Alpha Magnetic Spectrometer – 02 Avionics Outline

1. Alpha Magnetic Spectrometer – 02Phase II Flight Safety Review Avionics OverviewMay 21, 2007Timothy J. Urban / ESCG / Barrios Technology

2. Alpha Magnetic Spectrometer – 02Avionics Outline Timothy. J. Urban / ESCG

3. Alpha Magnetic Spectrometer – 02Avionics Overview Overview caveats: • The primary purpose of the payload is its science objectives. • The payload is designed to be fault-isolated from vehicle systems, and to be safe without services. • The only safety related payload operation is magnet charging, which is either operationally controlled or prohibited. • As such, the payload data systems architecture overview is provided as reference information only. Timothy. J. Urban / ESCG

4. Alpha Magnetic Spectrometer – 02Avionics Overview • J-Crate: Data Acquisition Interface Front-end • Interface: • JLIF: Low Rate Interface • JHIF: High Rate Interface) • JMDC: Redundant 4X Main Data Computer • PDS: Power Distribution System (front-end) • CAB: Cryomagnet Avionics Box • Cryomagnet Current Source (CCS) • Cryomagnet Self Protection (CSP) • Uninterruptible Power Source (UPS) • Cryomagnet Dump Diodes (CDD) Timothy. J. Urban / ESCG

5. Alpha Magnetic Spectrometer – 02Avionics Overview (continued) • Experiment Detector Electronics • xCrate: Detector Electronics • xPD: Detector Power • xHV: Detector High Voltage Source • Other Electronics: • Thermal • Monitor • Star Tracker • Global Positioning System • Laser Alignment Timothy. J. Urban / ESCG

6. Alpha Magnetic Spectrometer – 02Avionics Overview (continued) Systems Architecture • AMS-02 contains electronics boxes that supply the necessary services for each detector: • Readout • Monitor • Control electronics • Power distribution • The box nomenclature is generically xCrate, xPD or xHV • where “x” is a letter designating the detector function • “Crate” refers to the readout/monitor/control electronics box • “PD” refers to the Power Distribution box for that specific detector • xHV bricks provide high voltage for some detectors Timothy. J. Urban / ESCG

7. Alpha Magnetic Spectrometer – 02Avionics Overview (continued) Systems Architecture (continued) Values of “x” are designated as follows: • E ECAL • J Main Data Computers (MDC) and C&DH interfaces • JT Trigger and central data acquisition • M Monitoring • R RICH • S Time of Flight (TOF) Counters & Anti-Coincidence Counters (ACC) • T Tracker • TT Tracker Thermal • U Transition Radiation Detector (TRD) • UG TRD Gas Timothy. J. Urban / ESCG

8. Alpha Magnetic Spectrometer – 02Typical Crate Installation Timothy. J. Urban / ESCG

9. Alpha Magnetic Spectrometer – 02Avionics Layout Timothy. J. Urban / ESCG

10. Alpha Magnetic Spectrometer – 02Avionics Layout (continued) Timothy. J. Urban / ESCG

11. Alpha Magnetic Spectrometer – 02Avionics Overview Timothy. J. Urban / ESCG

12. Alpha Magnetic Spectrometer – 02Avionics Overview COMMAND AND DATA HANDLING SYSTEM Timothy. J. Urban / ESCG

13. Alpha Magnetic Spectrometer – 02Command and Data Handling System • J-Crate is the primary Command and Data Handling avionics for the payload • Four redundant Main Data Computers • Processes received commands and provides control to all subsystems • Transmission point for outbound science data • Command and Data Handling Interfaces: • STS, via ROEU PDA • 1553: Low speed commands and telemetry • RS-422: High-speed data • ISS, via UMA • 1553: Commands and telemetry (LRDL) • ISS Fiber-optic Payload Bus: High-speed data (HRDL) • J-Crate communicates within AMS-02 • AMS-02 Wire: (High performance serial 100Mbps custom wire, similar to ESA Space Wire) for High Rate communications • Controller Area Network (CAN) Bus: Protocol for Low Rate communications Timothy. J. Urban / ESCG

14. Alpha Magnetic Spectrometer – 02Command and Data Handling System Block Diagram AMSWire AMSWire Timothy. J. Urban / ESCG

