Alpha Magnetic Spectrometer 02 Phase II Flight Safety Review Mission Operations CERN TIM April 25, 2

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Alpha Magnetic Spectrometer 02Phase II Flight
Safety Review Mission OperationsCERN TIM
April 25, 2007Timothy J. Urban / ESCG /
Barrios Technology
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Alpha Magnetic Spectrometer 02Mission
Operations

• Outline
• Timeline
• Pre-Launch Operations
• Ascent Operations
• On-Orbit Operations
• STS
• SRMS to SSRMS Hand-off
• ISS
• EVA Compatibility
• Contingency Operations

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Alpha Magnetic Spectrometer 02Mission
Operations

• Overall Milestone Timeline

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Alpha Magnetic Spectrometer 02Mission
Operations
PRE-LAUNCH OPERATIONS
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Alpha Magnetic Spectrometer 02Mission
Operations Pre-Launch

• Outline
• KSC Flow
• Pre-Launch Operations
• T0 Umbilical Interfaces
• Standard Switch Panel Configuration
• Payload Data Interface Panel 2 (PDIP2)
  Configuration
• Timeline
• Launch Commit Criteria

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Alpha Magnetic Spectrometer 02Mission
Operations Pre-Launch

• KSC Flow
• Arrive at Space Station Processing Facility
  (SSPF)
• Integrate remainder of AMS-02 hardware
• Top-off SFHe and Warm He Gas Supply
• Power up/checkout Avionics and charge Magnet
• Discharge Magnet and power off all systems
• Functional Interface Test (FIT)
• Power up/checkout avionics, no Magnet Charge

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Alpha Magnetic Spectrometer 02Mission
Operations Pre-Launch

• KSC Flow (continued)
• Load into canister and transport to Canister
  Rotation Facility (CRF)
• Rotate canister in CRF (may require use of small,
  payload-mounted vent pump)
• Transport to Pad for Vertical Installation in
  Payload Change-out Room (PCR)
• Interface Verification Test (IVT)
• End to End Tests in STS
• Continued payload servicing until L-88 hours
• Continued payload monitoring until L-9 minutes

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Alpha Magnetic Spectrometer 02Mission
Operations Initial Operations
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Alpha Magnetic Spectrometer 02Mission
Operations Pre-Launch
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Alpha Magnetic Spectrometer 02Mission
Operations Pre-Launch

• PRE-LAUNCH OPERATIONS
• Activate/checkout AMS-02 avionics subsystems and
  thermally condition payload
• Approximately 1000 1500 W for J-Crate,
  Cryo-valves, Cryo-coolers, CAB critical
  functions, and SFHe Tank Vent Pump
• Maximum of 2 kW (peak) for calibration and
  contingency based upon thermal load in purged PLB
• No magnet charging possible on STS APCU power
  supplied to prime PDS side B has no
  connectivity to the CAB
• Final cryogenic servicing
• Cryosystems monitoring

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Alpha Magnetic Spectrometer 02Mission
Operations
PRE-LAUNCH OPERATIONS Cryogenic Ground Support
Equipment Layout in PCR
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Alpha Magnetic Spectrometer 02Mission
Operations Pre-Launch

• Pre-Launch Safety
• PCR / PLB payload operations are being evaluated
  for ground and vehicle safety hazards.

• Cryogenic temperature evaluation
• Vent Pump operations (110 VAC) Pre-Launch only
• He venting exhausted out PCR
• Payload servicing and check-out in vertical
  orientation
• Will be tested prior to arrival at KSC
• PLB thermal loads analysis in work

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Alpha Magnetic Spectrometer 02Mission
Operations Pre-Launch

• SFHe Tank Vent Pump

• Pre-Launch only
• T0 110 VAC interface and ground safety being
  worked with STS Program and KSC
• Rotating parts analysis to be performed

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Alpha Magnetic Spectrometer 02Mission
Operations Pre-Launch

