"'"Si'RUC'fb'Rg ..................... 632'B? .......52'599'"25"Hg"6_ ................... SPRCE SHUTTLE VEHICLE (SSV)
........................................................................................................................... REFERENCE: DRRRING SHUTDRO!
..._._..._._,_._._._._°_'_T'_" ................ 28.03._ ......... 595._ ...... 52._.i._ ..................o
Xo " 3"....................................................................................................................... X 985 875 NSTE RLL SIMENSIONS 1317 el
N. POWER I 16628[ 372/ 2546[ x. '.e_s ..Ei.i.c.es. I"
.................................................I.................t..................I.................t.................i °.......................................... • _ 209 2S58.SS
5. CONTROL 2785 - H655 TOx,o, 741-5._ INCHES................................................. I................. 1.................. !................. I................. (7_s.s> l _ _,_
I t I t .... .o-..- ,_ iI....................................................................................................................... L_eO 0 _ ..........i ,,,, . �-............r........._..VIONICS _ SB _ .._ _ _....................................................................................................................... F _ ......
7. ENVIRONMENT 9H5_ - ?SG ' i_6.5 , -- _ ! • $1I.?_ i
....................................................................................................................... Z 0 S _, • _RTTRCH XflIeS.SS /8. OTHER 9G_2 eS?6 69268 _, ,'-.. c. .Tt_c.
................................................. I ................. 1.................. r ................. /................. _ .... _._.__,_._ .L-:.'E___.!_ XTSOS.S?S XT_eO.SO ' f i /
9'"C'R_"_................................._2_ _11_.'" "-JI I I i IL/ --i............... I I. X, I I
o ...............P_.T...HPSS................_239T......68s.L:....3.8_.8_2..................J-'_""'"" _. _, ,__00._ _I73.025
iI_,..........................................................................................................................NON-CaRGO I_3_S B_O_ - _T_ _0, _ XB.......................................................................................................................... 32 2 2000.25
1......................................................1, CARGO 285.52 ........................................................NOTE:
.............!HER_...H_SS......B. EXTERNRL TRNK (ET), LWT-001
1.2_..NON.zP.ROP,EL.LR.NT........92.39 .......9.9H._ - C. SOLID ROCKET BOOSTER (SRB), (2_, STS-31
!._._..,._O.Pg._.A.NT................._.eS.Te....sZ3.3_3._.2.L_s.Ge............................................................................................................................................................................
CROSS HRSS 2_9502 654075_B00552( R+B+C = I
H50HJ29)
............................................................................................................................................................................................................................................................................. 0
SHUTMP01 CCSD WH 20 RUG 93
NOTE:ALL.ASSORTA_POI._ Hn_ SUNMA_YIS IN POUNDS. _ SPACE SHUTTLE DISCOVERY OV-t09, FLT 10 2t FEB 90
..Z._..............i....i............._._....i...._.........................................................................(........_._._._._......._..._.:...._".E_.................................................................................................................................................................1. STRUCTURE .............................................................................. 1.6#.2#..... 8:....#.[HER ............................................. ( ........#.6_.2..........e.£AZ...q.R#._.......................... eu62.8 .............E_._._E..E#._._ ......................................... #.9_.#............. &#._#.[_#...#.NE..n_.x...#.Z_ ................ e#._#.............TE_....£8.q#.E...........................................2#.e#................E._#...#.qN_.R...AU#...#._.#._E..............._.e#._#..............R.A¥.L£A.D...EEO_.LS.[.£#.#........................._7.4...........w.[_...G.R#._.........................................t.#.es.#................#_.#.R...££U¥_...8.NE..q].ST.R....................L#5.e.............................................................................................
.............................................................................................................................................................................................._7__¥_ ..........................................._...........__
...............................................................................................................................................................................................................ORY....PR,SS..........................i...._._.#._9.Z_
".'.'._'.'.'.'.'._'.'.'.'.'.'.'.'.'.'.'.'.'_.'_.'_.';.'.';'.'.'_.".'.'.'."".'.'.'.".'.'.'._"".'.'.'.'.'.'."."._'."".'.'.'.'..'.'.'._'.""'.'.'.'.".'.'.'.''.'.'.'."+,'.'.".'.'.5,'.'.'.'.".'.'.'CONTROL.'.'.'_.'.'.'.'.'.'.'.".'.'.'.'.'.'.'.'.'."'.'.'.".i'.".'.'.'.'.'.'.'.'.'.'.'.'.'.'..'.'.'.'.".'.'.".'.'.".i'.'.'_".".'".".'2785,"."".".'.'.'.".'."".'.'tO,.'.'.'."".'.'".'.'.NON-CARGO.'.'".'.'".'.'.".'."".'._'.'.'.'.'."'."".'.".'..'.'.".".'.".".'.'.'.""..'."..'..'.'..'.'.'.'.".'_"'.'.'".'_._.__._.'."
........................................................................................................_.EA._E..._._.R_._.............................2._e.5..............E_._.O_O..._._.O.MO.D_._.!.O._........................e..
....................................................................................................................................................................................................EEEs#_._F_.............................................#_L
...........................................................................................................................................................................EF._F._F..._._E.RF.S.I#._#&.................I._._L.
..........................................................................................................................................................................................................No._z.C.Eo.EF._ER._........................................RESERV AND RESIS PROPEU 327_
.""_.i_._ _'_.'__0"."";'_"i_"i'._".".;..("._.___.."""."_";i._.i._._i__'.'"."'."'.'.".'.."..i..'.".."."._"."'.""__'_:"_J;;_ iZ_: _; K:::_INDUCED ENVIRONMENTAL 280£0 COMMUNICATION AND TRAC_ 15_1 • STS OPERATOR 30½9
..............._.RO._._._.I.Q_ ............................i ....................... DRTA PROC AND. SO.FTWR ............... 1.3,32.........................!.NE.R.T....MRSS ........................._._._._8.5...m GUIDRNCE NRV RND CONTR 967
.....................................................................i.................................L_T.RP._._._._._._._................................._._.....!e_....U_.g_._._................................#._._......................................................................._.............................................................................................................................._.q_._...PE_._.K_....P._._ ..................._._6......................................................................................................................................................................................................._N_.E#.[._U.[..._A#.s#.#..........................._.e_._....._,....E_.qE%.&I._................................._....._._e._............................................................................................................................................................................................
ASCENT PROPULSION £1305
..........._._DtZ.._A._._._...SY.&..£qM._._..........._._ ..............................................................................................................................................................................................RERCT CONTR SYS (RCS) 3212
CONTROLS SYSTEM I_11 USABLE, OMS........................................................... 23N 16......................................................................................................... _._._#._.#..._._._EM ........................ 669 .... U$.RB._....R._# ........................................ _5.6#...
, ENVIRONMENTAL CONTROL 5380LIGHTING SYSTEM......................................................................_............................................................................................2o3
: PERSONNEL PROVISIONS 1871
......................................................................_......................_....................................................................._......................_..........................................................................................I
' .....................................................................i.............................................................................................i.......................GR088 MRS8 2_95o2......................................................................'....................0
SHUTMPO_ CCSO WH _0 NOV 92 m
SPACE SHUTTLE ORBITER JSC-26098
DESIGN MASS SUMMARY (JSC FORMAT)ALL MASS IN POUNDS
I. STRUCTURE
SECONDARY FORWARD RCS MODULE 9.