15. J-Crate Scheme & test setup 4* Main Computer + Interfaces Timothy. J. Urban / ESCG

16. Alpha Magnetic Spectrometer – 02J-Crate Flight Model Timothy. J. Urban / ESCG

17. Alpha Magnetic Spectrometer – 02J-Crate 1553 Data Interfaces Timothy. J. Urban / ESCG

18. Alpha Magnetic Spectrometer – 021553 Interface Architecture • Separate 1553 Interfaces for STS and ISS • STS interface includes two Remote Terminals (RTs), sub-addresses RT28 and RT4 • ISS interface is somewhat unconventional • From ISS, AMS-02 is electrically only one RT • The AMS-02 ISS 1553 interface logically reacts as four 1553 Protocol Engines, for redundancy • At start-up, all four are in Bus-Monitor mode • First command to bring up system is not acknowledged (solely used to select which of the four Protocol Engine goes to RT) Timothy. J. Urban / ESCG

19. Alpha Magnetic Spectrometer – 02Payload High Rate Data Link on ISS ~ 100Mbit/s Max. 2 Mbit/s Long-term Aggregate POCC Payload Operations Control Center NASA: APS Automated Payload Switch (1 of 2, each with 20 programmable interconnects, but only 4 outputs to HCOR) HCOR High-rate Communications Outage Recorder HRFM High Rate Frame Multiplexer HRM High Rate Modem Timothy. J. Urban / ESCG

20. Alpha Magnetic Spectrometer – 02Data System Components 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-02 Wire to 1553, RS422, and Fiber • TRD Gas control and TTCS control. • 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 software (data gathering and blocking into types) • CDP – Common Digital Part – Gate Array, DSP, Memory, s/w code to communicate on AMS-02 Wire – performs digitizing, blocking and compression • CDDC – Command Distributor/Data Concentrator – Reads CDP queue/combines pieces of single events, distributes commands to CDPs • AMS-02 Wire – Hi-performance serial 100 Mbps custom wire (similar to ESA Space Wire) • Controller Area Network (CAN) Bus - Protocol for Low Rate communications Timothy. J. Urban / ESCG

21. Alpha Magnetic Spectrometer – 02Command and Data Handling System Payload Tiered C&DH System Timothy. J. Urban / ESCG

22. Alpha Magnetic Spectrometer – 02Housekeeping Data Overview(equivalent to NASA H&S Data) Timothy. J. Urban / ESCG

23. Alpha Magnetic Spectrometer – 02Science Data Architecture thresholds, etc., by Timothy. J. Urban / ESCG

24. Alpha Magnetic Spectrometer – 02Data System resources Timothy. J. Urban / ESCG

25. Alpha Magnetic Spectrometer – 02Power Distribution System Overview The PDS is the primary power interface for the payload: • STS, via ROEU PDA • ISS SSRMS, via PVGF • ISS CAS, via UMA • Performs power isolation per SSP-57003 • Power exposure at the above interfaces, when the PDS is powered by another interface, is precluded as follows: • ROEU PDA diode protected • PVGF diode protected • UMA has a covered connector • Performs universal power conversion and distribution for the payload Timothy. J. Urban / ESCG

26. Alpha Magnetic Spectrometer – 02Avionics Overview - Power Systems Timothy. J. Urban / ESCG

27. Alpha Magnetic Spectrometer – 02Avionics Overview - Power Systems Timothy. J. Urban / ESCG

28. Alpha Magnetic Spectrometer – 02AMS-02 Resource Requirements • Power • Average 2.4 kW • Peak 2.8 kW • Data • Science Data: 2 Mbps (long-term aggregate) • Housekeeping Data: 10 Kbps • Critical Health Data: 10 bps S-Band, under negotiation with ISS Timothy. J. Urban / ESCG

29. Alpha Magnetic Spectrometer – 02Avionics Overview Mission Phased Avionics SystemsInterfaces and Functions Timothy. J. Urban / ESCG

30. Alpha Magnetic Spectrometer – 02Avionics Overview Mission Phased Avionics Interfaces • STS, via ROEU PDA • Pre-Launch • Ascent • On-Orbit • ISS SSRMS, via PVGF • ISS CAS, via UMA Timothy. J. Urban / ESCG

31. Alpha Magnetic Spectrometer – 02Payload Avionics Universal Interface Diagram Timothy. J. Urban / ESCG

32. Alpha Magnetic Spectrometer – 02Avionics Overview STS Pre-Launch Interfaces Via T0 through ROEU PDA • Power: • Payload: 120 VDC from MLP KSC GSE Power Supply • SFHe Vent Pump: 110 VAC from MLP Room 10 A Payload GSE Power Supply • Data: • 1553: Low-speed commands and telemetry • RS-422: High-speed data • MLP Room 10A Payload GSE computers (QTY 2) • Computers remotely monitored and operated via dedicated Ethernet Timothy. J. Urban / ESCG

