alpha magnetic spectrometer – 02 avionics outline
DESCRIPTION
Alpha Magnetic Spectrometer – 02 Phase II Flight Safety Review Avionics Overview May 21, 2007 Timothy J. Urban / ESCG / Barrios Technology. Alpha Magnetic Spectrometer – 02 Avionics Outline. Alpha Magnetic Spectrometer – 02 Avionics Overview. Overview caveats: - PowerPoint PPT PresentationTRANSCRIPT
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Phase II Flight Safety Review
Avionics Overview
May 21, 2007
Timothy J. Urban / ESCG / Barrios Technology
May 21, 2007 Timothy. J. Urban / ESCG 2
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Avionics Outline
May 21, 2007 Timothy. J. Urban / ESCG 3
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Alpha Magnetic Spectrometer – 02Avionics Overview
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 4
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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)
May 21, 2007 Timothy. J. Urban / ESCG 5
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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
May 21, 2007 Timothy. J. Urban / ESCG 6
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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
Alpha Magnetic Spectrometer – 02Avionics Overview (continued)
May 21, 2007 Timothy. J. Urban / ESCG 7
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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
Alpha Magnetic Spectrometer – 02Avionics Overview (continued)
May 21, 2007 Timothy. J. Urban / ESCG 8
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Alpha Magnetic Spectrometer – 02Typical Crate Installation
May 21, 2007 Timothy. J. Urban / ESCG 9
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Alpha Magnetic Spectrometer – 02Avionics Layout
May 21, 2007 Timothy. J. Urban / ESCG 10
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Alpha Magnetic Spectrometer – 02Avionics Layout (continued)
May 21, 2007 Timothy. J. Urban / ESCG 11
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Alpha Magnetic Spectrometer – 02Avionics Overview
May 21, 2007 Timothy. J. Urban / ESCG 12
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Alpha Magnetic Spectrometer – 02Avionics Overview
COMMAND AND DATA HANDLING SYSTEM
May 21, 2007 Timothy. J. Urban / ESCG 13
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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
May 21, 2007 Timothy. J. Urban / ESCG 14
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Alpha Magnetic Spectrometer – 02Command and Data Handling System
Block Diagram
AMSWire
AMSWire
May 21, 2007 Timothy. J. Urban / ESCG 15
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J-Crate Scheme & test setup4* Main Computer + Interfaces
J-Crate
CompactPCI Bus Backplane
AMS Specific Backplane (ASB) Signals and Power
JSBC
Local Bus
SDRAM Flash PROM
PPC 750 CPC 700
PCI Agent
DP
RA
M
Reg
isters
JIM-CAN
PCI Agent
DP
RA
M
Reg
isters
JIM-AMSW&15
53
PCI Agent
DP
RA
M
Reg
isters
JIM-HRDL/422
JBU
FPGA
JHIF
x4JL
IF
JPD US
CM
AMSWx4
CANx2
Front Panel Connectors
HRDLx2
RS422x2
1553x2
Powerx1
CANx2
CDDCCDDCCDDCCDDCx4
EVA PanelROEU Panel
May 21, 2007 Timothy. J. Urban / ESCG 16
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Alpha Magnetic Spectrometer – 02J-Crate Flight Model
May 21, 2007 Timothy. J. Urban / ESCG 17
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Alpha Magnetic Spectrometer – 02J-Crate 1553 Data Interfaces
May 21, 2007 Timothy. J. Urban / ESCG 18
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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)
May 21, 2007 Timothy. J. Urban / ESCG 19
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Alpha Magnetic Spectrometer – 02Payload High Rate Data Link on ISS
~ 100Mbit/sMax. 2 Mbit/s
Long-termAggregate
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 RecorderHRFM High Rate Frame MultiplexerHRM High Rate Modem
May 21, 2007 Timothy. J. Urban / ESCG 20
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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
Alpha Magnetic Spectrometer – 02Data System Components
May 21, 2007 Timothy. J. Urban / ESCG 21
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Payload Tiered C&DH System
Alpha Magnetic Spectrometer – 02Command and Data Handling System
May 21, 2007 Timothy. J. Urban / ESCG 22
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Alpha Magnetic Spectrometer – 02Housekeeping Data Overview(equivalent to NASA H&S Data)
May 21, 2007 Timothy. J. Urban / ESCG 23
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Alpha Magnetic Spectrometer – 02Science Data Architecture
thresholds, etc., by
May 21, 2007 Timothy. J. Urban / ESCG 24
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Alpha Magnetic Spectrometer – 02Data System resources
May 21, 2007 Timothy. J. Urban / ESCG 25
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Alpha Magnetic Spectrometer – 02Power Distribution System
OverviewThe 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 26
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Alpha Magnetic Spectrometer – 02Avionics Overview - Power Systems
May 21, 2007 Timothy. J. Urban / ESCG 27
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Alpha Magnetic Spectrometer – 02Avionics Overview - Power Systems
May 21, 2007 Timothy. J. Urban / ESCG 28
