Alpha Magnetic Spectrometer 02 Phase II Flight

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

Alpha Magnetic Spectrometer – 02 Avionics Outline Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 2

Alpha Magnetic Spectrometer – 02 Avionics Overview Alpha Magnetic Spectrometer Overview caveats: 1. The primary purpose of the payload is its science objectives. 2. The payload is designed to be fault-isolated from vehicle systems, and to be safe without services. 3. The only safety related payload operation is magnet charging, which is either operationally controlled or prohibited. 4. As such, the payload data systems architecture overview is provided as reference information only. May 21, 2007 Timothy. J. Urban / ESCG 3

Alpha Magnetic Spectrometer – 02 Avionics Overview Alpha Magnetic Spectrometer • J-Crate: Data Acquisition Interface Front-end – Interface: • • JLIF: Low Rate Interface JHIF: High Rate Interface) – JMDC: Redundant 4 X 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) May 21, 2007 Timothy. J. Urban / ESCG 4

Alpha Magnetic Spectrometer – 02 Avionics Overview (continued) Alpha Magnetic Spectrometer • Experiment Detector Electronics – x. Crate: Detector Electronics – x. PD: Detector Power – x. HV: Detector High Voltage Source • Other Electronics: – Thermal – Monitor • • • May 21, 2007 Star Tracker Global Positioning System Laser Alignment Timothy. J. Urban / ESCG 5

Alpha Magnetic Spectrometer – 02 Avionics Overview (continued) Alpha Magnetic Spectrometer 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 x. Crate, x. PD or x. HV – 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 – x. HV bricks provide high voltage for some detectors May 21, 2007 Timothy. J. Urban / ESCG 6

Alpha Magnetic Spectrometer – 02 Avionics Overview (continued) Alpha Magnetic Spectrometer Systems Architecture (continued) Values of “x” are designated as follows: • E • J • • May 21, 2007 ECAL 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 Thermal U Transition Radiation Detector (TRD) UG TRD Gas Timothy. J. Urban / ESCG 7

Alpha Magnetic Spectrometer – 02 Typical Crate Installation Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 8

Alpha Magnetic Spectrometer – 02 Avionics Layout Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 9

Alpha Magnetic Spectrometer – 02 Avionics Layout (continued) Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 10

Alpha Magnetic Spectrometer – 02 Avionics Overview Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 11

Alpha Magnetic Spectrometer – 02 Avionics Overview Alpha Magnetic Spectrometer COMMAND DATA HANDLING SYSTEM May 21, 2007 Timothy. J. Urban / ESCG 12

Alpha Magnetic Spectrometer – 02 Command Data Handling System Alpha Magnetic Spectrometer • J-Crate is the primary Command 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 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 100 Mbps custom wire, similar to ESA Space Wire) for High Rate communications – Controller Area Network (CAN) Bus: Protocol for Low Rate communications May 21, 2007 Timothy. J. Urban / ESCG 13

Alpha Magnetic Spectrometer – 02 Command Data Handling System Alpha Magnetic Spectrometer Block Diagram AMSWire May 21, 2007 Timothy. J. Urban / ESCG 14

J-Crate Scheme & test setup 4* Main Computer + Interfaces Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 15

Alpha Magnetic Spectrometer – 02 J-Crate Flight Model Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 16

Alpha Magnetic Spectrometer – 02 J-Crate 1553 Data Interfaces Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 17

Alpha Magnetic Spectrometer – 02 1553 Interface Architecture Alpha Magnetic Spectrometer • Separate 1553 Interfaces for STS and ISS • STS interface includes two Remote Terminals (RTs), sub -addresses RT 28 and RT 4 • ISS interface is somewhat unconventional – From ISS, AMS-02 is electrically one RT – The AMS-02 ISS 1553 interface logically reacts as four 1553 Protocol Engines, for redundancy • • May 21, 2007 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 18

Alpha Magnetic Spectrometer – 02 Payload High Rate Data Link on ISS Alpha Magnetic Spectrometer POCC Payload Operations Control Center ~ 100 Mbit/s Max. 2 Mbit/s Long-term Aggregate 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 May 21, 2007 Timothy. J. Urban / ESCG 19

Alpha Magnetic Spectrometer – 02 Data System Components Alpha Magnetic Spectrometer 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, RS 422, 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 RS 422 • 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 May 21, 2007 Timothy. J. Urban / ESCG 20

Alpha Magnetic Spectrometer – 02 Command Data Handling System Alpha Magnetic Spectrometer Payload Tiered C&DH System May 21, 2007 Timothy. J. Urban / ESCG 21

Alpha Magnetic Spectrometer – 02 Housekeeping Data Overview Alpha Magnetic Spectrometer May 21, 2007 (equivalent to NASA H&S Data) Timothy. J. Urban / ESCG 22

Alpha Magnetic Spectrometer – 02 Science Data Architecture Alpha Magnetic Spectrometer thresholds, etc. , by May 21, 2007 Timothy. J. Urban / ESCG 23

