AMS02 Thermal Test

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AMS02 Thermal Test

• Marco Molina, Christian Vettore, Massimiliano
  Olivier (CGS)
• Serena Borsini (UNIPG)

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Test specification

• TVTB Test specification issue 1
• November 2007
• Subdetectors test requirements collected
• TIM, February 2008
• TVTB Test specification issue 2
• Apr 14th 2008
• Comments received and implemented from AMS
• TVTB Test specification issue 2 rev H
• June 29th 2008
• Last comments have been gathered, will be
  incorporated before issuing the final one

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Apr 2008- Jul 2008

• Steady state thermal analysis have been done (S.
  Borsini , UNI PG)
• Maximum and minimum temperature achievable on the
  detectors
• IR lamps design has been consolidated
• Assessment on gradients on the gondola has been
  completed
• Power density has been calculated for the lamp to
  generate thermal gradients
• Transient analysis (cooling down) has been
  started

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Thermal test principle

• Thermal test conditions are NOT representative of
  the extremes AMS will experience on orbit
• Thermal test conditions, in general, are NOT
  representative for the entire detector of any
  specific on-orbit condition
• AMS will be in equilibrium with the impinging
  fluxes varying view factors to the ISS deep
  space unobstructed view

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T MAX
Thermal requirements for detector A
On orbit
Test
T MIN
6
Thermal requirements for detector B
T MAX
Test
On orbit
T MIN
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T MAX, B
Thermal requirements for detector B
Test
On orbit
Thermal requirements for detector A
T MAX, A
On orbit
Test
T MIN, A
T MIN, B
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Isochronous snapshot (same time), on orbit
T MAX, B
Thermal requirements for detector B
Test
On orbit
Thermal requirements for detector A
T MAX, A
On orbit
Test
T MIN, A
T MIN, B
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Isochronous snapshot (same time) Cold case in the
LSS
T MAX, B
Thermal requirements for detector B
Test
On orbit
Thermal requirements for detector A
T MAX, A
On orbit
Test
T MIN, A
T MIN, B
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Isochronous snapshot (same time) Hot case in the
LSS
T MAX, B
Thermal requirements for detector B
Test
On orbit
Thermal requirements for detector A
T MAX, A
On orbit
Test
T MIN, A
T MIN, B
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Isochronous snapshot (same time), Temperature
swing in the LSS
T MAX, B
Thermal requirements for detector B
Test
On orbit
Thermal requirements for detector A
T MAX, A
On orbit
Test
T MIN, A
T MIN, B
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What is it representative the TV test of?

• For each detector, a cold and a hot environment
  will be provided for performance evaluation in
  vacuum in the two conditions
• Transition between hot and cold
• Model correlation

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Model correlation in 2 steps

• Not being possible to reproduce entirely the ISS
  environment, an isothermal environment is used
  for model parameters identification
• The so called validated model (with identified
  parameters) is then used for on-orbit predictions

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?
LSS
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Test data
Parameters tuning (identification)
Test data?Model data VALIDATED MODEL
Model data
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On orbit predictions (final)
On-orbit temperature are predicted with higher
reliability
AMS VALIDATED MODEL is integrated with ISS
model

• Overall uncertainty in the temperature prediction
  will be reduced
• BUT
• Environment-related uncertainty cannot be reduced
  by the TVTB test

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Thermal extremes prediction in the LSS

• LSS analysis conditions
• COLD shroud at -90C, see next page for the
  other conditions
• HOT shroud at -10C, lamps OFF, AMS ON
• Nominal operations (power)

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COLD case analysis

• Transient to -90C for 20 hrs
• Heaters TRD and TRDGB ENABLED
• Heaters RAM set 1 on
• Lamps on Lower USS ON with a power of 500 W per
  module (1 module 8 lamps)
• AMS02 electronics on

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Temperature ranges during test

