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Electronics updates since Phase II Baroswitch Electronics (BSE)

Alpha Magnetic Spectrometer – 02 Phase III PSRP / SRP Electronics Summary January 12, 2010 Timothy J. Urban / ESCG / Barrios Technology. AMS02 Electronics Summary Outline. Electronics updates since Phase II Baroswitch Electronics (BSE) Cryomagnetic Pilot Valve Switch (CPVS) Box

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Electronics updates since Phase II Baroswitch Electronics (BSE)

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  1. Alpha Magnetic Spectrometer – 02Phase III PSRP / SRPElectronics SummaryJanuary 12, 2010Timothy J. Urban / ESCG / Barrios Technology

  2. AMS02 Electronics SummaryOutline • Electronics updates since Phase II • Baroswitch Electronics (BSE) • Cryomagnetic Pilot Valve Switch (CPVS) Box • Upstream Power Inhibits • Power Circuit Protection • Wire sizing • Component de-rating • High Voltages • Component accessibility • Corona testing • Grounding • Electronics • Thermal Control System Blankets • STS IVA Volume Hardware – Digital Data Recording System Tim Urban / ESCG

  3. AMS02 Electronics SummaryElectronics updates since Phase II • Baroswitch Electronics (BSE) – Design Evolved • Uses STS Standard Switch Panel 28VDC (less than one amp). • When STS PLB pressure < 15 mbar, a baroswitch closes. • This is a trigger to open a series of valves which opens the AMS flight vent, allowing LHe boil-off vapor to exhaust from the LHe tank, maintaining LHe temperature below the super-fluid Lamda point. • Time-tagged (180 seconds) STS Back-up Flight Computer Discrete Output Low (DOL) is a redundant trigger to this valve open operation. • Redundant trigger is “Or’ed” by the BSE. • The DOL, if later, will not undo the baroswitch trigger, and vice-versa. • Nominally occurs during powered ascent to prevent LHe contact on porous plug: Mission Success only – No safety implication. • Back-up plan would be for payload commands to open vent during an STS Orbiter +X maneuver. Tim Urban / ESCG

  4. AMS02 Electronics SummaryElectronics updates since Phase II • Cryomagnetic Pilot Valve Switch (CPVS) Box – New Addition • Boosts the trigger power from BSE to meet specifications / requirements of the valves. • Powered by payload Uninterruptible Power Supply (UPS) during ascent. • UPS power bus isolated from all other payload power buses. Tim Urban / ESCG

  5. AMS02 Electronics SummaryElectronics updates since Phase II Tim Urban / ESCG

  6. AMS02 “Global” Interfaces Upstream Inhibits (first level) Tim Urban / ESCG

  7. AMS02 Electronics SummaryUpstream Power Inhibits Tim Urban / ESCG

  8. AMS02 Electronics SummaryUpstream Power Inhibits • Inhibits are used to disable payload power prior to connector mate / de-mate (dead-faced). • Two upstream inhibits have been identified for all STS and ISS power sources. • These inhibits are STS and ISS vehicle utilizations that are enacted by flight procedure (OCAD). Tim Urban / ESCG

  9. AMS02 Electronics SummaryPower Circuit Protection • All payload power and data wire sizing, for both STS and ISS interfaces, was designed “carrying-through” the wire sizing used on the vehicle side of the interfaces (ICD compliant). • Payload designed and selected proper materials for integration cabling and circuit protection devices to meet: • NSTS 1700.7B, “Safety Policy and Requirements for Payloads using the Space Transportation System” • NSTS 1700.7B ISS Addendum, “Safety Policy and Requirements for Payloads using the International Space Station” • NASA Technical Memorandum #102179, “Selection of Wires and Circuit Protection Devices for NSTS Orbiter Vehicle Payload Electrical Circuits” Tim Urban / ESCG