Alpha Magnetic Spectrometer – 02 Data System resources Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 24

Alpha Magnetic Spectrometer – 02 Power Distribution System Alpha Magnetic Spectrometer 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 May 21, 2007 Timothy. J. Urban / ESCG 25

Alpha Magnetic Spectrometer – 02 Avionics Overview - Power Systems Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 26

Alpha Magnetic Spectrometer – 02 Avionics Overview - Power Systems Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 27

Alpha Magnetic Spectrometer – 02 AMS-02 Resource Requirements Alpha Magnetic Spectrometer • Power – Average 2. 4 k. W – Peak 2. 8 k. W • Data – Science Data: 2 Mbps (long-term aggregate) – Housekeeping Data: 10 Kbps – Critical Health Data: 10 bps S-Band, under negotiation with ISS May 21, 2007 Timothy. J. Urban / ESCG 28

Alpha Magnetic Spectrometer – 02 Avionics Overview Alpha Magnetic Spectrometer Mission Phased Avionics Systems Interfaces and Functions May 21, 2007 Timothy. J. Urban / ESCG 29

Alpha Magnetic Spectrometer – 02 Avionics Overview Alpha Magnetic Spectrometer Mission Phased Avionics Interfaces • STS, via ROEU PDA – Pre-Launch – Ascent – On-Orbit • ISS SSRMS, via PVGF • ISS CAS, via UMA May 21, 2007 Timothy. J. Urban / ESCG 30

Alpha Magnetic Spectrometer – 02 Payload Avionics Universal Interface Diagram Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 31

Alpha Magnetic Spectrometer – 02 Avionics Overview Alpha Magnetic Spectrometer STS Pre-Launch Interfaces Via T 0 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 10 A Payload GSE computers (QTY 2) Computers remotely monitored and operated via dedicated Ethernet May 21, 2007 Timothy. J. Urban / ESCG 32

Alpha Magnetic Spectrometer – 02 Avionics Systems Interface Diagram – STS Pre-Launch Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 33

Alpha Magnetic Spectrometer – 02 ROEU PDA and Interface Panel A Alpha Magnetic Spectrometer Interface Panel A May 21, 2007 Remotely Operated Electrical Umbilical Payload Disconnect Assembly Timothy. J. Urban / ESCG 34

Alpha Magnetic Spectrometer – 02 Avionics Overview – Pre-Launch Alpha Magnetic Spectrometer • 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 k. W (peak) for calibration and contingency Negotiating PLB thermal loads with STS ð 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 May 21, 2007 Timothy. J. Urban / ESCG 35

Alpha Magnetic Spectrometer – 02 Avionics Overview – Pre-Launch Alpha Magnetic Spectrometer SFHe Tank Vent Pump • Pre-Launch only • T 0 110 VAC interface and ground safety being worked with STS Program and KSC, including EMI May 21, 2007 Timothy. J. Urban / ESCG 36

Alpha Magnetic Spectrometer – 02 Avionics Overview – Pre-Launch Alpha Magnetic Spectrometer Payload Data Interface Panel 2 Configuration • • Low rate data (1553) is routed through T 0 umbilical to MLP GSE computers from Shuttle PDIP 2 with the “AMS-02 1553” switch in the “T 0” position, and program provided jumper installed on PDIP 2 front panel “J 4” connector High rate data (RS 422) is routed through T 0 umbilical to MLP GSE computers from Shuttle PDIP 2 via payload provided cable installed between PDIP 2 front panel “J 103” and “J 105” connectors. May 21, 2007 Timothy. J. Urban / ESCG 37

Alpha Magnetic Spectrometer – 02 Avionics Systems Interface Diagram – STS Ascent Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 38

Alpha Magnetic Spectrometer – 02 Avionics Overview – Ascent Alpha Magnetic Spectrometer SFHe Tank Nominal Vent Valve Operation • He Vapor pressure in SFHe tank must be maintained at a pressure to keep LHe temperature superfluid ð 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 ð ð 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. May 21, 2007 Timothy. J. Urban / ESCG 39

Alpha Magnetic Spectrometer – 02 Avionics Overview – STS Ascent Alpha Magnetic Spectrometer SFHe Tank Nominal Vent Valve Operation (continued) • Baroswitch Electronics (BSE) will open the vent valve: – 28 VDC power from SSP 2, Circuit Breaker @ 5 A – BSE to implement de-rated over-current protection circuit < 5 A • 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 18978 B, NS 2/81 -M 082 • • • May 21, 2007 Baroswitch is hermetically sealed Valve motor is brushless Thermal analysis to ensure BSE is below auto-ignition temperature Timothy. J. Urban / ESCG 40

Alpha Magnetic Spectrometer – 02 Avionics Systems Interface Diagram – STS On-Orbit Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 41

