CLRC 1FDR 10/01Jason Tarrant
SCT EC Support Structure
Support Structure
CLRC 2FDR 10/01Jason Tarrant
SCT EC Support Structure Cylinder, Wings & In-Fill Panels
CLRC 3FDR 10/01Jason Tarrant
SCT EC Support Structure
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
CLRC 4FDR 10/01Jason Tarrant
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
SCT EC Support Structure
Envelope
Figures reproduced from:0-TB-0049-177-01
CLRC 5FDR 10/01Jason Tarrant
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
SCT EC Support Structure
Actual Sizes
CLRC 6FDR 10/01Jason Tarrant
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
CLRC 7FDR 10/01Jason Tarrant
SCT EC Support Structure
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
CLRC 8FDR 10/01Jason Tarrant
X,Y,Z
Y,Z
X,Y
Y
X
Z
Y (in & out of screen)
Z = 0
SCT EC Support Structure
x,y,z Coupling
CLRC 9FDR 10/01Jason Tarrant
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
CLRC 10FDR 10/01Jason Tarrant
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)
CLRC 11FDR 10/01Jason Tarrant
SCT EC Support Structure
Low Mass & Radiation Length» Design optimisation through FEA to ensure
minimal use of material» Use of high stiffness to weight composite
structures & materials
CLRC 12FDR 10/01Jason Tarrant
SCT EC Support Structure
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.
CLRC 13FDR 10/01Jason Tarrant
SCT EC Support Structure
Support Cylinder
CLRC 14FDR 10/01Jason Tarrant
SCT EC Support Structure
Support Cylinder Continued…» Typical sandwich cross section
CLRC 15FDR 10/01Jason Tarrant
SCT EC Support Structure
Rear Wing
CLRC 16FDR 10/01Jason Tarrant
SCT EC Support Structure
Rear Wing Continued…» Typical sandwich cross section
CLRC 17FDR 10/01Jason Tarrant
SCT EC Support Structure
Front Wing
CLRC 18FDR 10/01Jason Tarrant
SCT EC Support Structure
Front Wing Continued» Typical Cross Section
CLRC 19FDR 10/01Jason Tarrant
SCT EC Support Structure In-Fill Panels
CLRC 20FDR 10/01Jason Tarrant
SCT EC Support Structure
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
CLRC 21FDR 10/01Jason Tarrant
SCT EC Support Structure
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).
CLRC 22FDR 10/01Jason Tarrant
SCT EC Support Structure
Cradled ECConcept
CLRC 23FDR 10/01Jason Tarrant
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