• T0 Umbilical Interfaces
• T0 Interfaces via ROEU PDA Vent Pump,
  Cryocoolers, valves, CAB critical monitoring
  functions, and J-Crate

• Power (120 VDC) to PDS
• Direct feed to Vent Pump (110 VAC) Pre-Launch
  Only
• 1553 for command/telemetry requirements
• High Rate Data via RS422
• Continuous data using both paths (redundancy)
  until L-9 min to monitor health status of Cryo
  systems (Vacuum Case pressure and SFHe
  pressure/temp), supporting GO / NO GO Call from
  AMS-02 See Page 15

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Alpha Magnetic Spectrometer 02Mission
Operations Pre-Launch

• Pre-Launch Configuration
• Payload Data Interface Panel 2 (PDIP2)

• Low rate data (1553) is routed through T0
  umbilical to MLP GSE computers from Shuttle PDIP2
  with the AMS-02 1553 switch in the T0
  position, and program provided jumper installed
  on PDIP2 front panel J4 connector
• High rate data (RS422) is routed through T0
  umbilical to MLP GSE computers from Shuttle PDIP2
  via payload provided cable installed between
  PDIP2 front panel J103 and J105 connectors.

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Alpha Magnetic Spectrometer 02Mission
Operations Pre-Launch

• Pre-Launch Standard Switch Panel Configuration

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Alpha Magnetic Spectrometer 02Mission
Operations Pre-Launch

• Pre-launch Timeline
• Installation at L-32 days through L-30 minutes
  operations
• L-88 hours complete Top-off SFHe activities
• L-80 hours payload disconnect, PLB door close
• At L-30 minutes
• Close SFHe Tank Vent Valve and deactivate Vent
  Pump
• Deactivate Cryo-coolers
• Power down all equipment with the exception of
  J-Crate and necessary CAB functions to monitor of
  cryogenics system health (limited to 120W)
• Monitor health status of cryogenic systems until
  L-9 min GO / NO GO Call from AMS-02 based on
  Cryogenic System Health
• At L-9 minutes Complete Payload Power-Down

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Alpha Magnetic Spectrometer 02Mission
Operations Pre-Launch Activity
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Alpha Magnetic Spectrometer 02Mission
Operations Pre-Launch

• Safety Launch Commit Criteria
• Loss of vacuum case seal immediately prior to
  launch results in over-pressurization of the SFHe
  Tank during ascent, over-pressurizing the PLB and
  possibly damaging the Aft Bulkhead

• Worst case leak in VC requires 23 minutes to
  generate sufficient He to burst disks, releasing
  gas into PLB
• PLB over-pressurization must occur between L30
  seconds and L1 minute to result safety hazard
• Monitor VC health / status until L-9 minutes
• Compared to trend data established over the
  lifetime of the experiment to indicate
  occurrence, and make the GO / NO GO Call
• Minimum of three measurements of temperature and
  pressure within the SFHe Tank will provide this
  data on redundant paths
• For operational scenarios that involve the burst
  disks rupturing at any other time, no hazard has
  been identified

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Alpha Magnetic Spectrometer 02Mission
Operations Pre-Launch

• Payload Launch Commit Criteria
• The only payload LCC that has been defined
  relates to the operability of ISS Bus A prior to
  payload bay closure. Because this Bus is
  required for magnet charging, verification that
  this Bus is operational must be made, or possibly
  corrected, prior to launch.

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LAUNCH
Alpha Magnetic Spectrometer 02Mission
Operations
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Alpha Magnetic Spectrometer 02Mission
Operations
ASCENT OPERATIONS
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Alpha Magnetic Spectrometer 02Mission
Operations Ascent

• SFHe Tank Nominal Vent Valve Operation
• He Vapor pressure in SFHe tank must be maintained
  at a pressure to keep LHe temperature superfluid
• Endurance Mission Success
• Vent valve to open when PLB pressure is less than
  the SFHe vapor pressure (lt 20 millibars)
• Must occur during Powered Flight
• Porous plug, which allows He vapor vent while
  containing the liquid within the tank
• When the valve is opened, liquid must not be in
  contact with the porous plug, which could act as
  a pump to drain the SFHe liquid from the tank
• Not a safety issue, due the rate of pumping that
  would occur
• Endurance Mission Success
• Porous plug is designed to be parallel to the
  acceleration vector during ascent. G-forces
  during powered flight will ensure only vapors are
  in contact with the plug at vent opening.