Alpha Magnetic Spectrometer – 02 Avionics Overview – STS On-Orbit Alpha Magnetic Spectrometer • Configure PDIP 1 and PDIP 2 • Unstow and activate Digital Data Recorder System-02 • Activate Assembly Power Converter Units – Powers AMS-02 Payload • Payload Check-out • Payload Deploy May 21, 2007 Timothy. J. Urban / ESCG 42

Alpha Magnetic Spectrometer – 02 Avionics Overview – STS On-Orbit Alpha Magnetic Spectrometer Configure PDIP 1 May 21, 2007 Timothy. J. Urban / ESCG 43

Alpha Magnetic Spectrometer – 02 Avionics Overview – STS On-Orbit Alpha Magnetic Spectrometer Configure PDIP 2 May 21, 2007 Timothy. J. Urban / ESCG 44

Alpha Magnetic Spectrometer – 02 Avionics Overview – STS On-Orbit Alpha Magnetic Spectrometer 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) May 21, 2007 Timothy. J. Urban / ESCG 45

Alpha Magnetic Spectrometer – 02 Avionics Overview – STS On-Orbit Alpha Magnetic Spectrometer 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. 8 k. W – Avionics thermal constraints may be imposed ð 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 May 21, 2007 Timothy. J. Urban / ESCG 46

Alpha Magnetic Spectrometer – 02 Avionics Overview – STS On-Orbit Alpha Magnetic Spectrometer Simplified Payload Power-Up Sequence May 21, 2007 Timothy. J. Urban / ESCG 47

Alpha Magnetic Spectrometer – 02 Avionics Systems Interface Diagram – Hand-Off Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 48

Alpha Magnetic Spectrometer – 02 PVGF Location Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 49

Alpha Magnetic Spectrometer – 02 SSRMS Power Block Diagram Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 50

Alpha Magnetic Spectrometer – 02 Avionics Overview – Hand-Off Alpha Magnetic Spectrometer 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 - Video routed through SSRMS – SSRMS supplies power for AMS-02 Heaters via PVGF during transfer operationss ð Magnet charging on SSRMS is 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 May 21, 2007 Timothy. J. Urban / ESCG 51

Alpha Magnetic Spectrometer – 02 Avionics Overview – Hand-Off Alpha Magnetic Spectrometer Payload Hand-Off (continued) • SSRMS routes Type II RPCM (25 A) power for AMS-02 Heaters during Transfer Ops, maximum 16. 7 Amps – Limited by SSRMS payload bus wire thermal load – Currently implementing current protection circuit, not for the payload, but to protect the SSRMS payload power bus wires ðDe-rating of this protection not required per JSC EEE parts – Proposing elimination of this circuit, based upon cumulative current limit of the piecemeal protection devices implemented for these heater circuits within the PDS þPSRP Technical Expert Concurrence ¨Pending review and approval from ISS EVR and PICB panels May 21, 2007 Timothy. J. Urban / ESCG 52

Alpha Magnetic Spectrometer – 02 Avionics Overview – Hand-Off Alpha Magnetic Spectrometer Payload Hand-Off (continued) • SRMS release of AMS-02 • Transfer to S 3 attach site • Attach AMS-02 to S 3 upper inboard site – Mechanical attachment via PAS – Electrical attachment via UMA • • Deactivate power via PVGF Ungrapple SSRMS Attach UMA and activate power Power up Avionics, perform abbreviated avionics checkout to verify payload power and communications May 21, 2007 Timothy. J. Urban / ESCG 53

Alpha Magnetic Spectrometer – 02 Avionics Overview – Hand-Off Alpha Magnetic Spectrometer Transfer to ISS 1 3 May 21, 2007 2 4 Timothy. J. Urban / ESCG 54

Alpha Magnetic Spectrometer – 02 Avionics Overview – Hand-Off Alpha Magnetic Spectrometer Berthing to ISS – S 3 Upper / Inboard May 21, 2007 Timothy. J. Urban / ESCG 55

Alpha Magnetic Spectrometer – 02 Avionics Systems Interface Diagram – ISS Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 56

Alpha Magnetic Spectrometer – 02 Avionics Overview – ISS Alpha Magnetic Spectrometer • • • 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 May 21, 2007 Timothy. J. Urban / ESCG 57

Alpha Magnetic Spectrometer – 02 Avionics Overview – ISS Alpha Magnetic Spectrometer On-Orbit ISS Operations (continued) ð Experiment Science: – 3+ years operation with magnet – After SFHe 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 May 21, 2007 Timothy. J. Urban / ESCG 58

Alpha Magnetic Spectrometer – 02 Avionics Overview – ISS Alpha Magnetic Spectrometer On-Orbit ISS Operations (continued) • Control of AMS-02 is from ground ð Only safety related operation is Cryomagnet charge – Only safety concern 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 May 21, 2007 Timothy. J. Urban / ESCG 59