FORWARD FUSELAGE-DOORS,MISC 436.3
FORWARD RCS MODULE-DOORS,MISC 33.CREW MODULE-DOORS,MISC 728.3
OMS/RCS POD-DOORS,MISC 2968.4
MID FUSELAGE-DOORS,MISC 117.5
AFT FUSELAGE-DOORS,MISC 505.7STRUCTURE - TULSA -PAYLOAD BAY 3008.6
DOOR ACTUATION - PAYLOAD BAY 186.
DOOR LATCH - PAYLOAD BAY 676.
RADIATOR HINGE&LATCH-PAYLD BAY 203.
MISCELLANEOUS - PAYLOAD BAY 580.SECONDARY CREW MODULE 1912.1
SECONDARY MID FUSELAGE 482.2
SECONDARY AFT FUSELAGE-BODY 1386.4
SECONDARY AFT FUSE-BODY FLAP 464.4
BASIC STRUCT AFT FUSE - BODY 7298.4
AFT FUSELAGE THRUST STRUCTURE 3182.4
BASIC STRUCT FWRD RCS MODULE 343.5
SECONDARY FORWARD FUSELAGE 493.7
BASIC STRUCT CREW MODULE 4213.6
BASIC STRUCT FORWARD FUSELAGE 4299.5
BASIC STRUCT MID FUSELAGE iii00.
TOTAL FOR BODY GROUP ( 44628.)RUDDER/SPEED BRAKE LWR SUP MEC 13.3OPERATING MECHANISM SUPPORTS 93.
RUDDER/SPEED BRAKE UPPER SURF. 324.5
RUDDER/SPEED BRAKE UP SUP MECH 15.1
RUDDER/SPEED BRAKE LOWER SURF. 319.OUTER PANEL TORQUE BOX 1406.7OUTER PANEL LEADING EDGE 88.5
OUTER PANEL TRAILING EDGE 287.7
STRUCTURE 61.2
TOTAL FOR TAIL GROUP ( 2609.)OUTER PANEL INTERIM SECTION 2291.4
OUTER PANEL TORQUE BOX 6357.4OUTER PANEL LEADING EDGE 188.2OUTER PANEL TRAILING EDGE 1306.7
SECONDARY STRUCTURE 2413.5
OPERATING MECHANISMS & CONTROL 382.
OPERATING MECH-ACTUATOR LOCKS 167.6 -MISC. PROVISIONS AND SUPPORT 112.8
ELEVON INBOARD SURFACE 1291.
ELEVON INBOARD SUPPORT MECH. 278.2
ELEVON OUTBOARD SURFACE 921.6
ELEVON OUTBOARD SUPPORT MECH. 339.6
TOTAL FOR WING GROUP ( 16050.)
TOTAL FOR STRUCTURE ( 63287.)
2. PROTECTION
TPS FIXED WING L.E. RCC 3663.4
TPS FIXED WING M.L.G. DOORS 313.8
TPS FIXED WING SURFACE 5566.8
TPS ELEVONS - INBOARD (WING) 1036.6D-82
dSC-2SOS8
TPS ELEVONS - OUTBOARD (WING) 802.2TPS FIN 969.6
TPS RUDDER/SPEED BRAKE LOWER 90.
TPS RUDDER/SPEED BRAKE UPPER 102.TPS FORWARD N.L.G. DOORS 135.7
TPS FORWARD R.C.S. MODULE 417.4
TPS FORWARD BODY 2208.3
TPS MIDBODY - PAYLOAD BAY DOOR 1075.2TPS MIDBODY 2688.7
TPS AFT E.T. UMBIL. DOORS 73.2
TPS AFT BODY 1053.
TPS OMS/RCS PODS 1436.. TPS BODY FLAP 943.4
TPS BASE HEAT SHIELD 407.
WING - INTERNAL 102.6
" TAIL - INTERNAL 11.5
FORWARD RCS MODULE - INTERNAL 194.3
BODY - FORWARD - INTERNAL 561.9
BODY-PAYLOAD BAY DOORS-INTERNA 366.3
BODY - MID - INTERNAL 1476.5
BODY - AFT - INTERNAL 212.2
OMS/RCS PODS - INTERNAL 449.6BODY - FLAP - INTERNAL 0.5
WING PURGE AND VENT 70.6
TAIL PURGE AND VENT i0.
BODY - FORWARD PURGE AND VENT 339.2
BODY - MID PURGE AND VENT 699.2
BODY - AFT PURGE AND VENT 343.7
OMS/RCS PODS PURGE AND VENT 21.4BODY-FORWARD DRN,WINDO,COND 125.4
BODY-MID DRN,WINDO,COND 36.1
BODY-AFT DRN,WINDO,COND 26.7
TOTAL FOR INDUCED ENVIRON PROT ( 28030.)
TOTAL FOR PROTECTION ( 28030.)
3. PROPULSION
SSME GIMBAL SYSTEM 1761.6
SSME HYDRAULIC SUPPLY 221.1
SSME-INSTL,HEAT SHIELD,GN2 PRG 1213.5PNEUMATIC SYSTEM - HELIUM 2100.4
ET PRESSURIZATION SYSTEM 164.4
PROPELLANT MANAGEMENT SYSTEM 38.
LH2 MAIN FEED SYSTEM 2014.7
LH2 FILL AND DRAIN SYSTEM 261.1
LH2-PRESTART COND, RELI EF, DUMP 376.1L02 MAIN FEED SYSTEM 2017.5
LO2 FILL AND DRAIN SYSTEM 242.3
LO2-OVBRD BLEED,RELF,POGO SUPP 123.3SSME 20771.
TOTAL FOR PROPULSION - ASCENT ( 31305.)OMS ENGINE INSTALLATION 638.6
OMS PRESSURIZATION SYSTEM 759.
OMS FUEL SYSTEM 839.5
OMS OXIDIZER SYSTEM 849.9
TOTAL FOR PROPULSION - OMS ( 3087.)
RCS AFT POD ENG. INSTALLATION 601.2
RCS AFT PRESSURIZATION SYSTEM 329.RCS AFT PROPELLANT SYSTEM FUEL 379.2
RCS AFT PROPELLANT SYSTEM OXID 371.6
D-83
JSC-26098RCS FWD MODULE ENGINE INST 869.
RCS FWD PRESSURIZATION SYSTEM 148.
RCS FWD PROPELLANT SYSTEM FUEL 265.3
RCS FWD PROPELLANT SYSTEM OXID 248.7
TOTAL FOR PROPULSION - RCS ( 3212.)
TOTAL FOR PROPULSION ( 37604.)
4. POWER
CONVERSION EQUIPMENT 242.7
CONTROL UNITS 1154.5DISTRIBUTION EQUIPMENT 532.6ELECTRICAL SUPPORTS 956.