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Alpha Magnetic Spectrometer 02Mission
Operations Ascent

• SFHe Tank Nominal Vent Valve Operation
  (continued)
• Avionics Baroswitch Electronics (BSE) will open
  the vent valve
• Barometric switch to trigger the BSE when PLB
  pressure is less than the SFHe (15 20
  millibars)
• Time-tagged Discrete Output Low (DOL) command via
  Backup Flight System (BFS) General Purpose
  Computer (GPC) to trigger BSE as a backup _at_ LTBD
  minutes
• In the event of an STS abort, the barometric
  switch will trigger BSE to close the vent valve
  during descent (non-hazard)
• Any potential ignition sources will be compliant
  with NSTS/ISS 18978B, NS2/81-M082

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Alpha Magnetic Spectrometer 02Mission
Operations
STS ON-ORBIT OPERATIONS
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Alpha Magnetic Spectrometer 02Mission
Operations STS On-Orbit

• Outline
• STS On-Orbit Interfaces
• Re-configure / Set-up AFD Equipment
• PDIP1 and PDIP2
• Digital Data Recording System-02 (DDRS-02)
• Payload Check-out
• Payload Deploy

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Alpha Magnetic Spectrometer 02Mission
Operations STS On-Orbit

• Configure AFD Equipment
• Configure PDIP1 and PDIP2
• Unstow and activate Digital Data Recorder
  System-02 (DDRS-02)
• Operated on Next Generation Laptop System (NGLS)
  computer
• Serves as a back-up recording device for payload
  data that is down-linked via the Ku-Band
• Single hard disk in the NGLS computer will
  provide recording capability for 40 hours worth
  of check-out data
• Back-up hard-disks flown (contingency)
• Activate Assembly Power Converter Units (APCUs)
• Powers AMS-02 Payload

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Alpha Magnetic Spectrometer 02Mission
Operations STS On-Orbit

• Configure PDIP1

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Alpha Magnetic Spectrometer 02Mission
Operations STS On-Orbit

• Configure PDIP2

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Alpha Magnetic Spectrometer 02Mission
Operations STS On-Orbit

• Digital Data Recorder System-02 (DDRS-02)

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Alpha Magnetic Spectrometer 02Mission
Operations STS On-Orbit

• Payload Power-up and Check-out
• Cryo-coolers and housekeeping data at MET 2 hr
  30 minutes
• Activate/checkout AMS-02 avionics subsystems and
  thermally condition payload
• Peak power draw on shuttle 2 kW based upon
  thermal loads in PLB
• No magnet charging possible on STS APCU power
  supplied to prime PDS side B has no
  connectivity to the CAB.
• Dock with ISS (MET Day 3)
• Make GO / NO GO Call prior to transfer on MET Day
  4
• Power down AMS-02 prior to transfer operations

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Alpha Magnetic Spectrometer 02Mission
Operations ISS

• Simplified Payload Power-Up Sequence

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Alpha Magnetic Spectrometer 02Mission
Operations STS On-Orbit

• Payload Deploy
• Grapple Flight Releasable Grapple Fixture (FRGF)
  with Shuttle Remote Manipulator System (SRMS)
• Disconnect Remotely Operated Electrical Umbilical
  (ROEU) and operate Payload Retention Latch
  Actuators (PRLAs)
• AMS-02 removed from PLB by SRMS

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SRMS TO SSRMS HAND-OFF OPERATIONS
Alpha Magnetic Spectrometer 02Mission
Operations
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Alpha Magnetic Spectrometer 02Mission
Operations Hand-Off