Alpha Magnetic Spectrometer – 02 Avionics Overview – ISS Alpha Magnetic Spectrometer Simplified Payload Power-Up Sequence May 21, 2007 Timothy. J. Urban / ESCG 60

Alpha Magnetic Spectrometer – 02 Avionics Overview – ISS Alpha Magnetic Spectrometer EVA Connector Panel • EVA Connector Panel allows for redundant avionics interfaces in contingency scenario – Connectors will meet the mating/demating requirements identified in letter MA 2 -99 -170, and comply with (SSQ 21654) • Connections are swapped to effect changing AMS-02 A(prime) / B(redundant) channels in the event that prime capability is lost: – Data: Payload Redundancy Only – Power: Payload and ISS Redundancy • Contingency release of failed UMA ð Cryomagnet charge can be performed on UMA powered PDS A-side (prime) bus only. May 21, 2007 Timothy. J. Urban / ESCG 61

Alpha Magnetic Spectrometer – 02 EVA Connector Panel Interfaces Alpha Magnetic Spectrometer A B Connector May 21, 2007 Timothy. J. Urban / ESCG 62

Alpha Magnetic Spectrometer – 02 EVA Connector Panel Location Alpha Magnetic Spectrometer EVA Connector Panel UMA May 21, 2007 Timothy. J. Urban / ESCG 63

Alpha Magnetic Spectrometer – 02 Avionics Overview – ISS Alpha Magnetic Spectrometer EVA Interface Panel and UMA Operations May 21, 2007 Timothy. J. Urban / ESCG 64

Alpha Magnetic Spectrometer – 02 Avionics Overview Alpha Magnetic Spectrometer Power Systems Detailed May 21, 2007 Timothy. J. Urban / ESCG 65

Alpha Magnetic Spectrometer – 02 Power Systems Detailed Alpha Magnetic Spectrometer • • • OUTLINE Power Distribution System Payload Bonding Payload Heaters Other Power Subsystems Cryomagnet Avionics Box – Cryomagnet Dump Diodes – Uninterruptible Power Supply May 21, 2007 Timothy. J. Urban / ESCG 66

Alpha Magnetic Spectrometer – 02 Power Systems Detailed Alpha Magnetic Spectrometer Power Distribution System – Front End Provides 1 MΩ isolation requirement for payload • Wire sizing is designed to meet: – NSTS 1700. 7 B, "Safety Policy and Requirements For Payloads Using the Space Transportation System“ – NSTS 1700. 7 B ISS Addendum, "Safety Policy and Requirements For Payloads Using the International Space Station“ – NASA Technical Memorandum #TM 102179, "Selection of Wires and Circuit Protection Devices for NSTS Orbiter Vehicle Payload Electrical Circuits" May 21, 2007 Timothy. J. Urban / ESCG 67

Alpha Magnetic Spectrometer – 02 Power Systems Detailed Alpha Magnetic Spectrometer PDS – Front End (continued) • PDS consists of four sections: – – 120 VDC Input 120 VDC Output 28 VDC (Internally Isolated) Output Control and Monitor (Isolated Low Voltage) • All 120 VDC outputs isolation provided by the end subsystem – DC-to-DC or AC converters – Relays • Isolation for all other outputs is provided internally to the PDS by DC-to-DC converters • PDS performs EMI filtration • PDS provides essential telemetry to the J-Crate May 21, 2007 Timothy. J. Urban / ESCG 68

Alpha Magnetic Spectrometer – 02 Power Systems Detailed Alpha Magnetic Spectrometer PDS – Front End (continued) • The PDS has two independent “channels” side A and side B which have four identical subsections, as described on the previous page • The only difference between the two channels is that side A is the only side that has power connectivity to the CAB to perform magnet charging May 21, 2007 Timothy. J. Urban / ESCG 69

Alpha Magnetic Spectrometer – 02 Power Distribution System Location Alpha Magnetic Spectrometer PDS May 21, 2007 Timothy. J. Urban / ESCG 70

Alpha Magnetic Spectrometer – 02 Avionics Overview - Power Systems Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 71

Alpha Magnetic Spectrometer – 02 Avionics Overview - Power Systems Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 72

Alpha Magnetic Spectrometer – 02 Power Distribution System Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 73

Alpha Magnetic Spectrometer – 02 Power Distribution System Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 74

Alpha Magnetic Spectrometer – 02 Power Distribution System Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 75

Alpha Magnetic Spectrometer – 02 Power Systems Detailed Alpha Magnetic Spectrometer Engineering Model (one-half populated) May 21, 2007 Timothy. J. Urban / ESCG 76

Alpha Magnetic Spectrometer – 02 Power Distribution System Bonding Alpha Magnetic Spectrometer The PDS bonding is designed per SSP-30240 Space Station Grounding Requirements, Rev. C: • Minimum isolation of 1 MΩ between: – Primary power positive line and chassis – Primary power return line and chassis – Primary power lines and all the secondary PDS power lines (positive and return lines) May 21, 2007 Timothy. J. Urban / ESCG 77