ELECTRICAL INSTALLATION 654.6ELECTRICAL CABLING 5327.7ELECTRICAL CONNECTORS 106.5
CABLING INSTALLATION & SUPPORT 1853.4
TOTAL FOR ELEC. CONVR.& DISTR. ( 10828.)HYDR POWER SUPPLY EQUIPMENT 201.
HYDR DISTRIBUTION & CONTROL 1049.2HYDR TEMPERATURE CONTROL SYSTE 599.8
TOTAL FOR HYDR. CONVR.& DISTR. ( 1850.)APU EXHAUST SYSTEM 82.2
APU WATER SYSTEM 92.3
POWER GEN SYSTEM FUEL CELL 1088.
PRSD OXYGEN 987.9
PRSD HYDROGEN 954.
APU POWER SYSTEM 366.3
APU FUEL SYSTEM 325.2APU LUBE OIL COOLANT LOOP 46.1
TOTAL FOR PRIME POWER ( 3942.)
TOTAL FOR POWER ( 16620.)
5. CONTROL
COCKPIT CONTROLS 70.4
SYSTEM ACTUATION-BODY FLAP 360.7SYSTEM ACTUATION-ELEVON 1097.3
SYSTEM ACTUAU-RUDDER SPD.BRAKE 1256.6
TOTAL FOR SURFACE CONTROLS ( 2785.)
TOTAL FOR CONTROL ( 2785.)
6. AVIONICS
C&T ANTENNAS 362.6
C&T INSTALLATION 144.7
C&T UNITS 846.8
C&T CIRCUITRY 176.9
TOTAL FOR COMMUNICATION & TRAC ( 1531.)DATA PROCESSING&SOFTWARE INST. 15.
DATA PROCESSING&SOFTWARE UNITS 1317.2
TOTAL FOR DATA PROCESSING & SO ( 1332.2)GN&C UNITS 816.9
GN&C INSTALLATION 150.
TOTAL FOR GUIDANCE NAVIG. & CO ( 966.9)OPERATIONAL FLIGHT INSTR INST. 58.6
INSTRUMENTATION UNITS 666.6
TOTAL FOR INSTRUMENTATION SYST ( 725.2)
TOTAL FOR AVIONICS ( 4555.3)
7. ENVIRONMENT
ROTATION HAND CONTROL 29.7
D-84
JSC-26098TRANSLATION HAND CONTROL 10.2
SPEED BRAKE/THRUST CONTROL 9.6INSTALLATION 50.
MISSION SPECIALIST STA PANELS 54.8
ON ORBIT STATION PANELS 166.1PAYLOAD MONITOR STATION PANELS 7.7
FLIGHT STATION PANELS 560.5
ANNUNCIATOR CONTROL ASSEMBLY 48.
MISSION SPEC STA PANEL INSTAL 12.
SUPPORTS 346.5
MIDSECTION PANELS 99.3
KEYBOARD 16.8
. TOTAL FOR CONTROLS SYSTEM ( 1411.2)
C&W INHIBIT/STATUS 3.2CLOSED CIRCUIT TV MONITOR 42.8
" TWO AXIS G METER 1.3
C&P DISPLAY UNIT, HUD 41.8
ELECTRONIC HUD 79.
ALTITUDE DIRECTOR INDICATOR 26.4
CROSS POINTER 5.
ANNUN-COMPUTER EVENT SEQUENCER 5.6
SURFACE POSITION INDICATOR 7.
DISPLAY ELECTRONIC UNIT 137.2
DISPLAY DRIVER UNIT 100.5
DISPLAY UNIT 104.8EVENT TIMER 3.2
MISSION TIMER 4.8
C&W ELECTRONIC UNIT 30.6
AIRSPEED/MACH INDICATORS 26.2
ALT/VERTICAL VELOCITY INDICAT 25.6
C&WANNUNCIATORDR 8.1
HORIZON SITUATION INDICATOR 15.4
TOTAL FOR DISPLAYS SYSTEM (668.4999)CABIN ATMOSPHERE REVITALIZATN 583.2
HEAT TRANSPORT WATER LOOP 331.
EQUIPMENT ENVIR CONTROL LOOP 746.6
CABIN PRESSURE CONTROL 464.9
AMMONIA SYSTEM 67.2
AIRLOCK SUPPORT SYSTEM 14.1
AIRLOCK SUPPORT SYSTEM-ORBITAL 15.HEAT TRANSPORT FREON LOOP 3078.
TOTAL FOR ENVIRONMENTAL CONTRL ( 5300.)LIGHT SYSTEM 203.
TOTAL FOR LIGHTING SYSTEM ( 203.)AIRLOCK 13.
PAYLOAD BAY 131.4
FOOD MANAGEMENT SYSTEMS 168.2
WASTE MANAGEMENT SYSTEM 261.WATER MANAGEMENT SYSTEM 243.
FIRE DETECTION SYSTEM 46.3
COMMANDER STATION 169.
PILOT STATION 169.
PAYLOAD MONITOR STATION 92.
MISSION MONITOR STATION 113.FURNISHINGS 396.
ORBITER-AIRLOCK PROVISIONS 69.1
TOTAL FOR PERSONNEL PROVISIONS ( 1871.)
TOTAL FOR ENVIRONMENT ( 9453.7)
D-85
JSC-26098
8. OTHER
MAIN ROLLING GEAR 2300.2
MAIN GEAR STRUCTURE 2714.4
NOSE ROLLING GEAR 183.6
NOSE GEAR STRUCTURE 600.6
MAIN RETARCT 348.1
BRAKE OPERATION 345.4NOSE RETRACT 107.2
NOSE STEERING 40.
AUX SYSTEMS - SEPARATION 908.3
AUX SYSTEMS-MANIPULATOR-SPAR 941.AUX SYSTEMS-MANIPULATOR INSTAL 378.9
AUX SYSTEMS-MANIPULATOR-GFE 0.3
TOTAL FOR LANDING & AUX. SYST ( 8868.)MID FUSELAGE FIXED SCAR ITEMS 96.8
WING FIXED SCAR ITEMS 2.2
MID FUSELAGE REMOVABLE PROVIS 675.
TOTAL FOR PAYLOAD PROVISIONS ( 774.)
TOTAL FOR OTHER ( 9642.)
9. GROWTH
MARGIN 420.
TOTAL FOR MARGIN ( 420.)
TOTAL FOR GROWTH ( 420.)
i0. NON-CARGO
AUXILIARY SYSTEMS 0.
EPS CRYO KIT NO.2 0.
TOTAL FOR PAYLOAD ACCOMODATION ( 0.)MARGIN i01.iCREW MEMBER PILOT 173.
CREW MEMBER PAYLOAD MONITOR 251.
CREW MEMBER MISSION MONITOR 511.
CREW ACCESSORIES - GFE 2954.
CREW ACCESSORIES - CFE 1390.9
CREW MEMBER COMMANDER 190.
TOTAL FOR PERSONNEL ( 5571.)ECS RESERVES 197.
HYDRAULIC COOLING RESIDUALS 126.
ASCENT PROPULSION RESIDUALS 50.MANEUVER RESIDUALS 96.
REACTION CONTROL RESIDUALS 32.ECS RESIDUALS 51.
PRIME POWER (EPS & APS) RESID 340.