• Payload Hand-Off
• Grapple Power and Video Grapple Fixture (PVGF)
  with Space Station RMS (SSRMS) located on MT
• External Berthing Cues System (EBCS) utilized to
  verify final approach to Attach Site (Power and
  Video functions routed through SSRMS)
• SSRMS supplies power for AMS-02 Heaters during
  Transfer Ops
• Magnet charging on SSRMS Operationally Controlled
• SSRMS Nominal power bus is connected to PDS side
  B, which has no connectivity to the CAB
• Magnet charge initiation requires a series of
  up-linked commands, none of which are stored
  on-board the computer
• The payload has no communications via the PVGF to
  receive these commands

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Alpha Magnetic Spectrometer 02Mission
Operations Hand-Off

• Payload Hand-Off (continued)
• SRMS release of AMS
• Transfer to S3 attach site
• Attach AMS-02 to S3 upper inboard site
  mechanical/ electrical (via PAS)
• Deactivate power via PVGF
• Connect UMA
• Activate payload power via UMA
• Power up Avionics, perform abbreviated avionics
  checkout to verify payload power and
  communications
• SSRMS Ungrapple

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Alpha Magnetic Spectrometer 02Mission
Operations Hand-Off

• Transfer to ISS

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Alpha Magnetic Spectrometer 02Mission
Operations Hand-Off

• Berthing to ISS S3 Upper / Inboard

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Alpha Magnetic Spectrometer 02Mission
Operations
ISS ON-ORBIT OPERATIONS
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Alpha Magnetic Spectrometer 02Mission
Operations ISS

• On-Orbit ISS Operations
• Power-up and complete systems check-out
• Thermal monitor and condition cryosystems
• Power-down all subsystems except those integral
  to magnet charging
• Begin magnet charging operations
• Post-magnet charge systems power-up and check-out

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Alpha Magnetic Spectrometer 02Mission
Operations ISS

• On-Orbit ISS Operations (continued)
• Experiment Science
• 3 years operation with magnet
• After LHe depletion and magnet is no longer
  functional, the payload will continue with
  further physics goals
• Nominal End of Mission
• No STS flights for return of AMS-02 Payload.
• Will remain on ISS for duration of ISS mission
  life, and re-enter with ISS vehicle

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Alpha Magnetic Spectrometer 02Mission
Operations ISS

• On-Orbit ISS Operations (continued)
• Primary control of AMS-02 is from ground
• Only safety related operation is Cryomagnet
  charge
• Only safety hazard when EVA/EVR operations on
  AMS-02
• Requires a series of up-linked commands (not
  stored on-board)
• Data down-linked via ISS Ku-Band
• Proposed to use S-Band to downlink minimal health
  data
• In case of loss of power and/or communications,
  payload is safe without services

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Alpha Magnetic Spectrometer 02Mission
Operations ISS

• Simplified Payload Power-Up Sequence

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EVA Compatibility
Alpha Magnetic Spectrometer 02Mission
Operations
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Alpha Magnetic Spectrometer 02Mission
Operations EVA

• Translation Paths
• Translation paths were evaluated by Worksite
  Analysis and in NBL
• EVA translation in proximity to and in contact
  with AMS-02 payload approved for both STS and ISS
  EVA
• For ISS EVA when magnet charge is possible, suit
  certification for operations in magnetic field
• EMU 300 Gauss
• Orlon 175 Gauss
• Hazard avoided by magnet discharge prior to EVA
  or limiting EVA exposure via Keep Out Zones
• Translation allowed between attach sites on truss
  and up USS to access PVGF
• Translation path for foldable ROEU to be
  validated in NBL

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Alpha Magnetic Spectrometer 02Mission
Operations EVA

• PVGF Translation Path

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Alpha Magnetic Spectrometer 02Mission
Operations EVA

• S3 Truss Translation Paths

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Alpha Magnetic Spectrometer 02Mission
Operations EVA

• Translation Path

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Alpha Magnetic Spectrometer 02Mission
Operations EVA