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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
May 21, 2007 Timothy. J. Urban / ESCG 29
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Alpha Magnetic Spectrometer – 02Avionics Overview
Mission Phased Avionics Systems
Interfaces and Functions
May 21, 2007 Timothy. J. Urban / ESCG 30
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Mission Phased Avionics Interfaces • STS, via ROEU PDA
– Pre-Launch– Ascent– On-Orbit
• ISS SSRMS, via PVGF• ISS CAS, via UMA
Alpha Magnetic Spectrometer – 02Avionics Overview
May 21, 2007 Timothy. J. Urban / ESCG 31
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Alpha Magnetic Spectrometer – 02Payload Avionics Universal Interface Diagram
May 21, 2007 Timothy. J. Urban / ESCG 32
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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
Alpha Magnetic Spectrometer – 02Avionics Overview
May 21, 2007 Timothy. J. Urban / ESCG 33
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Alpha Magnetic Spectrometer – 02Avionics Systems Interface Diagram – STS Pre-Launch
May 21, 2007 Timothy. J. Urban / ESCG 34
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Alpha Magnetic Spectrometer – 02ROEU PDA and Interface Panel A
Remotely Operated Electrical UmbilicalPayload Disconnect Assembly
Interface Panel A
May 21, 2007 Timothy. J. Urban / ESCG 35
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• 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
Alpha Magnetic Spectrometer – 02Avionics Overview – Pre-Launch
May 21, 2007 Timothy. J. Urban / ESCG 36
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SFHe Tank Vent Pump
Alpha Magnetic Spectrometer – 02Avionics Overview – Pre-Launch
• Pre-Launch only• T0 110 VAC interface and ground safety being worked with STS
Program and KSC, including EMI
May 21, 2007 Timothy. J. Urban / ESCG 37
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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.
Alpha Magnetic Spectrometer – 02Avionics Overview – Pre-Launch
May 21, 2007 Timothy. J. Urban / ESCG 38
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Alpha Magnetic Spectrometer – 02Avionics Systems Interface Diagram – STS Ascent
May 21, 2007 Timothy. J. Urban / ESCG 39
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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.
May 21, 2007 Timothy. J. Urban / ESCG 40
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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
Alpha Magnetic Spectrometer – 02Avionics Overview – STS Ascent
May 21, 2007 Timothy. J. Urban / ESCG 41
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Alpha Magnetic Spectrometer – 02Avionics Systems Interface Diagram – STS On-Orbit
May 21, 2007 Timothy. J. Urban / ESCG 42
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• 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
Alpha Magnetic Spectrometer – 02Avionics Overview – STS On-Orbit
May 21, 2007 Timothy. J. Urban / ESCG 43
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Configure PDIP1
Alpha Magnetic Spectrometer – 02Avionics Overview – STS On-Orbit
May 21, 2007 Timothy. J. Urban / ESCG 44
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Configure PDIP2
Alpha Magnetic Spectrometer – 02Avionics Overview – STS On-Orbit
May 21, 2007 Timothy. J. Urban / ESCG 45
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Digital Data Recorder System-02 (DDRS-02)
Alpha Magnetic Spectrometer – 02Avionics Overview – STS On-Orbit
• 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 46
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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 kW– 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
Alpha Magnetic Spectrometer – 02Avionics Overview – STS On-Orbit
May 21, 2007 Timothy. J. Urban / ESCG 47
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Simplified Payload Power-Up Sequence
Alpha Magnetic Spectrometer – 02Avionics Overview – STS On-Orbit
May 21, 2007 Timothy. J. Urban / ESCG 48
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Alpha Magnetic Spectrometer – 02Avionics Systems Interface Diagram – Hand-Off
May 21, 2007 Timothy. J. Urban / ESCG 49
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Alpha Magnetic Spectrometer – 02PVGF Location
May 21, 2007 Timothy. J. Urban / ESCG 50
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Alpha Magnetic Spectrometer – 02SSRMS Power Block Diagram
May 21, 2007 Timothy. J. Urban / ESCG 51
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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 operationssMagnet 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
Alpha Magnetic Spectrometer – 02Avionics Overview – Hand-Off
May 21, 2007 Timothy. J. Urban / ESCG 52
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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 wiresDe-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
PSRP Technical Expert ConcurrencePending review and approval from ISS EVR and PICB panels
Alpha Magnetic Spectrometer – 02Avionics Overview – Hand-Off
May 21, 2007 Timothy. J. Urban / ESCG 53
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Payload Hand-Off (continued)• SRMS release of AMS-02• Transfer to S3 attach site • Attach AMS-02 to S3 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