PRIME POWER (EPS & APS) RESERV 450.HYDRAULIC COOLING RESERVES 149.
TOTAL FOR RESRV&RESID-NON PROP ( 1491.)MANEUVER RESIDUALS 890.
REACTION CONTROL RESIDUALS 587.
MANEUVER RESERVES 758.
REACTION CONTROL RESERVES 1039.
TOTAL FOR RESRV&RESID-PROP ( 3274.)
TOTAL FOR NON-CARGO ( 10336.)
Ii. CARGO
PAYLOAD/MODULE 25503.TOTAL FOR PAYLOAD ( 25503.)
MISSION KITS 3049.
D-86
JSC-26098
TOTAL FOR STS-OPERATOR ( 3049.)
TOTAL FOR CARGO ( 28552.)
12. NON-PROPELLANTUNUSABLE - SSME 1613.
UNUSABLE - ORBITER 3379.
RESERVE - ORBITER 174.
TOTAL FOR ASCENT PROP - DUMP ( 5166.)ASCENT PROPULSION 171.9
HYDRAULIC COOLING 157.1
CABIN ATMOSPHERE 185.
ECS 662.
- PRIME POWER (EPS & APS) 2897.TOTAL FOR IN-FLIGHT LOSSES ( 4073.)
TOTAL FOR NON-PROPELLANT ( 9239.)
13. PROPELLANT
MANEUVER 23416.
TOTAL FOR USABLE-OMS ( 23416.)REACTION CONTROL 5562.
TOTAL FOR USABLE-RCS ( 5562.)
TOTAL FOR PROPELLANT ( 28978.)
GROSS VEHICLE WEIGHT 249502.
D-87
NOTE: ALL MASS DATA_POIHT _ __y
IS IN POUNOS. H SPACE SHUTTLE EXTERNRL TRNK (ET), LNT-OOt t5 JUN 82
I. STRUCTURE _ 52588 4. POWER 372 8. OTHER ( 6676
..........L.[Q. OXY.T_,N.K .............. 12485 ..........._._!.R.I._._.,._._T.EM .............................9._2............ QRB/SRB AT!ACHME.N.T ......... 4234.............[E_!8._ .............................................!._.L!.#.........................................................................................................RQNC_._8.QEE_Y._._!EM.......i............SZG.
LIQ HYO TANK 27991 MECHANICAL SYSTEM : 1233
SEPARATION HARDWARE 883
.....................................................................'...........................................................................................'...........................................................................................S. GROWTH _...........i........
................................................................................................_.,...._._.Rg._......................................................_........_._:..H.q_QR_._...................................( ........_.ze_..UHUSRBLE FLUIDS 991FLIGHT PERFORMRHCE 3197
RESERVE
RESIDUAL LIQ HYO i 1689
: , • RESIDUAL LIQ OXY : 3012
LLLT I II I;LLTLLLLLTLLLTLTLLTLI ?ii LLTLLLLLTILTIZLLL?LLTTHERMRL PROTECTION : 5959 INSTRUMENTRTION 68
...................".................................................i................................................................................................................... i"INERT flRSS 76824..................................................................... !......................................................................................................................................................................................... !.....................
12. NON-PROPELLANT 39½8: LIQUIDS AND GASES 39H8
....9"i..............................................................PROPULSION _.........2"95'1................................................................................................................................................................................................................................................................................................................................................................................•............................................................................................
.........._.Lq..._..._X_LE_..................................k8_.7...................................................................................................................................................................................................._.[_.._.O..._!EM ..................................[k_! ..........................................................................................................................................................................................
................................................................................................._:ifi_iR____ .............................._..........._.........i_7_R6PgLE_T ...................................ig_5Se5
...................................................................................................................................................................................................._,_8.Bg.g...ER_._g_0.N!..................L_._._.8......................................................................................................................................................................................................_._g..._!._ ..............................................U.e,_..
LESS PRE-PRESS GASES -42_
TRANSFERRED TO ORB 183: SSME BUILOUP PROPEL : 48t5
...................:................................................. !........................................................................................... _............................................................................................ i .........................................................................................: .......................................................................................... _...................... ...................................................................... i.................... !
: : :
.....................................................................L...........................................................................................i......................GROSS.RSS _Tis54875.....................................................................: ............................................................................................ i...................... _...................................................................... :.....................= , i i :
SHUTMP03 CCSD WH tO NOV 92
JSC-2S098SPACE SHUTTLE EXTERNAL TANK
DESIGN MASS SUMMARY (JSC FORMAT)ALL MASS IN POUNDS
I. STRUCTURE
BHD 89.
FRAME, FWD II0.
OGIVE, FWD 1283.
OGIVE, AFT 3168.
FRAME, XT 745 245.BARREL 2399.
FRAME, INTERTANK 790.
DOME, AFT 2560.
BAFFLES, SLOSH 1841.
PRIMER, AFT DOME 0.
TOTAL FOR L02 TANK ( 12485.)BARREL PANELS, MACHINED 3699.
BARREL PANELS, SKIN/STRINGER 4114.
FRAMES, STABILIZING (4) 1102.FRAME, SRB THRUST XT 985 752.
BEAM, SRB THRUST 1114.
FITTING, SRB THRUST (2) 821.ACCESS DOOR 42.
SPLICES, BARREL PANELS (8) 127.
STABILIZERS, FRAME 103.
FASTENERS, ET ASSY 104.FAIRINGS 85.
INTERNAL PRIMER 50.
TOTAL FOR INTERTANK ( 12113.)DOME, FWD 1380.FRAME XT 1109.9 1130.
BARREL, NO. 4 4537.FRAME XT 1377 414.
BARREL, NO. 3 4555.FRAME XT 1624 413.
BARREL, NO. 2 4885.
FRAME XT 1871 1162.
BARREL, NO. 1 4988.FRAME XT 2058 2482.
DOME, AFT 2045.
TOTAL FOR LH2 TANK ( 27991.)
TOTAL FOR STRUCTURE ( 52589.)
2. PROTECTION
NOSE CONE 23.
._ L02 TANK 1216.INTERTANK 1045.
LH2 TANK 2762.INTERFACE HARDWARE 151.
PROP/MECH 218.ELECTRICAL 300.
RANGE SAFETY SYSTEM 6.
CLOSEOUT 238.
TOTAL FOR THERMAL PROTECT SYS ( 5959.)
TOTAL FOR PROTECTION ( 5959.)
3. PROPULSION
LO2 FEED SYSTEM 1515.
L02 ANTIGEYSER SYSTEM 0.
D-89
JSC-26098
LO2 VENT SYSTEM 95.
LO2 PRESSURIZATION SYSTEM 197.
TOTAL FOR LO2 SYSTEM ( 1807.)LH2 FEED SYSTEM 691.
LH2 RECIR. SYSTEM 31.
LH2 VENT SYSTEM 97.
LH2 PRESSURIZATION SYSTEM 325.
TOTAL FOR LH2 SYSTEM ( 1144.)
TOTAL FOR PROPULSION ( 2951.)
4. POWER
ET/SRB CABLING 306.
ET/SRB CABLING SUPPORTS 66. _TOTAL FOR ELECTRICAL SYSTEMS ( 372.)
