AMS-02

1
AMS-02 Integration Test Plans Status
Trent Martin
24 January, 2007
2
Agenda

• Integration Documentation
• AMS Assembly Area/Clean Room 867
• STA Flight Integration Hardware Status
• Pre-integration of STAs in the Flight USS prior
  to STA VC/CMR arrival
• Pre-integration of Detectors on the STA VC
  Flight USS prior to Flight Cryomagnet arrival
• Integration discussion items plans for
  resolutions
• Final Flight Integration

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Integration Documentation

• All NASA developed AMS documentation can be found
  at
• http//ams-02project.jsc.nasa.gov/html/Documents.h
  tm
• Includes payload Interface Control Documents and
  AMS-02 Assembly and Testing Integration Plan

4
AMS 02 Integration at CERN
Assembled AMS 02
Upper Part
Lower Part
AMS 02 Shipping
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KSC
CERN / ESTEC

• Beam Test
• Experiment
• Calibration
• Thermal Vacuum
• Test _at_ ESTEC

AMS-02
KSC Processing
AMS-02
Hurricane Cover SSPF
3 Operational Years
ISS
Launch
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AMS 02 Assembly Sequence for Pre-Integration and
Flight Integration
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Upper USS Magnet
UPS

• Technical Interchange Meeting
• July 23, 2004
• R.Becker (MIT)

Magnet
CAB
USS-02
CVB
1) SCL delivers Magnet (Flight) or NASA delivers
STA Magnet (Pre-Integration) 2) NASA delivers
USS 3) USS main bolted to Vacuum Case (Magnet
must be warm) placed into rotation assembly
stand
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Crate Installation using Jig
Electronics Assembly Jig Installed
Electronics mounted in sequence with detectors
during pre-integration



-
Radiator Mounted Electronics Assembly
Jig replaced with Radiator during flight
integration when all crates are linked and form
a self supporting structure

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ACC  
ACC  
VC
VC

• Finger brackets bolted to inner lower bore of VC
• 16 Scintilator panels placed in inner bore
  resting on finger brackets
• 3) Carbon composite cylinder and with
  compliant brackets mounted at upper and lower
• inner edge of VC securing the paddles
• 4) PMTs, fiber couplers, and optical fibers
  mounted to Conical flange

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Tracker, Cooling, Star Tracker
Tracker Electronics Crates
5)
Star Tracker
6)
 
3)
4)
1)
Tracker  
Flange of VC
Tracker Cooling Box
VC
2)
1) Tracker Inner planes and upper conical flange
lowered and secured 2) Lower conical flange
mounted 3) Cooling loops, TTCS, plumbing 4)
Outer planes (1 5) 5) Crates cabling 6)
Star Tracker camera
4)
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TRD Upper TOF
Upper TOF 1) Upper TOF mounted to TRD
TRD MLI
TRD
TRD GAS System
1) TRD with M-structure lowered onto USS
bolted 2) Gas system installed and plumbed to
TRD 3) MLI enclosure 4) Crates Cabling
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Lower USS Integration
(5) Lower TOF 1) Reinforced with Jig, rolled
underneath AMS lifted into position. Struts
adjusted and bolted in place 2) Crates and Cabling
(6) RICH 1) RICH lowered, shimmed and bolted to
lower USS 2) Crates and Cabling  
(7) ECAL RICH/Lower USS assembly lifted lowered
onto ECAL then bolted in place Crates
Cabling These steps can be done in parallel
with upper USS integration and only need to be
done once (ie. No pre-integration)
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Upper Lower Parts Integration
Upper Part
 
Lower Part

1. Lower part rolled underneath Upper
2. Lifted in place, shimmed, and bolted
3. Electrical connections made

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De-integration for Flight Magnet
Temporarily remove mid-brackets and lower struts
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Temporarily Reattach Top Brackets to Upper USS
Move Main Ram Wake Radiators outward to allow
installation of Flight VC Magnet
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• Radiators Electronics
• Zenith radiators with plumbing attached assembled
  in quadrants bolted to TRD upper honeycomb and
  heat exchangers to Cryocoolers
• Plumbing secured and insulated
• Main radiators jigs removed from self supporting
  crates and radiators bolted
• Tracker Radiators Jigs holding heat exchangers
  removed and radiators lowered and bolted to USS
  and exchangers

Zenith Radiator
Tracker Radiator
Tracker Radiator
RAM Radiator
WAKE Radiator
RAM Radiator
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AMS Assembly Area
Clean Room 867
Everything in the AMS Assembly Area/Clean Room
867 needed to begin the STA integration will be
ready no later than (NLT) February 2, 2007.

• Operation as a Clean Room (air conditioning,
  filters, sealed positive pressure) will be
  ready in May, 2007

• Rotation Assembly Stand (RAS) delivered,
  assembled, installed, and ready for use

• Scaffolding delivered, assembled, and ready for
  use

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AMS Assembly Area
Clean Room 867

• Information provided in the Resource Requirements
  checklists has been used to order common use
  supplies and to estimate facility requirements
• Work area required with without crane access
  special access
• Crate storage area, volume, and environment
• Tables chairs
• Storage cabinets open shelves
• Air bearing pallet requirements
• Cleaning fluids/supplies vacuum cleaners
• Supply gases (He, CO2, N2, Compressed air, etc.)
• Fans for ventilation/cooling of hardware
  personnel
• Power requirements
• ???
• If you didnt ask for it on the checklists, do
  NOT expect it to be provided!