Alpha Magnetic Spectrometer – 02Avionics Overview – Hand-Off
May 21, 2007 Timothy. J. Urban / ESCG 54
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Transfer to ISS
AMS
AMS
AMS on ISS
AMS
SRMS
SSRMS
S3 attach site
1 2
3 4
Alpha Magnetic Spectrometer – 02Avionics Overview – Hand-Off
May 21, 2007 Timothy. J. Urban / ESCG 55
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Berthing to ISS – S3 Upper / Inboard
Alpha Magnetic Spectrometer – 02Avionics Overview – Hand-Off
May 21, 2007 Timothy. J. Urban / ESCG 56
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Alpha Magnetic Spectrometer – 02Avionics Systems Interface Diagram – ISS
May 21, 2007 Timothy. J. Urban / ESCG 57
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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
Alpha Magnetic Spectrometer – 02Avionics Overview – ISS
May 21, 2007 Timothy. J. Urban / ESCG 58
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On-Orbit ISS Operations (continued)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
Alpha Magnetic Spectrometer – 02Avionics Overview – ISS
May 21, 2007 Timothy. J. Urban / ESCG 59
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On-Orbit ISS Operations (continued)• Control of AMS-02 is from groundOnly 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
Alpha Magnetic Spectrometer – 02Avionics Overview – ISS
May 21, 2007 Timothy. J. Urban / ESCG 60
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Simplified Payload Power-Up Sequence
Alpha Magnetic Spectrometer – 02Avionics Overview – ISS
May 21, 2007 Timothy. J. Urban / ESCG 61
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EVA Connector Panel• EVA Connector Panel allows for redundant avionics
interfaces in contingency scenario– Connectors will meet the mating/demating requirements
identified in letter MA2-99-170, 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 UMACryomagnet charge can be performed on UMA powered
PDS A-side (prime) bus only.
Alpha Magnetic Spectrometer – 02Avionics Overview – ISS
May 21, 2007 Timothy. J. Urban / ESCG 62
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Alpha Magnetic Spectrometer – 02EVA Connector Panel Interfaces
Connector
A
B
May 21, 2007 Timothy. J. Urban / ESCG 63
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Alpha Magnetic Spectrometer – 02EVA Connector Panel Location
EVA ConnectorPanel
UMA
May 21, 2007 Timothy. J. Urban / ESCG 64
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EVA Interface Panel and UMA Operations
Alpha Magnetic Spectrometer – 02Avionics Overview – ISS
May 21, 2007 Timothy. J. Urban / ESCG 65
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Alpha Magnetic Spectrometer – 02Avionics Overview
Power Systems Detailed
May 21, 2007 Timothy. J. Urban / ESCG 66
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Alpha Magnetic Spectrometer – 02Power Systems Detailed
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 67
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Alpha Magnetic Spectrometer – 02Power Systems Detailed
Power Distribution System – Front End
Provides 1MΩ isolation requirement for payload• Wire sizing is designed 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 #TM 102179, "Selection of Wires and Circuit Protection Devices for NSTS Orbiter Vehicle Payload Electrical Circuits"
May 21, 2007 Timothy. J. Urban / ESCG 68
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Alpha Magnetic Spectrometer – 02Power Systems Detailed
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 120VDC 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 69
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Alpha Magnetic Spectrometer – 02Power Systems Detailed
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 70
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Alpha Magnetic Spectrometer – 02Power Distribution System Location
PDS
May 21, 2007 Timothy. J. Urban / ESCG 71
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Alpha Magnetic Spectrometer – 02Avionics Overview - Power Systems
May 21, 2007 Timothy. J. Urban / ESCG 72
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Alpha Magnetic Spectrometer – 02Avionics Overview - Power Systems
May 21, 2007 Timothy. J. Urban / ESCG 73
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Alpha Magnetic Spectrometer – 02Power Distribution System
May 21, 2007 Timothy. J. Urban / ESCG 74
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Alpha Magnetic Spectrometer – 02Power Distribution System
May 21, 2007 Timothy. J. Urban / ESCG 75
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Alpha Magnetic Spectrometer – 02Power Distribution System
May 21, 2007 Timothy. J. Urban / ESCG 76
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Alpha Magnetic Spectrometer – 02Power Systems Detailed
Engineering Model (one-half populated)
May 21, 2007 Timothy. J. Urban / ESCG 77
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Alpha Magnetic Spectrometer – 02Power Distribution System Bonding
The PDS bonding is designed per SSP-30240 Space Station Grounding Requirements, Rev. C:
• Minimum isolation of 1MΩ 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 78
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• 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.