33. Alpha Magnetic Spectrometer – 02Avionics Systems Interface Diagram – STS Pre-Launch Timothy. J. Urban / ESCG

34. Alpha Magnetic Spectrometer – 02ROEU PDA and Interface Panel A Remotely Operated Electrical Umbilical Payload Disconnect Assembly Interface Panel A Timothy. J. Urban / ESCG

35. Alpha Magnetic Spectrometer – 02Avionics Overview – Pre-Launch • Activate/checkout AMS-02 avionics subsystems and maintenance of cryo-systems • Approximately 500 W @ 120 VDC for J-Crate, cryo-valves, and CAB critical functions • Approximately 500 ~ 1000 W @ 110 VAC for SFHe tank vent pump • Maximum 2 kW (peak) for calibration and contingency • Negotiating PLB thermal loads with STS • Magnet charging on Pad Operationally Controlled • Magnet charge initiation requires a series of transmitted commands, none of which are stored on-board the AMS-02 computer Timothy. J. Urban / ESCG

36. Alpha Magnetic Spectrometer – 02Avionics Overview – Pre-Launch SFHe Tank Vent Pump • Pre-Launch only • T0 110 VAC interface and ground safety being worked with STS Program and KSC, including EMI Timothy. J. Urban / ESCG

37. Alpha Magnetic Spectrometer – 02Avionics Overview – Pre-Launch Payload Data Interface Panel 2 Configuration • 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. Timothy. J. Urban / ESCG

38. Alpha Magnetic Spectrometer – 02Avionics Systems Interface Diagram – STS Ascent Timothy. J. Urban / ESCG

39. Alpha Magnetic Spectrometer – 02Avionics Overview – 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 (< 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 low 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. Timothy. J. Urban / ESCG

40. Alpha Magnetic Spectrometer – 02Avionics Overview – STS Ascent SFHe Tank Nominal Vent Valve Operation (continued) • Baroswitch Electronics (BSE) will open the vent valve: • 28VDC power from SSP2, Circuit Breaker @ 5A • BSE to implement de-rated over-current protection circuit < 5A • BSE will open the vent valve when triggered: • 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 @ L+TBD minutes. • In the event of an STS abort, barometric switch will trigger BSE to close the vent valve during descent. • BSE will be compliant with NSTS/ISS 18978B, NS2/81-M082 • Baroswitch is hermetically sealed • Valve motor is brushless • Thermal analysis to ensure BSE is below auto-ignition temperature Timothy. J. Urban / ESCG

41. Alpha Magnetic Spectrometer – 02Avionics Systems Interface Diagram – STS On-Orbit Timothy. J. Urban / ESCG

42. Alpha Magnetic Spectrometer – 02Avionics Overview – STS On-Orbit • Configure PDIP1 and PDIP2 • Unstow and activate Digital Data Recorder System-02 • Activate Assembly Power Converter Units • Powers AMS-02 Payload • Payload Check-out • Payload Deploy Timothy. J. Urban / ESCG

43. Alpha Magnetic Spectrometer – 02Avionics Overview – STS On-Orbit Configure PDIP1 Timothy. J. Urban / ESCG

44. Alpha Magnetic Spectrometer – 02Avionics Overview – STS On-Orbit Configure PDIP2 Timothy. J. Urban / ESCG

45. Alpha Magnetic Spectrometer – 02Avionics Overview – STS On-Orbit 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) Timothy. J. Urban / ESCG

46. Alpha Magnetic Spectrometer – 02Avionics Overview – STS On-Orbit Payload Power-up and Check-out • Cryocoolers and housekeeping data at ~ MET 2 hr 30 minutes • Activate/checkout AMS-02 avionics subsystems and thermally condition payload • Peak power draw from Orbiter APCU, quantity 2 wired in parallel, is 2.8kW • Avionics thermal constraints may be imposed • No magnet charging is possible on STS – APCU power is supplied to prime PDS side “B”, which has no connectivity to the CAB, and thus the magnet • Power down AMS-02 prior to transfer operations • Disconnect ROEU ODA from PDA prior to deploy AMS-02 Timothy. J. Urban / ESCG

47. Alpha Magnetic Spectrometer – 02Avionics Overview – STS On-Orbit Simplified Payload Power-Up Sequence Timothy. J. Urban / ESCG

48. Alpha Magnetic Spectrometer – 02Avionics Systems Interface Diagram – Hand-Off Timothy. J. Urban / ESCG

49. Alpha Magnetic Spectrometer – 02PVGF Location Timothy. J. Urban / ESCG

50. Alpha Magnetic Spectrometer – 02SSRMS Power Block Diagram Timothy. J. Urban / ESCG