• TRD
• side panel from -5 C to 20C
• M-structure (corner bracket) from -14C to 16
  C
• M structure (center) from 1C to 20C
• Lower TOF from -16C to 14C
• Upper TOF from -6C to 24C
• Ecal from 5C to 38C
• Rich from -16C to 15C
• Tracker
• Hybrids from -18C to -12C
• Silicon tracker from -13C to 5C
• Cryocoolers from -17C to 18C
• TRD temperatures are not stabilized after 20
  hours longer transients needs to be run

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Temperature ranges during test

• CAB from -12C to 18C
• TTCB
• Baseplate from -20C to 5C
• Start-up radiator from -17C to -4C
• Star tracker electronics from -4C to 8C
• Acc from -19C to 20C
• Tracker radiator
• Ram side from -54 to 4C
• Wake side from -52C to 3C

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• TRD GB baseplate from -18C to 14C
• XPD from -14C to TBD in the hot case
• Crates from -5C to 33C
• PDS from 12C to 39C
• E-crates from -9C to 8C
• UPS from -30C to 12C
• HV on lower USS from -50C to 5C
• By switching on the lamps, can be raised up
  to 30C

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• Hottest temperature is driven by ECAL (38C)
• Coldest temperature is driven by UPS (-30C)

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LAMPS POWER FLUXES ESTIMATION
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LAMPS ON TRACKER WAKE RADIATOR
LAMPS POWER EVALUATION
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LAMPS ON TRACKER WAKE RADIATOR
Lamp power from TD 0,19 x Plamos if Plamps
1000 W ? 300 W/m2 if Plamps 1960 W ? 600
W/m2 if Plamps 2776 W ? 820 W/m2
Number of lamps on the tracker radiator will be
doubled
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LAMPS ON TRD
LAMPS POWER EVALUATION
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LAMPS ON TRD
Lamp power from TD 0,25 x Plamos if Plamps
1000 W ? 600 W/m2 if Plamps 1960 W ? 1100
W/m2 if Plamps 2776 W ? 1600 W/m2
Number of lamps on the TRD will be doubled
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LAMPS ON ECAL
LAMPS POWER EVALUATION
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LAMPS ON ECAL
NODE 90400
Lamp power from TD 0,04 x Plamos if Plamps
1000 W ? 440 W/m2 if Plamps 1960 W ? 870
W/m2 if Plamps 2776 W ? 1200 W/m2
Number of lamps on the ECAL will be incremented
by 50 (for accomodation reasons)
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Total IR lamps

• 92 lamps (30 spares)
• 32 independent controllable power supply (10 A
  max)
• It is recommended by NASA/Jacobs to have more
  power supply units for contingency (to oversupply
  the lamps, as needed)
• Final number of power supply and feed lines will
  be given to ESTEC in September

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Test sequence
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Test sequence

• Functional checkout before vacuum
• Bake out
• Initial cooling down
• Switch on
• CCEB (for monitoring Pt1000 sensors)
• M (for monitoring various temperatures)
• UG (to monitor TRD TEMPERATURE)
• The Upper TOF is switched on for thermal reasons.
• TRD GAS is switched on
• Cryocoolers are switched ON, to follow the
  recommendation by the Magnet group of running
  them as much as possible
• Before Magnet charging everything will be ON with
  exception of
• TRD
• RICH
• ECAL
• TRACKER

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• Magnet charge
• Cold thermal balance
• Cold start
• PDS
• J-crate
• CCEB (For monitoring)
• M-crate
• UG-crate
• TOF
• TRDGB (For operational and thermal)
• Cryocoolers
• TRACKER, RICH, ECAL, TRD are switched on with no
  priority driven by thermal considerations

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• Cold to hot transition
• Hot thermal balance
• Hot start
• PDS
• J-crate
• CCEB
• M-crate
• UG-crate
• All the other detectors (TOF, TRD GAS BOX,
  Cryocoolers , TRACKER, RICH, ECAL, TRD)
• Hot to cold transition
• Cold thermal balance number 2
• Hot thermal balance number 2
• Magnet discharge
• Re-pressurization
• Functional checkout at ambient conditions
• End of the test

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Example of transient analysis
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PDS
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RICH
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Conclusions