TOTAL FOR POWER ( 372.)
6. AVIONICS
INSTRUMENTATION 22.INSTRUMENTATION SUPPORTS 46.
TOTAL FOR INSTRUMENTATION ( 68.)
TOTAL FOR AVIONICS ( 68.)
8. OTHER
FWD BI-POD ASSY 203
AFT ET/ORB TRUSS 3407
TANK FITTINGS - ORB/ET 317
TANK FITTINGS - SRB/ET 307
TOTAL FOR ORB/SRB ATTACHMENTS ( 4234 )
HARDWARE, CFE SOURCE 247
HARDWARE, GFE SOURCE 79
TOTAL FOR RANGE SAFETY SYSTEM ( 326 )MECHANICAL SUPPORT SYSTEMS 112
NOSE CONE 74.
FAIRINGS & CONDUIT 640.LINE & CONDUIT SUPPORTS 362.
TUMBLE SYSTEM 45.
TOTAL FOR MECHANICAL SYSTEMS ( 1233.)
SRB (GFE) 824.
ORB (GFE) EO-I, EO-2, EO-3 59.TOTAL FOR SEPARATION HARDWARE ( 883.)
TOTAL FOR OTHER ( 6676.)
i0. NON-CARGO
PROPELLANT, LH2 TANK 223.
PROPELLANT, LH2 LINE 68.
PROPELLANT, LO2 LINE i00.TOTAL FOR UNUSABLE FLUIDS ( 391.)
FPRLH2 718.
FPR LO2 2479.TOTAL FOR FLIGHT PERFO RESERVE ( 3197.)
RESIDUAL LH2 1609.
TOTAL FOR RESIDUAL LH2 ( 1609.)
RESIDUAL LO2 3012.TOTAL FOR RESIDUAL LO2 ( 3012.)
TOTAL FOR NON-CARGO ( 8209.)
12. NON-PROPELLANT
GH2, INFLIGHT 958.GO2, INFLIGHT 2567.
D-90
JSC-26098
GH2, TRAPPED ULLAGE VAPOR 164.
GO2, TRAPPED ULLAGE VAPOR 197.
HELIUM, LH2 TANK PRE-PRESS 41.
HELIUM, L02 TANK PRE-PRESS 21.
TOTAL FOR LIQUIDS & GASSES ( 3948.)
TOTAL FOR NON-PROPELLANT ( 3948.)
13. PROPELLANT
USABLE LH2 223617.
USABLE L02 1544811.
TOTAL FOR USABLE PROPELLANT (1568428.)FUEL BIAS ii00.
TOTAL FOR FUEL BIAS ( ii00.)LESS PRE-PRES GASSES - LH2 -205.
LESS PRE-PRES GASSES - LO2 -218.
TOTAL FOR LESS PRE-PRES GASSES ( -423.)TRANSFERRED TO ORBITER - LH2 51.TRANSFERRED TO ORBITER -LO2 132.
TOTAL FOR TRANSFERRED TO ORB ( 183.)SSME BUILDUP PROP - LH2 647.
SSME BUILDUP PROP - LO2 3368.
TOTAL FOR SSME BUILDUP PROP ( 4015.)
TOTAL FOR PROPELLANT (1573303.)
GROSS VEHICLE WEIGHT 1654075.
D-91
DATAPOINT UHHRRY NOTE:SRB'SAREBASEDNOTE: ALL MASS
ON STS-31 LEFT, BUTIS IN POUNOS SPACE SHUTTLE SOLID ROCKET BOOSTER iSRB) MASSES ARE FOR TWO.FOR TWO SRB' S. RPPROXBPR 1990
.....................................................................C'"'2"54"gGO"'_'"4".""p'OW'ER............................................. _ .........25_'G'_' 8. OTHER 69260...!_...._R_!_._g ................................................................................................................................................................................................................................................BODY STRUCTURE BATTERY _ 180 RECOVERY SYSTEM 18054
NOSE CAP 553 DISTRIBUTORS i 95 SEPARATION SYSTEM 1498
FRUSTRUM 7762 RECOVERY AIDS G RANGE SAFETY AND ABORT 289............................................................................................................................... | .................. . ................................................................................................................
FORWARD SKIRT 13268 BARO SNITCH { 65 ATTACHMENT PROVISIONS 816
AFT SKIRT 29084 TRANSDUCERS i 328 ...........NOZZLE_r...........................................ASSEMBLY :..........47562::_ATTACH STRUCTURE 4870 WIRE : 1050 TUNNEL i llu("SYSTEMS TUNNEL 879 CANISTERS i 758 9, GROWTH -SEPARATION RING 312 BRACKETS AND SUPPTS : 21 DRY h_S (FOR TWO) 385892
.................................................................................................................................................................. } ........................................................................................... i ......................
SAM STRUCTURE RATE GYROS i 55 ..................................................................... i.....................................F'ORWRRD"'CRS'E'"RSS'Y................. 5"266'9 ........................................................................5. CONTROL _ ........46"55": 10. NON-CARGO ( -
CENTER CASE ASSY FWD 43123 TVC ACTUATORS : 1397 ................................................................... :........................................................................................... J............................................................................................ _......................
CENTER CASE ASSY AFT 42B77 TVC HYD FLUID RESERVO[E 273 ...........................................................................................AFT CASE RSSY 58311 TVC HYD FLUID i 14B t.................................................................................................................................................................. • ........................................................................................... [
CASE STIFFENER RING 1460 TVC FUEL ! 127TVC INSTALLATION . 2712
THERMAL PROTECTION 293G INSTRUMENTATION 269PAINT 29T, SEALANT 121 418 . INERT _RSS (FOR TWO) 385892
INSULATION 4B727INHIBITOR 3730 ......................................................................_.................................................................................................................
IHSULAT ION EXTERNAL i 1915 .......................................................................................................................................................................................