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AMS Assembly Area
Clean Room 867
Remov-able Ceiling Panels
Airlock
Ceiling Panels are NOT Removable
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AMS STA Integration Hardware

• STA VC integration with the STA Magnet (Cold Mass
  Replica - CMR) was completed in December at SM
• STA VC Arrived in Terni/INFN for Sine Sweep Tests
  on January 10th
• Test hardware was previously shipped to Terni and
  testing has been completed
• Ship STA VC to ESTEC for Acoustic Tests - March
  07
• Return to CERN for integration in USS late
  March 07
• Depends on results of STA VC/CMR sine sweep
  acoustic tests

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AMS Flight Integration Hardware

• Flight USS is complete and has arrived at CERN
  with the Primary Support Stand (PSS) and the
  Primary Lift Fixture (PLF)

• Flight Vacuum Case is complete and will be
  shipped to SCL/SM when they have room in their
  facility to accommodate it (after Flight
  Cryomagnet tests are completed and the SFHe Tank
  is delivered and SFHe leak tested)

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Pre-integration of STAs in the Flight USS Prior
to STA VC Arrival

• STA Hardware Pre-integration in Flight USS
• On-line integration of the STA Crates/Radiators
  on the USS will begin the week of February 5,
  2007 before the STA VC arrives
• This allows work to proceed even if the sine
  sweep acoustic tests are delayed
• 10T crane installation will be delayed until
  after STA Pre-integration is complete at
  beginning of March
• If necessary, the USS/STAs in PSS will be moved
  away from crane installation
• There are 3-4 weeks available in March to use
  the flight USS STAs for fit checks, cable
  plumbing runs, measurements, etc.

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Pre-integration of STAs in the Flight USS Prior
to STA VC Arrival

• STA Hardware assembly in Flight USS (cont)
• Integration of all STAs in USS to be completed by
  mid-April 07
• Even though the STA VC delivery to Terni slipped
  5 weeks and the RAS readiness at CERN slipped 3
  weeks, this is only 2 weeks later than
  previously reported at AMS TIM on October 27,
  2006
• Ship USS with STAs to Munich/IABG in April 07
• Static Tests
• Modal Tests
• Return USS with STAs to CERN in August 07
• Depends on results of STA VC/CMR sine sweep
  acoustic tests and USS/STA modal static tests

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Interference between Flight VC/Magnet
Electronics Crates during Final Flight
Installation

• R. Becker/MIT, J. Kastelic P. Mott/JS, R.
  Stafford-Allen/SM to determine how much room is
  required to clear the Flight VC/Magnet as well as
  how much room is available by Jan 29th.
• Provide estimate of additional length required
  for lower inter-radiator cables to M. Capell A.
  Lebedev
• Final cable routing must accommodate additional
  length
• Be sure theres no interference with hardware
  mounted outboard of crate jigs during
  pre-integration activities
• Upper inter-radiator connections will be
  disconnected because the additional length will
  be too much additional weight
• C. Lauritzen/JS to determine if there is any
  problem on the USS if the brackets are
  temporarily re-attached at a wider position by
  Feb 5th
• M. Molina/CGS to determine if Radiator brackets
  are OK by Feb 5th
• Consider using blocks/spacers under the brackets
  and reattaching the lower struts
• K. Bollweg J. Heilig will arrange trial test
  using STA Crates/radiators in late February

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Pre-integration of Detectors on STA VC USS
prior to Cryomagnet Arrival

• All the detector groups have continued to
  evaluate the pre-integration proposal and have
  agreed that it should proceed according to the
  schedules thoroughly discussed at this TIM
• Current estimate of Pre-integration start
  August, 2007
• Pre-integration finish December, 2007
• Optical fibers between ACC VC for TAS will be
  installed
• Constantly monitor the Cryomagnet progress and
  decide how much more flight hardware to
  pre-integrate
• Current estimate of magnet delivery to CERN
  February, 2008
• Do as little de-integration as possible just in
  time to remove the STA VC and install the Flight
  VC Cryomagnet in the USS

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Pre-integration of Detectors on STA VC USS
prior to Cryomagnet Arrival

• Consider removing the STA VC, Tracker, and ACC
  from the USS as an assembly so parallel work can
  continue during Flight VC/Magnet installation
• Use VC rotation fixture and wheels/brackets
  developed at SM
• This could shorten deintegration by 2-3 weeks
  thus allowing combined cosmic ray testing to be
  extended

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Final integration of Detectors on Flight VC USS
after Cryomagnet Arrival

• All detectors must be integrated and functionally
  tested with the Flight VC and
  Cryomagnet at CERN by July, 2008
• Beam tests at CERN (1 month reserved)
• Thermal Vacuum Tests at ESTEC (3 months
  reserved)
• EMI Tests at ESTEC (1 month reserved)
• Delivery to KSC in December, 2008

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What we have sort of.
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(No Transcript)
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Where we must be by December 2008 at KSC...