Alpha Magnetic Spectrometer – 02 PDS Bonding (continued) Alpha Magnetic Spectrometer • The PDS box is equipped with a bonding stud • The PDS Bonding Stud shall be connected to the AMS-02 structure by means of a bond strap • A copper bus bar is located inside the PDS in order to collect the single point bonding from the Power Boards – The copper bus bar is isolated from the PDS wall – The copper bus bar shall be connected internally to the PDS bonding stud by means of ring terminals • The bonding stud will be connected to the AMS-02 support structure in such a manner: – To conduct electrical faults current without creating thermal or electrical hazard – To minimize differences in potential between all equipment • The mechanical box will operate as a shield against the internally generated emissions and the externally generated emissions. May 21, 2007 Timothy. J. Urban / ESCG 78

Alpha Magnetic Spectrometer – 02 Power Distribution System Bonding Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 79

Alpha Magnetic Spectrometer – 02 Payload Bonding Alpha Magnetic Spectrometer • Fault bond path is achieved through UMA to ISS power systems via 8 awg “green wire” (one per bus) – common with AMS-02 structure • Payload avionics boxes are bonded to radiators, or USS structure where applicable, with redundant bond straps • Vacuum Case and Radiators are bonded to USS structure with redundant straps • USS structure joints: – Some are alodine bonded through riveted joints (not fasteners) – Those joints that do not meet Class R bond will use bond straps • Bond strap points throughout the payload will be alodined • All thermal blankets are bonded per SSP 30245 and NASA/TP-1999 -209263 May 21, 2007 Timothy. J. Urban / ESCG 80

Alpha Magnetic Spectrometer – 02 Payload Bonding Alpha Magnetic Spectrometer • Payload level Class R bond supplied through Nickel Plating on V-guides on active CAS • All GFE is bonded to structure per installation drawings: – – – ROEU PDA UMA FRGF PVGF EBCS • All bonds will be verified at integration: – Electronics and USS structural: Class R – Non-USS structural: Class H – Blankets & Plumbing: Class S May 21, 2007 Timothy. J. Urban / ESCG 81

Alpha Magnetic Spectrometer – 02 Payload Heaters Alpha Magnetic Spectrometer • Temperature sensors will monitor all critical temperatures and allow for additional computer control of heaters • Most non-safety critical heaters are controlled by the PDS and also have at least 2 thermostats in series • PDS internal heaters have 3 thermostats in series • Heaters are sized for minimum Voltage – PDS internally converted 28 VDC – ISS provide 120 VDC • Heaters and thermostats strings are redundant and can be operated by either A or B power feed • All safety critical heater applications use a 2 fault tolerant control, utilizing 3 thermostatically controlling devices with at least 1 of these devices in the power return leg. May 21, 2007 Timothy. J. Urban / ESCG 82

Alpha Magnetic Spectrometer – 02 Payload Heaters Alpha Magnetic Spectrometer • This is typical for safety critical heaters. • However, no heaters are required for safety. May 21, 2007 Timothy. J. Urban / ESCG 83

Alpha Magnetic Spectrometer – 02 Cryomagnet Avionics Box (CAB) Alpha Magnetic Spectrometer • The CAB consists of the following subsystems: – Cryomagnet Current Source (CCS) – Cryo Controller and Signal Conditioner (CCSC) – Cryomagnet Self Protection (CSP) • The Cryomagnet Charge/Discharge Circuit consists of: – – – CCS Power Switch Shunt Cryomagnet Dump Diodes (External to CAB) Magnet Coils May 21, 2007 Timothy. J. Urban / ESCG 84

Alpha Magnetic Spectrometer – 02 Cryomagnet Avionics Box Block Diagram Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 85

Alpha Magnetic Spectrometer – 02 Cryomagnet Avionics Box Location Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 86

Alpha Magnetic Spectrometer – 02 Cryomagnet Avionics Box Layout Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 87

Alpha Magnetic Spectrometer – 02 Cryomagnet Current Source (CCS) Alpha Magnetic Spectrometer • CCS design includes three protection barriers in series to prevent an actual current at the magnet higher than 459 A: – Software protection (value between 455. 33 A and 459) – Field Programmable Gate Array (FPGA) protection (limit is 459 A) – Hard-wired control electronics protection circuitry (limit 459 A) • Isolation for the 120 Vdc line (feed thru from PDS) is performed via DC to DC Converters in the CCS – 120 Vdc input is limited to max. 2200 W for power management • All input/outputs (power and data) from CAB back toward ISS are protected with High Voltage (8 k. V) protection to prevent feedback from unprotected quench (analysis shows maximum voltage is 5. 5 k. V). May 21, 2007 Timothy. J. Urban / ESCG 88