• TVTB test spec document can be found at
• ftp//ftp.cgspace.it/Projects/AMS/TWG/DOC/SPEC/1-L
  SS/TVTB-TEST-SPEC/
• Coming next TVTB workshop in Milano in September
  23-24 2008
• Test duration estimate
• Thermal transient calculations from Thermal group
• Time estimate for each detector tests from AMS
  subdetectors see next page
• Draft step-by-step procedure (S. Lucidi)
• Test procedure to ESTEC Nov 1st 2008

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REQUEST TO SUBDETECTORS

• Functional test duration (including activation of
  the subdetector) has been estimated 2 hours.
• Subdetectors needing more time should let us
  know, as well as any critical parameters to
  monitor.

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TV test scope

• Functional performance verification of the entire
  detector
• Under vacuum conditions
• At the extreme achievable thermal environment
  (hot and cold)
• Respecting the flight hardware limits (WITHIN
  ACCEPTANCE LEVELS)
• Driven by the test configuration
• TVT stand
• IR lamps
• SUCCESS CRITERION Proper functioning of sub
  detectors and electronics.
• REMARK IT IS NOT A (PROTO)-QUALIFICATION TEST
• Equipments and detectors will not necessarily go
  to their flight extremes

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MATERIALS COMPATIBILITY with vacuum

• NASA-gtESTEC
• AMS flight hardware DML
• AMS-gt ESTEC
• TVT test stand and all hardware used for the test
  outgassing data
• AMS-provided cables
• scaffolding
• AMS-provided piping
• valves
• ESTEC -gt NASA/AMS
• ESA-provided hardware outgassing data
• Lamps and their rigs
• Test MLI
• Test heaters
• ESTEC provided pipes

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ITEMS TO BE PROVIDED BY ESTEC

• 450 Temperature sensors (thermocouples) (50
  spares)
• Some of them, according to Tab. 8-1 will be
  needed in advance for being pre-installed at CERN
• IR lamps with power supply, controllers and
  cabling, as specified in 7.2.3
• 106 Lamps 30 spares
• 18 independent power supply and controllers for
  the IR lamps
• IR Lamps cabling
• IR lamps rigs
• Venting lines
• TRD gas BOX vent line
• Pipe inside and outside the LSS
• Test MLI (0.05 effective emittance) to wrap-up
  the pipe
• Heaters (2 W / m) underneath the MLI and power
  supply
• Cryogenic system venting (see paragraph 7.5 )
• Feed-through
• AMS Power, Command and Data (see paragraph 7.3 )
• For Helium lines (see figure Fig. 7-2)
• For TRD vent lines
• Test MLI for the LSS floor (as specified in
  paragraph 7.2 )

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Temperature sensors

• 350 thermocouples are foreseen for the test
  article.
• LSS shroud temperature shall be monitored with
  50 sensors to provide information on temperature
  uniformity.
• 50 sensors shall be used to monitor the TVT
  stand temperature

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At the end of the test each subdetector will have
undergone

• Partial functional test
• At ambient before the test
• In a cold environment (twice)
• In a hot environment (twice)
• Transient data (cooling down in case of a power
  loss) will be collected
• In a cold environment (twice)
• In a hot environment (twice)
• Response of some subdetctors (TRD, TOF) to
  environment variation will
• AMS02 Activation sequence is tested
• Magnet charge and discharge is tested
• High beta-angle (heat unbalance) is tested for
  RICH, ECAL and TRD
• RAM-WAKE unbalance is tested for the TTCS

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Overall duration

• Bake out and thermostats check-out (initial
  cooling down) 200 hours
• Cold thermal balance (5 plateau) 300 hours
• Power outage in a cold case 10 hours
• Hot thermal balance 100 hours
• Power outage in a hot case 10 hours
• Cold TB number 2 80 hours
• Hot TB number 2 80 hours
• Magnet discharge 5 hours
• LSS chamber re-pressurization 30 hours
  .
• TOTAL 815 hours 34 days

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Lamp group 1 (AMS bottom)
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LAMP GROUP 2 (ECAL/RICH side)
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LAMP GROUP 3 (TRD side)
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LAMP GROUP 4 (Tracker radiator)