  10. AMS02 Electronics SummaryPower Circuit Protection Tim Urban / ESCG

  11. AMS02 Electronics SummaryPower Circuit Protection PDS Protective Devices – Derating Summary Tim Urban / ESCG

  12. AMS02 Electronics SummaryPower Circuit Protection PDS Protective Devices – Derating Summary Tim Urban / ESCG

  13. AMS02 Electronics SummaryPower Circuit Protection BSE Protective Devices – Derating Summary Tim Urban / ESCG

  14. AMS02 Electronics SummaryHigh Voltages • All payload high voltage sources are potted, and inaccessible; either by sub-system structure or MLI blanket. • All high voltage cables have been properly selected and de-rated (COTS equipment). Tim Urban / ESCG

  15. AMS02 Electronics SummaryHigh Voltages Tim Urban / ESCG

  16. AMS02 Electronics SummaryHigh Voltages Example of High Voltage Component Potting. ECAL Photo Multiplier Tube Tim Urban / ESCG

  17. AMS02 Electronics SummaryHigh Voltages Coronal Discharge Testing of TRD High Voltage Straws. Tim Urban / ESCG

  18. AMS02 Electronics SummaryHigh Voltages Corona Test Results for TRD UTE Tim Urban / ESCG

  19. AMS02 Electronics SummaryPayload Grounding • The AMS-02 payload structure is mechanically grounded, depending on mission phase, as follows: • STS – via the payload mounting trunnions • SSRMS – via the SSRMS / PVGF interface • ISS CAS site – via the PAS guide vane pins • Payload grounds are designed for DC component of Class R (< 2.5mOhm), so the intent will meet Class H. • Payload structure riveted joints have been measured in compliance with this – will repeat after integrated TVT to demonstrated no thermal relaxation. • Electronics are assembled with Alodined links that ground them together – then bond straps ground them to the radiators, which are ground strapped to the USS. Tim Urban / ESCG

  20. AMS02 Electronics SummaryPayload Grounding – RAM Electronics Alodined mechanical links Ground Straps Tim Urban / ESCG

  21. AMS02 Electronics SummaryPayload Grounding • Electronics ground strap. Tim Urban / ESCG

  22. Vacuum case is grounded to USS via 00AWG wires (QTY 2). + Z + X + Y + X (RAM) ORBITER + Y + Z ISS + Y + Z + Y + X (RAM) + Z + X ISS ORBITER AMS02 Electronics SummaryPayload Grounding VC Bonding Strap 1 VC Bonding Strap 2 VC Bonding Strap 2 January 12, 2010 Tim Urban / ESCG 22

  23. AMS02 Electronics SummaryPayload Grounding • Vacuum case is grounded to USS via 00AWG wires (QTY 2). VC Bonding Strap 2 VC Bonding Strap 1 Tim Urban / ESCG

  24. AMS02 Electronics SummaryPayload Grounding • MLI Blanket Class S bond wire grounded. Tim Urban / ESCG

  25. AMS02 Electronics SummaryUngrounded MLI Blankets Non-grounded interior MLI blankets will require EMEP TIA: • TRDGB (XE & CO2 tanks, Valve block bootie • TTCS tubing lines • Cryocooler evaporators Tim Urban / ESCG

  26. Digital Data Recording System (DDRS) Records back-up of down-linked science data on-board STS Provides contingency STS crew capabilities: Limited payload systems health monitor Limited payload command (worked with MCC-H and POCC) Materials and flammability assessment complete Full scope of EMI testing complete (susceptibility and emissions) AMS02 Electronics SummaryIVA Habitable Volume Equipment January 12, 2010 Tim Urban / ESCG 26

  27. AMS02 Electronics SummaryIVA Habitable Volume Equipment Configure Payload Data Interface Panel#1 (PDIP1) NOTE: Placards may not represent flight configuration. January 12, 2010 Tim Urban / ESCG 27

  28. AMS02 Electronics SummaryIVA Habitable Volume Equipment USB/422 Adaptor Box with Integrated PDIP Cable PGSC based “AMS Laptop” January 12, 2010 Tim Urban / ESCG 28

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