Alpha Magnetic Spectrometer 02 AMS02 KSC TIM

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Alpha Magnetic Spectrometer 02 (AMS-02)KSC TIM

• Overview
• Prepared By P. Nemeth

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Objective

• AMS, the Alpha Magnetic Spectrometer, is a space
  borne experiment scheduled for a three years
  mission on the International Space Station. It
  is designed to study
• the presence or absence of antimatter in distant
  galaxies through the detection of cosmic
  anti-nuclei as anti-Helium and anti-Carbon.
• the origin and structure of dark matter which is
  believed to make up 90 of the known universe
• the origin and the composition of charged cosmic
  rays as well as other phenomena which may exist
  in nature which we have not yet imagined or had
  the tools to discover

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Heritage

• The same technology used for research in particle
  physics is adapted in AMS for space application.
• The charge sign and magnetic rigidity of cosmic
  rays will be determined by the deflection of
  their trajectory in the magnetic field of the
  instrument, while an array of precision particle
  detectors will perform redundant measurements of
  charge magnitude, velocity and energy.
• The operation principles of the apparatus have
  been tested in the space environment during a
  precursor flight of the experiment , 10 days of
  successful data taking onboard of the shuttle
  Discovery in June 1998.

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Principle Components

• Super-Fluid Helium Dewar
• Super-conducting Magnet and Associated Avionics
• Power Distribution System
• Data Acquisition System
• Particle Detectors and Associated Electronics
• Transition Radiation Detector (TRD)
• Time of Flight (TOF)
• Tracker
• Electromagnetic Calorimeter (ECAL)
• Ring Imaging Cherenkov Counter (RICH)
• Anti-Coincidence Counter (ACC)

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AMS-02 Cut-Out View
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Mechanics for Electronics Crates Boxes
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ISS 108x80m 420T 86KW 400km AMS
3x3x3m 7T 2KW 3 years
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NASA AMS Electrical Interfaces on ISS

• Power
• 109-124VDC
• 2KW max
• EMC
• LRDL
• 1553B Bus
• 1 Kbit/s in
• 10 Kbit/s out
• HRDL
• Taxi F/O
• lt2Mbit/sgtorbit

Ensure AMS side of interfaces conform to NASA
requirements
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AMS-02 STS Power Distribution Block Diagram
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Passive UMA EVA Connector Layout
UMA Passive Half
PWR 1
PWR 1
PWR 2
PWR 2
1553 Bus Stub A/ 1553 Bus Stub B/ RT Address
Avionics (Primary)
1553 Bus Stub A
1553 Bus Stub B RT Address
Fiber Optic
Fiber Optic
J1
1553 Bus A/ 1553 Bus B/ RT Address (Redundant)
Avionics (Redundant)
Fiber Optic (Redundant)
AMS EVA Interface Panel
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Data Overview
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Subdetector Requirements Summary
7 Gbit/sec ? 2 Mbit/sec ? Restrict Rate Size
Specify, design, develop, produce High Speed,
High Capacity, Low Power, Low Weight, Reliable
Signal Data Processing ON ORBIT !
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AMS-02 Data Interfaces

• J-Crate Front-End interface for all data
  from/to AMS
• RS-422
• 1553 (STS and ISS)
• HRDL
• ACOP Pressurized component
• Express Locker design
• Data Recorder
• Continuous communication to AMS
• Burst Playback mode for downlink

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J-Crate Scheme test setup 4 Main Computer
Interfaces
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ACOP Design Front View
All the Boards are replaceable
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1553 Interface Block Diagram
AMS-02 J-Crate
J1553 RT 28
To/From STS OIU2
J1553 RT 4
To/From STS OIU2
J1553-Y
To/From ISS PLMDM
J1553-Z
To/From ISS (Via EVA Connector Swap)
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1553 Interface Architecture

• Separate 1553 Interfaces for STS and ISS
• STS interface includes two Remote Terminals
  (RTs), addresses 28 and 4
• ISS interface is somewhat unconventional
• Electrically only one RT
• Logically reacts as four 1553 Protocol Engines
• At start-up, all four in Bus-Monitor mode
• First command to bring up system is not
  acknowledged (solely used to select which
  Protocol Engine goes to RT)

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Data System Components

• Crate Electronics Box
• J-Crate Performs Top Level DAQ, contains four
  JMDCs, JLIF, and JHIF
• JMDC Main Data Computer Combines Housekeeping
  data and Science data for distribution, performs
  minor processing , combines pieces of event data
  into complete event, converts CAN and AMS Wire to
  1553, RS422, and Fiber, also TRD Gas control and
  TTCS control.
• JBU Buffer Unit Contained within JMDC, 2GB
  buffer (1GB/hr)
• JLIF Low-rate data Interface Transceivers for
  1553
• JHIF High-rate data Interface Fiber Interface
  and Transceivers for RS422
• USCM Universal Slow Control Module 8051 based
  CPU and O/S with processing s/w (data gathering
  and blocking into types)
• CDP Common Digital Part Gate Array, DSP,
  Memory, s/w code to communicate on AMS Wire
  performs digitizing, blocking and compression
• CDDC Command Distributor/Data Concentrator
  Reads CDP queue/combines pieces of single events,
  distributes commands to CDPs
• AMS Wire Hi-performance serial 100 Mbps custom
  wire (similar to ESA Space Wire)
• LVDS Low Voltage differential signal
• JPD J-Crate Power Distribution Box

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Housekeeping Data Overview (equivalent to NASA
HS Data)
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Science Data
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Testing
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Data Compatibility Testing

• Suitcase Test Environment for Payloads (STEP)
  Testing (May 2003)
• Preliminary Interface Test
• Taxiscope testing (June 2003)
• 1553 RT Validation testing (June 2003)
• APS testing (June 2003)
• Orbiter Interface Unit (OIU) Lab Testing (June
  2003)
• Functional Interface Test (FIT)
• Electrical Simulation Test Laboratory (ESTL)
  testing RS-422

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Final KSC Checkout

• Payload Rack Checkout Unit (PRCU) testing at JSC
• PTCS testing at KSC (during on-line processing)
• OIU testing in Launch Processing Integration
  Stand (LPIS)
• Orbiter End to End Test

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Operations
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Operations Centers

• AMS-02 support personnel will staff a Payload
  Operations Control Center (POCC) and Science
  Operations Center (SOC) for the entire 3-year
  mission
• ACOP will be launched on STS 3 to 6 months prior
  to AMS-02 and checked out prior to AMS arrival
• The location of these facilities will change
  based on mission phase
• Prior to ACOP launch (subset) through AMS-02
  Launch plus 3 months will be at JSC
• Launch plus 3 months until EOM at CERN
• Some subset will exist at KSC prior to launch also