.....................................................................(.........i6e3. PROPULSION
IGNITION SYSTEM 1000
.._,_,..._._.I.R_g._Z..........................................._._,.,_....ER_P_k_._ ................................._._._#..,..................................................................... JOINT HERTER SYSTEM 786 SEPARATION 1247
-- MAIN 2213145IGHITOR 2G8
....................................................................._............................................................................................i...........................................................................................i......................................................................................... :.......................................................................................... :...................... t..................................................................... : I
: GROSShAS8 (FOR T_O)I 2600552i
SHUTMP02 CCSD WH 10 NOV 92
JSC-26098
SPACE SHUTrLE SOLID ROCKET BOOSTER
DESIGN MASS SUMMARY (JSC FORMAT)
ALL MASS IN POUNDS
1. STRUCTURE
SKIN (INC WELDS) 229.1RNG FRAMES,STRNGERS,TIE RODS 36.1FITTINGS 10.4ASSEMBLY HARDWAR E 1.1
" TOTAL FOR NOSE CAP (276.7)
SKIN (INC WELDS) 1231.4RNG FRAMES,STRNGERS,LONGERONS 985.4BEAMS & SHEAR PANELS 478.9BULKHEADS 38.4FITTINGS 90.4BRACKETS,DOUBLERS,GUSSETS 464.4FLOTATION 229.3ATTACH HARDWARE 279.3ASSEMBLY HARDWARE 83.6
TOTAL FOR FRUSTRUM (3881.1)
SKIN (INC WELDS) 2144.1RNG FRAMES,STRNGERS,LONGERONS 1948.8BEAMS & SHEAR PANELS 36.2BULKHEADS 330.7BRACKETS,DOUBLERS,GUSSETS 849.3CUTOUTS & ASSOCIATED STRUCT 62.4THRUST POST 292.6THRUST POST FITTING 799.1PINS 25.1VENT PORTS 1.1MISC 120.9ASSEMBLY HARDWARE 19.6
TOTAL FOR FORWARD SKIRT (6629.9)
SKIN (INC WELDS) 4691.7RNG FRAM ES,STRNGERS,STRUTS,TIE 5308.2INTERCOASTALS 205.6HOLDDOWN STRUCTURE 2705.4BRACKETS,DOUBLERS,GUSSETS 640.8CUTOUTS & ASSOCIATED STRUCT 30.4FITTINGS 142.0ATTACH HARDWARE 603.8SEPARATION MOTOR MOUNTS 197.1ASSEMBLY HARDWARE 17.2
TOTAL FOR AFT SKIRT (14542.2)STRUTS 545.0SRM RING 1890.2
TOTAL FOR ATTACH STRUCTURE (2435.2)FWD SKIRT TUNNEL 42.5FWD MOTOR CASE TUNNEL 179.0AFT MOTOR CASE TUNNEL 126.3AFT SKIRT TUNNEL 24.9TUNNEL SPLICES 11.9ASSEMBLY HARDWARE 55.0
TOTAL FOR SYSTEMS TUNNEL (439.6)
D-93
JSC-26098
ASSEMBLY HARDWARE 156.0TOTAL FOR SEPARATION RING (156.0)
FORWARD DOME SEGMENT 3686.0CYLINDER SEG FWD 11230.0CYLINDER SEG AFT 11266.0JOINT - HARDWARE 166.6COATINGS 85.0UNACCOUNTABLE -98.9
TOTAL FOR SRM FORWARD CASE ASSY (26334.7)CYLINDER SEG FWD 10707.0CYLINDER SEG AFT 10725.0JOINT - HARDWARE 83.3COATINGS 74.0UNACCOUNTABLE -27.9CYLINDER SEG FWD 10653.0CYLINDER SEG AFT 10556.0JOINT - HARDWARE 83.3COATINGS 74.0UNACCOUNTABLE -27.9
TOTAL FOR SRM CTR CASE ASSY FWD (42899.7)ATTACH SEG 7003.0STIFFENER SEQ FWD 8402.0STIFFENER SEG AFT 8498.0AFT CASE SEGMENT 4920.0JOINT- HARDWARE 253.0COATINGS 93.4UNACCOUNTABLE -14.0
TOTAL FOR SRM AFT CASE ASSEMBLY (29155.4)STIFFENER RING 729.8
TOTAL FOR SRM STIFFENER RING (729.8)TOTAL FOR STRUCTURE (127480.3)
2. PROTECTIONNOSE CAP 26.9FRUSTRUM 80.5FORWARD SKIRT 87.9SYSTEMS TUNNEL 46.9ET ATTACH RING 77.3AFT SKIRT 507.1HEAT SHIELD 633.2ORDINANCE RING 8.0
TOTAL FOR THERMAL PROTECTION (1467.8) _
PAINT 148.4TOTAL FOR PAINT (148.4)
SEALANT 60.5TOTAL FOR SEALANT (60.5)
FWD DOME 683.2CYLINDER 2533.8JOINT 1270.7
TOTAL FOR SRM FWD SEGMENT INSULATION (4487.7)
FWD JOINT 168.6CYLINDER 1279.4AFT JOINT 1298.8
TOTAL FOR SRM CENTER SEG FWD INSULATION (2746.9)FWD JOINT 168.6CYLINDER 1241.4
D-94
JSC-26098
AFT JOINT 1298.8TOTAL FOR SRM CENTER SEG AFT INSULATION (2708.9)
JOINT 83.6CYLINDER 6430.7AFT DOME 3906.1
TOTAL FOR SRM AFT SEGMENT INSULATION (10420.4)FWD DOME 86.3CYLINDER 258.9
TOTAL FOR SRM FWD SEGMENT LINER (345.3)INHIBITOR FACE 37.4CYLINDER 280.9
•,. TOTAL FOR SRM CENTER SEG F'WDLINER (318.3)INHIBITOR FACE 37.4CYLINDER 281.8
'_ TOTAL FOR SRM CENTER SEG AFT LINER (319.3)INHIBITOR FACE 14.5CYLINDER 267.5AFT DOME 80.5
TOTAL FOR SRM AFT SEGMENT LINER (362.5)SLEEVE 5.1AFT FACE 272.9
TOTAL FOR SRM FWD SEGMENT INHIBITOR (278.0)FWD FACE 545.7AFT FACE 20.7
TOTAL FOR SRM CENTER SEG FWD INHIBITOR (566.4)FWD FACE 537.5AFT FACE 19.2
TOTAL FOR SRM CENTER SEG AFT INHIBITOR (556.7)FWD FACE 464.0
TOTAL FOR SRM AFT SEGMENT INHIBITOR (464.0)FWD SEG (2 EA) 100.2FWD CTR SEG 50.6AFT CTR SEG 50.6
AFT SEG (3 EA) 150.2FWD SKIRT 16.3AFT SKIRT 18.2FIELD JOINTS 69.4
TOTAL FOR JOINTS (456.5)RING INSUL (3) 178.3STUB INSUL (1) 31.0
TOTAL FOR STIFFENER RING (209.3)_- FWD SEGMENT 54.2
F'3NDCTR SEGMENT 59.4AFT CTR SEGMENT 59.1AFT SEGMENT 45.0
TOTAL FOR SYSTEMS TUNNEL (217.8)GEl-AFT SEGMENT 65.2