Alpha Magnetic Spectrometer – 02 Cryomagnet Current Source (CCS) Alpha Magnetic Spectrometer • The CCS performs magnet charging electrical function • To charge the magnet, the Semiconductor switch on the charging circuit is closed, and power is supplied to the transformer input. • The current is slowly ramped up over a period of approximately 1. 5 hours to 459 Amps. • Current during charge and discharge operations is monitored using a 500 A shunt. • The connection from the CCS to the magnet is made via three pairs of 00 AWG wires. • Once full operating current is reached, the Persistent Switch is closed – The switch consists of a pair of super-conducting wires – “closed” by cooling them down to superconducting temperatures. May 21, 2007 Timothy. J. Urban / ESCG 89

Alpha Magnetic Spectrometer – 02 Magnet Charging (continued) Alpha Magnetic Spectrometer • With the persistent switch closed, 459 A is running through both sides of the circuit (the magnet side and the charger side). – To avoid ripple currents through the persistent switch, the current on the charger side is slowly reduced to zero. • Once the current on the charger side is removed, the Semiconductor Switch is opened, and the charging system is disconnected from the magnet circuit. • Mechanical disconnects on the charging leads for the magnet are used to provide thermal isolation from the outside environment during all operations except charging and discharging. • Prior to charging or discharging, the mechanical disconnects must be connected and cooled, and then disconnected after the operation is complete. May 21, 2007 Timothy. J. Urban / ESCG 90

Alpha Magnetic Spectrometer – 02 Magnet Charging (continued) Alpha Magnetic Spectrometer Mechanical Disconnects and Persistent Switch • Mechanical Disconnects are bi-metallic switch operated from a pre-cooled pressure operated bellow connection • Persistent switch consists of two super-conducting resistors in parallel that reach 30 ohms when heated above superconducting temperatures (heated by low voltage heaters to “open”) May 21, 2007 Timothy. J. Urban / ESCG 91

Alpha Magnetic Spectrometer – 02 Cryomagnet Charge Cable Routing Alpha Magnetic Spectrometer VC Port for Cable Interface Charge Cables (00 AWG) CAB Connections May 21, 2007 Timothy. J. Urban / ESCG 92

Alpha Magnetic Spectrometer – 02 Cryomagnet Charge Cable VC Interface Alpha Magnetic Spectrometer Current Leads Soldered VC Upper Ring VC Port 00 AWG Cable Attach Points (X 3 each) Current Leads Soldered May 21, 2007 Timothy. J. Urban / ESCG 93

Alpha Magnetic Spectrometer – 02 Cryomagnet Dump Diodes (CDD) Alpha Magnetic Spectrometer • For magnet power down, the mechanical leads are connected and the persistent switch is opened to allow the current in the magnet to be dumped to a bank of 18 diodes: – Half on Port side – Half on Starboard side – Both Port and Starboard banks in series with each other • The diodes will be mounted on the two wake-side sill trunnion joints (large thermal mass) • The cryomagnet current will be dissipated conductively as thermal energy to the structure • These diodes will be protected by a cover to prevent incidental contact • Dump time is estimated at 80 minutes May 21, 2007 Timothy. J. Urban / ESCG 94

Alpha Magnetic Spectrometer – 02 Cryomagnet Dump Diodes (CDD) - Schematic Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 95

Alpha Magnetic Spectrometer – 02 Cryomagnet Dump Diodes (CDD) Alpha Magnetic Spectrometer Cryomagnet Dump Diodes (CDD) Subassembly May 21, 2007 Timothy. J. Urban / ESCG 96

Alpha Magnetic Spectrometer – 02 Cryomagnet Dump Diodes (CDD) Alpha Magnetic Spectrometer Cryomagnet Dump Diodes (CDD) Subassembly Diode Q-Pad II washer location Mounting block 3, rectifier assembly C (new design being machined) Torlon washer & mounting bolts Bottom Chotherm pad May 21, 2007 Timothy. J. Urban / ESCG 97

Alpha Magnetic Spectrometer – 02 Cryomagnet Dump Diodes (CDD) Alpha Magnetic Spectrometer CDD QM Assembly Sequence May 21, 2007 Timothy. J. Urban / ESCG 98

Alpha Magnetic Spectrometer – 02 Cryomagnet Dump Diodes (CDD) Alpha Magnetic Spectrometer CDD Typical Installation without Protective Cover CDD Assembly Discharge Cabling Sill Trunnion Block May 21, 2007 Timothy. J. Urban / ESCG 99

Alpha Magnetic Spectrometer – 02 Cryomagnet Dump Diodes (CDD) Alpha Magnetic Spectrometer CDD Typical Installation (QM) with Protective Cover Completed CDD Assembly Sill Trunnion Block May 21, 2007 Timothy. J. Urban / ESCG 100