• EVA Keep Out-Zones
• The AMS-02 Vacuum Case ribs are not designed to
  withstand EVA Kick-loads
• Worked with the EVA Projects Office
• Reviewed during NBL operation
• Not deemed a concern
• VC is classified as an EVA Keep Out Zone
• Additionally, the Star Tracker Baffles are also
  considered EVA Keep Out Zones (sharp edges)
• Detailed thermal analysis shall be performed to
  determine if any additional areas of concern are
  identified due to EVA touch temp violations

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CONTINGENCY OPERATIONS
Alpha Magnetic Spectrometer 02Mission
Operations
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Alpha Magnetic Spectrometer 02Outline

• EVA Operation
• STS
• ROEU Release
• PRLA Release
• FRGF Release
• ISS
• EVA Interface Panel Operations
• PAS Release
• PVGF Release
• ROEU Folding Bracket
• NBL Testing
• Completed Testing
• Forward Work
• EVR Operation
• Mission Abort

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Alpha Magnetic Spectrometer 02Contingency
Operations STS EVA

• AMS-02 designed to be compatible with
• Manual ROEU disconnect
• Access issue only
• Can be performed from Orbiter Sill
• Manual Payload Retention Latch Actuators (PRLA)
  operation
• Access issue only
• Can be performed from Orbiter Sill
• Flight Releasable Grapple Fixture (FRGF) Release
• Access issue only
• Can be performed from Orbiter Sill or post-deploy

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Alpha Magnetic Spectrometer 02Contingency
Operations STS EVA

• AMS-02 in PLB (ROEU and PRLA Access)

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Alpha Magnetic Spectrometer 02Contingency
Operations STS EVA

• FRGF Release

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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• EVA Interface Panel
• Passive UMA Removal contingency operation as
  required by SSP-57003
• Capture Bar Unloading and Release contingency
  operation as required by SSP-57003
• PVGF Contingency Release
• PVGF Grapple Release
• Latching End Effector (LEE) Release
• Foldable ROEU

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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• EVA Interface Panel
• EVA Interface Panel allows for redundant avionics
  interfaces in contingency scenario
• Connectors will meet the mating/demating
  requirements identified in letter MA2-99-170, and
  comply with (SSQ 21654)
• Connections are swapped to effect changing A
  (prime) / B (redundant) channels in the event
  that prime capability is lost
• Data Payload Redundancy Only
• Power Payload and ISS Redundancy
• Cryomagnet charge can be performed on UMA powered
  PDS A-side (prime) bus only.

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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• EVA Interface Panel and UMA Operations

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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• Capture Bar Unload/Release
• WIF/PFR location identified on Truss for this
  operation (as necessary)
• Handrails on Keel accessible during operation,
  Keel available for additional handhold location
• Capture Bar Load Release Screws are captive and
  can be loosened with PGT/extension
• Once unloaded capture bar handle must be lifted
  and pulled to release
• Procedure/access verified by NBL Test

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Alpha Magnetic Spectrometer 02Capture Bar
With Removal Handle
PAS Platform Passive Half
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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• Capture Bar Unload

Approximately 80 turns Alternating for
balanced load release
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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• Capture Bar Release

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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• Capture Bar Handle Release Handrail Locations

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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• PVGF Release
• PVGF can be released by releasing Grapple Pin or
  by releasing LEE (ISS EVA standard procedure)
• Handrail placement on USS provides translation
  path
• WIF location on USS Sill Beam for PFR Access w/
  nearby handrails for installation of PFR
• Both Grapple Pin release and LEE release
  accessible from same location, operation
  performed with PGT/extension
• Access verified by NBL Test

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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• PVGF Release

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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• PVGF Handrails/WIF

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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• PVGF Related Handrails

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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• Foldable ROEU PDA
• Designed to be compatible with folding in STS or
  on ISS
• Designed as contingency to limit protrusion
  outside of standard Attach Payload Envelope,
  bracket holding Passive Disconnect Assembly (PDA)
  for Remotely Operated Electrical Umbilical can be
  folded down.
• Working with EVA Project Office to define
  additional requirements (if applicable) for
• Handrails
• WIF
• Actuation force measurement test
• Additional hardware to be developed to
  demonstrate access on existing NBL mockup
• EVA approved MSWG approved Push-In-Place (PIP)
  Pins used for locking feature in both positions