TOTAL FOR GEl-AFT SEGMENT (65.2)CLOSEOUT INSUL 9.2IGNITER INSUL 0.4
TOTAL FOR HEATER (9.6)TOTAL FOR PROTECTION (26208.4)
3. PROPULSIONLINER 3.3CHAMBER INSULATED 340.3
D-95
JSC-2E_098
INSULATION 6.5ADAPTER 99.5INITIATOR 4.2CHAMBER ATT HDW 14.6INGNITER ATT HDW 19.6UNACCOUNTABLE -2.9
TOTAL FOR SRM IGNITION SYSTEM (485.1)S/A DEVICE 13.0
TOTAL FOR SRM S/A DEVICE (13.0)S/A ATTACH HDW 2.0
TOTAL FOR SRM S/A ATTACH HDW (2.0)TOTAL FOR PROPULSION (500.1)
4. POWERSRB BATTERY 90.0
TOTAL FOR PRIME POWER (90.0)DISTRIBUTORS 47.5RECOVERY AIDS 2.8BARO SWITCH 32.3TRANSDUCERS 163.2WIRE 524.9CANISTERS 374.0BRACKETS & SUPPORTS 10.3RATE GYROS 27.6
TOTAL FOR ELECTRICAL&INSTRUMEN (1182.6)TOTAL FOR POWER (1272.6)
5. CONTROL
ACTUATORS 698.6RESERVOIR 136.6FUEL BOTTLES 64.0PLUMBING,VALVES,REGULATORS 159.8FITTINGS & BRACKETRY 918.2HPU SYSTEM 214.2TVC HYDRAULIC FLUID 73.0TVC FUEL 63.6
TOTAL FOR THRUST VECTOR CONTRL (2328.0)TOTAL FOR CONTRL (2328.0)
6. AVIONICSFWD OFI 5.gFWD GEl 6.2CNTR FWD OFI 0.8CNTR FWD GEl 12.1CNTR AFT OFI 0.8CNTR AFTGEI 15.2AFT OFI 54.6AFT GEl 34.1EXIT CONE SEVERANCE CABLE 3.7EXIT CONE GEl 1.3
TOTAL FOR SRM INSTRUMENTATION (134.6)TOTAL FOR AVIONICS (134.6)
7. ENVIRONMENTJOINT HEATER 2.8JOINT HEATER CABLE 15.6
D-96
JSC-2GOS8
JOINT HEATER CABLE 12.8
JOINT HEATER 58.8JOINT HEATER CABLE 12.0JOINT HEATER INSUL 39.9JOINT HEATER 58.8JOINT HEATER CABLE 11.7JOINT HEATER INSUL 39.9JOINT HEATER 58.8JOINT HEATER CABLE 42.2JOINT HEATER INSUL 39.9
. TOTAL FOR SRM JOINT HEATER SYS (393.2)
TOTAL FOR ENVIRONMENT (393.2)
_" 8. OTHERRECOVERY AIDS 84.5DECELERATION SUBSYSTEM 8942.3
TOTAL FOR RECOVERY SYSTEM (9026.8)FWD MOTOR CASE 171.6FWD MOTOR NOZZLE/AFT CLOSURE 138.8FWD MOTOR LINER 9.8FWD MOTOR IGNITER 18.8FWD MOTOR PAINT 2.0AFT MOTOR CASE 182.0AFT MOTOR NOZZLE/AFT CLOSURE 129.2AFT MOTOR LINER 9.8AFT MOTOR IGNITER 18.8AFT MOTOR PAINT 2.0
CDF/MANIFOLD ASSY 30.0INSTALLATION HARDWARE 6.4
TOTAL FOR SEPARATION SYSTEM (719.2)RANGE SAFETY & ABORT 144.4
TOTAL FOR RANGE SAFETY & ABORT (144.4)PINS (531) 194.3RETAINERS (531) 11.4RETAINER BANDS 28.5ADHESIVE 7.4PACKING 17.4LUBRICANT 0.9
--- JOINT FILLER 4.1FWD SKIRT A"n'ACH 78.6
AFT SKIRT A'I-I'ACH 62.3
"_ TOTAL FOR SRM A'n'ACHMENT PROV (404.8)FIXED HOUSING ASSY 2523.4FLEX BEARING ASSY 1593.9BOOT RINGS & ATTACH 81.2NOZZLE ATTACH HDW 308.4FLEXSEAL ASSY 6671.7NOSE ASSY 2430.2THROAT ASSY 1551.8FIND EXIT CONE ASSY 2350.6UNACCOUNT WT -115.3NOZZLE PLUG 87.2
D-97
JSC-26098
AFT EXIT CONE ASSY 6297.8TOTAL FOR SRM NOZZLE ASSEMBLY (23780.9)
FWD SEGMENT 47.5FWD CENTER SEGMENT 47.1AFT CENTER SEGMENT 47.1AFT SEGMENT 54.5SPLICE JOINTS 9.0
TOTAL FOR MOUNT PROV-RUBBER (205.3)
FWD SEGMENT 82.7
FWD CENTER SEGMENT 82.3AFT CENTER SEGMENT 82.3AFT SEGMENT 88.7SPLICE JOINTS 12.2
TOTAL FOR FLOOR SUB-ASY(GFE) (348.2)TOTAL FOR OTHER (34629.8)
13. PROPELLANTSEPARATION SYST PROP 623.6
TOTAL FOR SEPARATION SYST PROP (623.6)
FWD SEGMENT 301148.9FWD CENTER SEGMENT 271939.2AFT C ENTER SEGMENT 271762.9AFT SEGMENT 261721.2
TOTAL FOR MOTOR PROPELLANT (1106572.2)
MAIN IGNITER PROP 132.4INITIATOR PROPELLANT 1.4
TOTAL FOR IGNITER PROPELLANT (133.9)TOTAL FOR PROPELLANT (1107329.7)
GROSS VEHICLE WEIGHT 1,300,276.4
D-98
SPACE SHUTTLE VEHXCIIE
IBIL.L..-J Y o q
Yo +256.9
• 936.68
Yo -258.5
NOTE:,_1_ RLL DIMENSIONS RRE IN Y0-466"34 --'--
INCHES UNLESS NOTED._o
47X0236.0] OIIL eL"I"L_N 2ee _ _
- , _ 7 I ,__ s ,-_ ..... I-tt ....
Xv32"t.22 Xe266.16 XT217"t'635 Xml989"599 t.... ZTu,98.8 AND Z|9.8
(STRTIC,UHPRESSURIZEO,UHLOROED) SSVX CCSD WH 21 DEC 93 _
oo
SPLICE SHUTTLE VENXCIIEREFERENCE: DWG NO. VC70-000002, DESIGN GEOM ORBITER, REV 9 SEP 00
I SHUTTLE OPERATIONAL ORTR BOOK, VOL 1NOTE:SOILS DATA FIRE ALSO TAKEN FROll I : 129e. 3 >'SHUTTLE OPERflT|OHflL DATA BOOK I I REFERENCE BODY LENGTH
VOLURE I DATED lSSD REFLECTING THE i I (1528..',) - 2aS.e) X-15128 3 x°lT:'lLATEST REVISIONS RS OF I :_ RUG 98. I I ,vT_¢. u i "_'_'--_ -zoll¢'_- _"
I NOTE: RLL OihENSlOHS ill I /_--,,/.#.._--zoTiil.eI ARE IN INCHES lilT.RE .Vf _ /
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(330,69) 200 / XT li i.c.(s Poe XT 1837.29FULLY LOADED _T 963.35 I RNO?,is I---I x T XT _olt_. se XB
XB XT I138.9 2048.90 NELO XT395.00 1012.7?5 TRNGENT TRNGENT 1930.6372173.025
2215.838 _oo. >E INNER STRUCT IlLXT (18½.6531 FT) X B ,.,-c
_2'/'. '_2 (STATIC, UItPRESSURIZED, UNLORDEO) _OOO. 05B
SHUTDROI CCSD NH _I DEC 93;
O_
Do
SPnCE SHUTTLE OEBITERNOTE : I o.s vngNULLIISO'OUTBO
RLL DIMENSIONS RRE IN I IN UNSPITCHNU_LPLm_E GEOMETRYINCHES UNLESSNOTED. _ 1_"__leexL* oR- • NTV .INCLUUES PSNU8 nNO WING VERTICRL FLRP
/ il\TOLERRI,CE S M FT t 8S90 q13.:3S 13S.'/5 !