Alpha Magnetic Spectrometer – 02 Cryomagnet Dump Diodes (CDD) Alpha Magnetic Spectrometer CDD Locations and Cable Routing CDD Port Assembly Discharge Cables Routed to CAB Bank-to-Bank Discharge Cables Routed under Beam CDD Starboard Assembly May 21, 2007 Timothy. J. Urban / ESCG 101

Alpha Magnetic Spectrometer – 02 Cryomagnet Dump Diodes (CDD) Alpha Magnetic Spectrometer CDD Thermal Vacuum Test Set-up May 21, 2007 Timothy. J. Urban / ESCG 102

Alpha Magnetic Spectrometer – 02 Cryomagnet Dump Diodes (CDD) Alpha Magnetic Spectrometer CDD Thermal Vacuum Test Set-up Thermal Vacuum Chamber Power Supplies May 21, 2007 Isolated T/C Converter T/C DAQ Modules Diode Bank on Sill Trunnion Block Timothy. J. Urban / ESCG 103

Alpha Magnetic Spectrometer – 02 Cryomagnet Control and Signal Conditioning Alpha Magnetic Spectrometer • The Cryomagnet Control and Signal Conditioning (CCSC) provides the interface between the AMS-02 Main Data Computers (MDCs) and the Cryomagnet. • The CCSC is responsible for: – – Reception of commands from the MDCs Transmission of telemetry to the MDCs Commanding of the CCS Control of the Cryomagnet auxiliary functions (i. e. heaters, valves, etc. ) – Monitoring of the CCS, Cryomagnet, and CAB operating parameters and status • The CCSC also performs system fault detection and management functions, formatting of telemetry, and data storage for system status. • The CCSC is required to interface with the Uninterruptible Power Source (UPS). Timothy. J. Urban / ESCG May 21, 2007 104

Alpha Magnetic Spectrometer – 02 Cryomagnet Self Protection (CSP) Alpha Magnetic Spectrometer • The CSP performs an assisted magnet quench in the event that an unassisted quench pre-cursory condition is detected. • The quench protection electronics issues a command to the Uninterruptible Power Source (UPS) to provide a pulse of 45 A to quench heaters located throughout the magnet. • The pulse, for a duration of 150 ms, is required to raise the entire magnet up to a non-superconducting state. – The magnet current is dissipated as heat energy within the magnet. • After 8 hours, when either power or communications has be lost, the CSP performs an ramp down to protect the magnet. May 21, 2007 Timothy. J. Urban / ESCG 105

Alpha Magnetic Spectrometer – 02 Cryomagnet Self Protection (CSP) Alpha Magnetic Spectrometer • Designed for mission success purposes only, no safety hazard ð The magnet structure will remain safe even if CSP circuitry does not function • CSP circuitry is redundant, and designed to identify a quench prelude condition in any individual coil and quench entire magnet evenly • Redundant heater chains routed to alternating coils (either chain sufficient to quench magnet) • Protects magnet by ensuring no magnet conductor deformation due to isolated heating, which could result in degraded performance May 21, 2007 Timothy. J. Urban / ESCG 106

Alpha Magnetic Spectrometer – 02 CSP Block Diagram Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 107

Alpha Magnetic Spectrometer – 02 Uninterruptible Power Supply (UPS) Alpha Magnetic Spectrometer • The UPS will consist of a redundant set of Lithium-Ion batteries • To ensure mission success during loss of ISS power or communication, the UPS battery will provide control power to payload – – Watch-dog timer/control circuit Quench monitoring Initiation of quench heater 45 A pulse Nominal ramp-down at the end of the eight hours. • Are sized for a minimum of 8 hours of operation, plus assisted quench operation / ramp down May 21, 2007 Timothy. J. Urban / ESCG 108

Alpha Magnetic Spectrometer – 02 Uninterruptible Power Supply (UPS) Alpha Magnetic Spectrometer • Battery is designed to meet: – NSTS 1700. 7 B, “Safety Policy and Requirements For Payloads Using the Space Transportation System” – NSTS 1700. 7 B ISS Addendum, “Safety Policy and Requirements For Payloads Using the International Space Station” – JSC 20793, “Manned Space Vehicle Battery Safety Handbook” • JSC EP 3 Battery Safety Form May 21, 2007 Timothy. J. Urban / ESCG 109

Alpha Magnetic Spectrometer – 02 CAB to UPS Block Diagram Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 110

Alpha Magnetic Spectrometer – 02 Uninterruptible Power Supply Components Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 111

Alpha Magnetic Spectrometer – 02 UPS Battery Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 112

Alpha Magnetic Spectrometer – 02 UPS Battery “Bricks” Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 113

Alpha Magnetic Spectrometer – 02 UPS Battery Management System (BMS) Alpha Magnetic Spectrometer • BMS is a radiation tolerant circuit that monitors and maintains a series string of eight Li-ion battery cells, with a nominal output voltage of 32 VDC. • The battery is monitored for unhealthy temperature and/or electrical conditions, upon which the system reacts to protect the cells. – – – Automatic Cell Balancing Thermal Monitoring Over-discharge Monitoring Short Circuit Protection Cell Over-voltage Monitoring • BMS consists of three PCBs: – Master Control Board – QTY 2 Monitor/Equalizer boards May 21, 2007 Timothy. J. Urban / ESCG 114