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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• Foldable ROEU (extended)

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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• Foldable ROEU (extended)

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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• Foldable ROEU (folded)

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Alpha Magnetic Spectrometer 02Contingency
Operations ISS EVA

• Foldable ROEU (folded)

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NBL Testing
Alpha Magnetic Spectrometer 02Mission
Operations - EVA
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Alpha Magnetic Spectrometer 02Mission
Operations - EVA

• NBL Testing
• First access test in NBL completed in March 2002
  with low fidelity mockup (only Passive PAS)
• Second NBL access test (with higher fidelity
  mockup, full experiment envelope) performed in
  November 2002
• No mission specific NBL testing required
• No specific EVA training requirements

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Alpha Magnetic Spectrometer 02Mission
Operations - EVA

• NBL Testing (continued)
• Testing to evaluate AMS-02 Contingency EVA
  interfaces was performed November 12th thru 15th,
  2002 (five astronauts performed tasks)
• Testing included
• PVGF Contingency Release
• PVGF Grapple Release
• LEE Release
• Capture Bar Unloading and Release
• Connector Panel Access/Evaluation
• Passive Umbilical Mating Assembly (UMA) bolt
  access
• And, crew translation path evaluation

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Alpha Magnetic Spectrometer 02Mission
Operations - EVA

• NBL Test Results
• All tested tasks were deemed acceptable as
  documented in Crew Consensus Report (reference
  letter CB-02-129)
• Only minor issues identified with
• Labeling (updates completed and approved)
• Fit-checks (verified with flight hardware at
  Lockheed Martin)
• Connector clocking (updated and approved)
• Potential future work for Foldable ROEU

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Alpha Magnetic Spectrometer 02Phase II Flight
Safety Review

• Contingency EVR Operations
• Single operation considered for EVR relocation of
  AMS-02
• SSRMS operation in magnetic field is not
  certified
• Hazard avoided by magnet discharge prior to EVR

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Alpha Magnetic Spectrometer 02Mission
Operations - Contingency

• Mission Abort
• In the event of an abort (e.g. RTLS, TAL, or any
  other return with AMS-02 still in STS 4 PRLAs
  engaged)
• Close vent valve when PLB pressure exceeds 15
  20 millibars
• SSP supplied 28 VDC only
• APCU supplied 120 VDC to payload PDS powered off
• Upon landing, services should be applied via the
  T0 Umbilical, to perform the following
• Allow internal Electronics to Monitor He tank
  pressure
• Operate vent valve and vent pump
• Not a safety concern, but rather a refurbishment
  concern (dont want to rupture burst disks)
• Initial projection from KSC for nominal landing
  indicates 10 hrs.
• Endurance Mission Success for turn-around

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Backup Slides
Alpha Magnetic Spectrometer 02Mission
Operations
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Alpha Magnetic Spectrometer 02Phase II Flight
Safety Review
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Alpha Magnetic Spectrometer 02Payload Avionics
Universal Interface Diagram
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Alpha Magnetic Spectrometer 02Payload
Interface Diagram STS Pre-Launch
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Alpha Magnetic Spectrometer 02Payload
Interface Diagram STS Ascent
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Alpha Magnetic Spectrometer 02Payload
Interface Diagram STS On-Orbit
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Alpha Magnetic Spectrometer 02Payload
Interface Diagram Hand-Off
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Alpha Magnetic Spectrometer 02Avionics Systems
Interface Diagram ISS
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Alpha Magnetic Spectrometer 02Mission
Operations Scrub Launch Activity

• Scrub Turnaround Scenario

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Alpha Magnetic Spectrometer 02Mission
Operations Scrub Launch Activity

• Scrub Recycle Turnaround Scenario