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Cit in G89.2_1 :_63.50C v ;_ 137.86 108._7• ;a _7_.81 199.8[
IIAC Yo = 182.13 Z • 635.5£':
hOUHT _"_'_ L___rtJ1_ " .RE UPPER ENGINE flIRFO|L TIP.OO[2-6_t .DO 10 o SYI1• YRM NULL 0 YO = 199o0010 MOO GO-q8 WEDGE
BRL • OR -9
XOS?9'S# Yo-89"q' ZoqqS "_ ! RT Y . O V v (TRIL VOLUhE) 0.0_37
,_ LH MRH|PULRTOR |HSTRLLED __+L_Yo,|,._ SM EXPOSED. FT2(TOTRL) EO|,.q (,NCL GLV) 963.|CLERR SGLOVE EXPOS*U, FTE (TOTRL) ;)30.8
8,4 TOTRL METTEO, FT 2 4001.Z 733.83
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...= .= c=-_, ., ORX; _ CCSD HH 9 RUG 93¢.JO_
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INCLUDESI 0 SNUBANnTOLERANCE × 1306. 90
._o816.72
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I Xo498, Zo469, Yo_;:> GIIIBRL j�¯�i�RTx01445, z0443ILOTS EYE
10° ' "11 "11""Xo127T.8% ZoSOC
180 DOWN TO" I + ............ _ ......... "_ ........
,-,_ ', ____ _1 MAIN LRNOING GEAR %03o I TRUNNION X01180, Zo283_,._ I L.
1
STATIC GAD LINE 3°56"
STATIC GRO CONTACT PT 160 20"
x o374.75, Zo225.4 Zr._NES_170"5
STATIC GAD CONTACT PTNLG TRUNNION X0374.75, Z0298 Xo11?2.2S5 ' ZoI70. 5
NOSE GEAR STOWED, X0304.42, Z0325.?5 I .... I .... I MPS LOWER ENPITCH NULL 10 °
0 IN 20(_ GIHBRL +1 tO RT
xo=4se.tT, Zo34e.s4I I I I I I I I
200 qO0 SO0 800 I000 IZO0 1½00 ISO0
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SHUTDR13 CCSD I,,IH 1S RUG 93
',,,,0oo
SPnCE SHUTTLE VEHXCLEEXTERNRL TRHK ( E T )
NOTE: STRTIONS RRE TRNK STRTIOHS, X T RHD RLL DIMENSIONS RRE IN INCHES. THE OIMEHSIONS SHOWN RRE
PRIIIRRY STRUCTURE OUTER MOLDLINE. THERMRL PROTECTION THICKNESS VARIES BETWEEN 8.5 TO 2.0.
1845.805 >
I TRNGENT TRNGEHT TRNGENT
327.2_ 760.35 969.95 1136.99 aeq8.90I 37t.00 I TR. i ,es_.??SI I I' . / 839.05 L _ _ | |
I _ '89.35-----_"f9. _12q. 125H124. 12511( 912.00 ql:_q '. 1'5 L
|i 'TF"| I I
331,00D
-i,,, WE,',, F F F --I/ ,,"'CE /| WELDI "ELO/ "ELDI "E'DI
375.99 ?q?. 35 IIPI.9 1123.15 1998.35 1626.8 18?q. 75 ;=963.90 2173.925WELD WELD WELD WELD WELD WELD WELD WELD
I I I I, I I I ,I I I I I I I I I I I I I I0 200 400 600 800 1000 1200 1400 1600 1800 2000
SCALE IN INCHES
SHUTDR03 CCSD WH 9 RUG 9S0
7 \ .f .,
SPnCE SHUTTLE VI-;H}{CLI-;SOLID ROCKET BOOSTER (sR8)
2 °HULL POSITION + OR - 8°(SQURRE PRTTERH) GIIiBRL xe-- a000,058 MOTOR NOZZLE
• 8°INCLUOES 0.4°OVERTRRVEL RNO 0.5°RLLIGNMENT | UNPRESURIZEOI
Xe
TRH _-- 2ooo.o5 MOTORNOZZLEX 531.48 THEORETICRL PRESSURIZED
_--13.28 SPHERICAL R _0 PIVOTGIMBRL 1POINT
XB48.6 38 X s 1H91 • ½8 Xe 1863. 458 154.9 MRX OIR PRESSURIZEDI
i °°1 , , /'S_'O"RXO'RUN'ESSORIZEO'1600 1800 2000 2200400 I I 600 800 1000 1200 14a
_._+ ...-.__.__.............. ,.......I _-4L I- _._._. _gFT;F_
II -""F T I II_T -°°°°°° ----"XB 995.00| SEGMENTS 146.00 0.0. XSI511.O0 XS 1837.29 J
I I I<-'i---'_1°3"5° I0 AFT OOMEXI29g. 00 Xs1823.85 _ XR2000. 058/
X 403.38 TRN I
SIDE VIEW ×B
I1930. 637
I I I I I I I I I I I I I I I I I I I I I0 200 400 600 800 1000 1200 IH00 1600 1800 2000
SCALE IN IHCHES
SHUTDR04 CCSD WH 13. RUG 93
JSC SPACEC_NFT(ALL TO SAME SCALE IN LRUNCH VEHICLE CONFIGURRTION)
APOLLO/SATURN V SKYLRB
-- TWO-STAGE SATURN V
_ooo --
_ I; I --- _ I
-- 3000 RPOLLO-SOYUZ 3000 --SRTURH IB
, SHUTTLE --
0 ! SPACE VEHICLE __& - I
I , _eee --
- _°°° i ! ,
-- GEMINI --r- T
MERCURY TITAN i T-- , i --- RTLRS =i i I !i,_j_,_ i
_ -i
_ -
- _ g -t_ ._ _ I o
-- 0 IN
_N JSCSCR02 CCSD WH 23 OCT 92 _o
JSC SPACIEC_FT(ALL TO SRME SCALE IN LRUNCH CONFIGURRTION)
JSC SPnCEC_nFT(RLL TO SRI1E SCRLE IN ORBIT CONFIGURATION)
JSC-26098
DISTRIBUTION FOR JSC - 26811
NAS JSCBH/Whitlock,Richard
BU2/Cyr, Kelley
EA43/Lawson,Shelby
EA6/Erwin,Harry
' EA6/Graves,Claude ., . _.EA6/McHenry,ElricEA6_ed, Robert :2
EA63/Branch(51)
EA63tTeixeira,Charles
EA64/Mallini,Charles
EG/Cockrell,Bedford
ES1/Modlin,Thomas
ESl/Zupp, GeorgeESter Glenn
ES2/Verinder,Irene
ESS/Nagy, KornelES5/Ross, Thomas
ES5/Schneider,WilliamOBl/Stecklein, Jonette
PS33/$TI Center(3)VG4/Akkerman,James
NAgA/KgCDF-FLS/Evans,Ray
NASAnC365/Eldred,Charles(2) ';_.367/Freeman,Delma
367/Piland,William
PD21/Shelton, B.
PT51/Hueter,Uwe
