Alpha Magnetic Spectrometer Alpha Magnetic Spectrometer – 02 Phase III PSRP / SRP Electronics Summary January 12, 2010 Timothy J. Urban / ESCG / Barrios Technology

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG2 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 AMS02 Electronics Summary Outline

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG3 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. AMS02 Electronics Summary Electronics updates since Phase II

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG4 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. AMS02 Electronics Summary Electronics updates since Phase II

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG5 AMS02 Electronics Summary Electronics updates since Phase II

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG6 AMS02 “Global” Interfaces Upstream Inhibits (first level)

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG7 AMS02 Electronics Summary Upstream Power Inhibits

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG8 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). AMS02 Electronics Summary Upstream Power Inhibits

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG9 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 B, “Safety Policy and Requirements for Payloads using the Space Transportation System” –NSTS B 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” AMS02 Electronics Summary Power Circuit Protection

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG10 AMS02 Electronics Summary Power Circuit Protection

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG11 AMS02 Electronics Summary Power Circuit Protection PDS Protective Devices – Derating Summary CIRCUITS PROTECTIVE DEVICEPART NUMBERMIL SPEC MINIMUM TRIP THRESHOL D (Amp) MINIMUM TRIP DECISION TIME MAIN PWR FEED Local Heaters FuseP600L MIL-PRF sec 120 VDC Heater Lines FuseP600L MIL-PRF sec FuseP600L MIL-PRF sec FuseP600L MIL-PRF sec 120 VDC CCEB Line Solid State Limiting Circuit ms 120 VDC CCS Line FuseP600L MIL-PRF sec Solid State Limiting Circuit ms 28 VDC 5A Output Lines Solid State Limiting Circuit ms 28 VDC 10A Output Line Solid State Limiting Circuit ms

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG12 AMS02 Electronics Summary Power Circuit Protection CIRCUITS PROTECTIVE DEVICEPART NUMBERMIL SPEC MINIMUM TRIP THRESHOL D (Amp) MINIMUM TRIP DECISION TIME AUX PWR FEED Local Heaters FuseP600L MIL-PRF sec 120 VDC Heater Lines FuseP600L MIL-PRF sec FuseP600L MIL-PRF sec FuseP600L MIL-PRF sec 120 VDC CCEB Line Solid State Limiting Circuit ms 28 VDC 5A Output Lines Solid State Limiting Circuit ms 28 VDC 10A Output Line Solid State Limiting Circuit ms PDS Protective Devices – Derating Summary

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG13 AMS02 Electronics Summary Power Circuit Protection CIRCUITS PROTECTIVE DEVICEPART NUMBERMIL SPEC MINIMUM TRIP THRESHOLD (Amp) MINIMUM TRIP DECISION TIME MAIN PWR FEED 28 VDC Input Line (<1 Amp) FuseP600L MIL-PRF sec BSE Protective Devices – Derating Summary

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG14 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). AMS02 Electronics Summary High Voltages

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG15 AMS02 Electronics Summary High Voltages

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG16 AMS02 Electronics Summary High Voltages Example of High Voltage Component Potting. ECAL Photo Multiplier Tube

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG17 AMS02 Electronics Summary High Voltages Coronal Discharge Testing of TRD High Voltage Straws.

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG18 AMS02 Electronics Summary High Voltages Corona Test Results for TRD UTE

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG19 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. AMS02 Electronics Summary Payload Grounding

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG20 AMS02 Electronics Summary Payload Grounding – RAM Electronics Alodined mechanical links Ground Straps

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG21 Electronics ground strap. AMS02 Electronics Summary Payload Grounding

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG22 AMS02 Electronics Summary Payload Grounding + X (RAM) + Y + Z ISS + Z + X + Y ORBITER VC Bonding Strap 1 Vacuum case is grounded to USS via 00AWG wires (QTY 2). ORBITER + X (RAM) + Y + Z ISS + Z + X + Y VC Bonding Strap 2

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG23 AMS02 Electronics Summary Payload Grounding Vacuum case is grounded to USS via 00AWG wires (QTY 2). VC Bonding Strap 1VC Bonding Strap 2

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG24 MLI Blanket Class S bond wire grounded. AMS02 Electronics Summary Payload Grounding

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG25 Non-grounded interior MLI blankets will require EMEP TIA: TRDGB (XE & CO2 tanks, Valve block bootie TTCS tubing lines Cryocooler evaporators AMS02 Electronics Summary Ungrounded MLI Blankets

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG26 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 Summary IVA Habitable Volume Equipment

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG27 AMS02 Electronics Summary IVA Habitable Volume Equipment NOTE: Placards may not represent flight configuration. Configure Payload Data Interface Panel#1 (PDIP1)

Alpha Magnetic Spectrometer January 12, 2010Tim Urban / ESCG28 AMS02 Electronics Summary IVA Habitable Volume Equipment PGSC based “AMS Laptop” USB/422 Adaptor Box with Integrated PDIP Cable