SCT EC Support Structure

CLRC 1FDR 10/01Jason Tarrant

SCT EC Support Structure

Support Structure


SCT EC Support Structure Cylinder, Wings & In-Fill Panels



Requirements» Strength to Support 9 Wheels, Services &

Thermal Enclosure.» Maintain Module Positions in Long & Short

Term (Defined in ATL-IS-ER-0027)

» Low Mass & Radiation Length Construction» Maintain External Dimensions that Remain

Within Defined Envelope (0-TB-0049-177-01)

» Radiation Tolerance to 0.24MGy


R59

9 R

MIN

. OU

TE

R T

HE

RM

AL

EN

C.

R58

2 R

MA

X. S

UP

PO

RT

CY

LIN

DE

R

R57

2 R

MIN

. SU

PP

OR

T C

YLI

ND

ER

R61

0 R

MA

X. O

UT

ER

TH

ER

MA

L E

NC

.

2797 Z MAX. FRONT WING2767 Z MIN. REAR WING

822 Z MAX. FRONT WING810 Z MIN. FRONT WING


Envelope

Figures reproduced from:0-TB-0049-177-01


Ø1

164,

95 L

AR

GE

ST

OD

810,87 LOWEST Z TO START OF HEATERS(810.44 WITHOUT CME)

812,87 WING TIP LOW Z

821,87 WING TIP HIGH Z

821,51 Z AT CORNER OF CYLINDER

582

,47

TO

CO

RN

ER

OF

CY

LIN

DE

R

2767 CYLINDER DATUM PLANE

2766,5 WING TIP LOW Z (NO SERVICES HERE)

2794 WING TIP HIGH Z

2796,2 HIGHEST Z TO END OF HEATERS

583

,23

TO

CE

NT

RE

OF

CY

LIN

DE

R

821,65 INSIDE WING FACE (BOW IN)

821,37 INSIDE WING FACE (BOW OUT)

1945,49 'LONG' CYLINDER


Actual Sizes


SCT EC Support Structure Manufacturing & Assembly Tolerances

» Deviation of final component size from nominal (within tolerance)

» Accuracy of alignment when assembling components

» Deformation of components during assembly (mainly Wheels & Services)

» Accuracy of integration with TRT» Accuracy of Squirrel Cage Mount Rails w.r.t.

nominal beamline



Adjustments to Reduce Effects of M&A» Wheel (& attached modules) Aligned With Disc

Fixings– Sag in Cylinder– Averaging Out Locations of Module Rings– Averaging Out Component Assembly Misalignment

» Wing Couplings (Shimmed & Slotted)– Adjust Relative to Squirrel Cage & Cryostat– Averaging Out Component Assembly Misalignment


X,Y,Z

Y,Z

X,Y

Y

X

Z

Y (in & out of screen)

Z = 0


x,y,z Coupling


Acclimatisation & Run-In» Thermal Contractions upon cool-down» Effects of moisture desorption in dry atmosphere

In Service Deformation» Local excitation where structures position affected» Variation in ambient temperature and effect on structural

size» Long term creep effects» ‘One-off’ excitations where structural position affected



SCT EC Support Structure Short Term Stability

» From ATL-IS-ER-0027, required stability in 1 day;– z = 200m– r = 50m– r- = 50m

» Short term instability from, Excitation/CTE (CME after acclimatisation << 10m in any direction / day)

» Calculated– z = 52m @ W1 (worst case)– r = 9m (x), < 3m (y) (not incl. external input)

– r- = 10m (x + 10%), no twist, (not incl. external input)



Low Mass & Radiation Length» Design optimisation through FEA to ensure

minimal use of material» Use of high stiffness to weight composite

structures & materials



Radiation Resistance» Materials Verified;

– XN-50A/RS-3 5x107 Gy TD (CERN TIS 98-01, 18/5/98, Compilation of Radiation Damage Test Data, Tavlet M et al.)

– RS-3 unfilled slight effect up to 107 Gy, RS-4A similar composition so no expected problems (same ref. as above)

– Nomex 107 Gy TD, very similar to Korex so no expected problems (CERN TIS 82-10, 4/11/82, Compilation of Radiation Damage Test Data,Beynel P et al.)

– Metallics, no expected problems.



Support Cylinder



Support Cylinder Continued…» Typical sandwich cross section



Rear Wing



Rear Wing Continued…» Typical sandwich cross section



Front Wing



Front Wing Continued» Typical Cross Section


SCT EC Support Structure In-Fill Panels



Conclusion» Support Structure size adjusted from envelope size

to account for likely deformations» Manufacture & assembly tolerances adjusted out

via disc fixings wing couples, acclimatisation adjustments possible too

» Support Structure materials chosen for structural ‘ability’, environmental stability and radiation length characteristics



Conclusion Continued…» Overall component shapes defined by;

– Envelopes– Structural requirements (through analysis & prototyping)– Interactions with components and with assembly /

integration procedures.

» Based on components shapes that have been successfully prototyped (prototype Barrel Cylinder & prototype Rear Wing).



Cradled ECConcept


EC Mass & Radiation Length

Part Mass (kg)Rad Length (%)

Front wing & In-Fills 5.77 1.43Membrane 0.93 0.21Rear wing 11.16 2.56Support cylinder 13.72 0.58Inner thermal enclosure 11.18 1.59Outer Thermal Enclosure 24.47 1.25Thermal end cap rear 0.85 0.49Cooling pipe links 4.24 0.25Power tapes links- All 14.79 0.38Optic fibres links 1.46 0.04Al Foils 6.48 0.37Disk Fixation Devices 0.86 0.09Services Management Hardware 1.07 0.03Outer Thermal Enclosure Brackets 1.07 0.03Cooling Fluids 3.62 0.14Services Thermal Feed Through 5.68 1.34Total 107.35

Part Mass (kg)Rad Length (%)

Patch Panels (All) / disk 1.79 2.29Total (assumes all full disk, will be smaller in reality) 16.10

Discs 2,3,4,5,6 = 5.7 KgDiscs 1,7,8 = 4.5 KgDisc 9 = 2.9 KgPatch panels = 16.1 kgRest of the End-cap = 107.4kgThe total mass =

168.4 kg per End-cap

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SCT EC Support Structure