Alpha Magnetic Spectrometer – 02 UPS BMS Electronics Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 115

Alpha Magnetic Spectrometer – 02 Other Power Components Alpha Magnetic Spectrometer • Cryocooler Electronics Box (CCEB): – 120 VDC Bus Isolation provided by relays – Over current protection provided by dedicated circuitry in all 8 power amplifiers – Circuit protection provided by Solid State Power Controller (SSPC) in PDB and fuse (TBR) in CCEB • Detector Power Distribution (X-PD) and Detector High Voltage (X-HV): – X: sub-detectors, as previously explained – Galvanic isolation via converters – X-HV are potted for high voltage protection, and cabling has been sized as well • May 21, 2007 Maximum 2500 V Timothy. J. Urban / ESCG 116

Alpha Magnetic Spectrometer – 02 Avionics Overview Alpha Magnetic Spectrometer Payload and Integration Cables May 21, 2007 Timothy. J. Urban / ESCG 117

Alpha Magnetic Spectrometer – 02 Payload and Integration Cables Alpha Magnetic Spectrometer • Since the PDS and J-Crate provide isolation for any faults subsequent to them in the system, payload cables failures are not a threat to vehicle systems • Integration cables between these components and the ISS and STS interfaces meet the requirements to protect vehicle systems – Proper wire sizing – Designed and manufactured in compliance with SSP 57003 – Manufactured and tested by JSC per NASA/JSC-7003 May 21, 2007 Timothy. J. Urban / ESCG 118

Alpha Magnetic Spectrometer – 02 Payload and Integration Cables Alpha Magnetic Spectrometer • Wire sizing is designed to meet: – NSTS 1700. 7 B, "Safety Policy and Requirements For Payloads Using the Space Transportation System“ – NSTS 1700. 7 B ISS Addendum, "Safety Policy and Requirements For Payloads Using the International Space Station“ – NASA Technical Memorandum #TM 102179, "Selection of Wires and Circuit Protection Devices for NSTS Orbiter Vehicle Payload Electrical Circuits" May 21, 2007 Timothy. J. Urban / ESCG 119

Alpha Magnetic Spectrometer – 02 Payload Avionics Universal Interface Diagram Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 120

Alpha Magnetic Spectrometer – 02 Alpha Magnetic Spectrometer May 21, 2007 Payload and Integration Cables Tracking Matrix – reference only Timothy. J. Urban / ESCG 121

Alpha Magnetic Spectrometer – 02 Avionics Overview Alpha Magnetic Spectrometer Integrated Payload Avionics Testing May 21, 2007 Timothy. J. Urban / ESCG 122

Alpha Magnetic Spectrometer – 02 Integrated Payload Avionics Testing Alpha Magnetic Spectrometer • Integrated Payload testing: – – – Functional Beam TVT EMI: SSP 30237 testing agreed to by EMEP KSC Post-delivery functional STS and ISS FIT / IVT • DDRS-02 Testing – – JSC certification IVT with NGLS P/L End-to-end Software verification EMI (delta certification to NGLS – either test or analysis) May 21, 2007 Timothy. J. Urban / ESCG 123

Alpha Magnetic Spectrometer – 02 Integrated Payload Avionics Testing Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 124

Alpha Magnetic Spectrometer – 02 Integrated Payload Avionics Testing Alpha Magnetic Spectrometer May 21, 2007 Timothy. J. Urban / ESCG 125

Alpha Magnetic Spectrometer – 02 Alpha Magnetic Spectrometer Integrated Payload Avionics Testing COMPLETED • Suitcase Test Environment for Payloads Testing (May ‘ 03) • Preliminary Integration Test (June ‘ 03) – – Taxiscope testing (High Rate Data Link check-out) 1553 RT Validation testing APS testing Orbiter Interface Unit (OIU) Lab Testing • Functional Integration Test at KSC (January ‘ 05) – Follow-on at ISS System Integration Lab (ISIL) JSC (June ’ 05) May 21, 2007 Timothy. J. Urban / ESCG 126

Alpha Magnetic Spectrometer – 02 Alpha Magnetic Spectrometer Integrated Payload Avionics Testing PLANNED • Suitcase Test Environment for Payloads Testing (June ‘ 07) – PLMDM file transfer protocol • Electrical Power Quality Test (JSC EPSL) Early FY 2008 • Testing at KSC (during on-line processing) – – Cargo Integration Test Equipment (CITE) Payload Rack Checkout Unit (PRCU) / STEP Early STS IVT with QM J-Crate “OPF Sill-side” Integrated Payload Orbiter End to End Test May 21, 2007 Timothy. J. Urban / ESCG 127