Alpha Magnetic Spectrometer – 02PDS Bonding (continued)
May 21, 2007 Timothy. J. Urban / ESCG 79
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Alpha Magnetic Spectrometer – 02Power Distribution System Bonding
May 21, 2007 Timothy. J. Urban / ESCG 80
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Alpha Magnetic Spectrometer – 02Payload Bonding
• 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 81
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Alpha Magnetic Spectrometer – 02Payload Bonding
• 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 82
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Alpha Magnetic Spectrometer – 02Payload Heaters
• 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 83
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Alpha Magnetic Spectrometer – 02Payload Heaters
• This is typical for safety critical heaters.• However, no heaters are required for safety.
May 21, 2007 Timothy. J. Urban / ESCG 84
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Alpha Magnetic Spectrometer – 02Cryomagnet Avionics Box (CAB)
• 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 85
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Alpha Magnetic Spectrometer – 02Cryomagnet Avionics Box Block Diagram
May 21, 2007 Timothy. J. Urban / ESCG 86
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Avionics Box Location
May 21, 2007 Timothy. J. Urban / ESCG 87
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Avionics Box Layout
May 21, 2007 Timothy. J. Urban / ESCG 88
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Current Source (CCS)
• CCS design includes three protection barriers in series to prevent an actual current at the magnet higher than 459A:– Software protection (value between 455.33A and 459) – Field Programmable Gate Array (FPGA) protection (limit is 459A)– Hard-wired control electronics protection circuitry (limit 459A)
• Isolation for the 120Vdc 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 (8kV) protection to prevent feedback from unprotected quench (analysis shows maximum voltage is 5.5 kV).
May 21, 2007 Timothy. J. Urban / ESCG 89
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 500A 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.
Alpha Magnetic Spectrometer – 02Cryomagnet Current Source (CCS)
May 21, 2007 Timothy. J. Urban / ESCG 90
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Magnet Charging (continued)
• 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 91
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 super-conducting temperatures (heated by low voltage heaters to “open”)
Alpha Magnetic Spectrometer – 02Magnet Charging (continued)
May 21, 2007 Timothy. J. Urban / ESCG 92
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Charge Cable Routing
VC Port for Cable Interface
Charge Cables (00 AWG)
CAB Connections
May 21, 2007 Timothy. J. Urban / ESCG 93
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Charge Cable VC Interface
Current Leads Soldered
Current Leads Soldered
00 AWG CableAttach Points(X3 each)
VC Port
VC UpperRing
May 21, 2007 Timothy. J. Urban / ESCG 94
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Dump Diodes (CDD)
• 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 95
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Dump Diodes (CDD) - Schematic
May 21, 2007 Timothy. J. Urban / ESCG 96
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Dump Diodes (CDD)
Cryomagnet Dump Diodes (CDD) Subassembly
May 21, 2007 Timothy. J. Urban / ESCG 97
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Dump Diodes (CDD)
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 98
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Dump Diodes (CDD)
CDD QM Assembly Sequence
May 21, 2007 Timothy. J. Urban / ESCG 99
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Dump Diodes (CDD)
CDD Typical Installation without Protective Cover
CDD Assembly
Sill Trunnion Block
Discharge Cabling
May 21, 2007 Timothy. J. Urban / ESCG 100
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Dump Diodes (CDD)
CDD Typical Installation (QM) with Protective Cover
Completed CDD Assembly
Sill Trunnion Block
May 21, 2007 Timothy. J. Urban / ESCG 101
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Dump Diodes (CDD)
CDD Locations and Cable Routing
Discharge CablesRouted to CAB
CDD PortAssembly
Bank-to-BankDischarge Cables
Routed under Beam
CDD StarboardAssembly
May 21, 2007 Timothy. J. Urban / ESCG 102
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Dump Diodes (CDD)
CDD Thermal Vacuum Test Set-up
May 21, 2007 Timothy. J. Urban / ESCG 103
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Dump Diodes (CDD)
CDD Thermal Vacuum Test Set-up
Power Supplies T/C DAQ Modules
Isolated T/C Converter
Thermal VacuumChamber
Diode Bank on Sill Trunnion Block
May 21, 2007 Timothy. J. Urban / ESCG 104
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Control and Signal Conditioning
• 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).
May 21, 2007 Timothy. J. Urban / ESCG 105
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Self Protection (CSP)
• 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 45A 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 106
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Cryomagnet Self Protection (CSP)
• Designed for mission success purposes only, no safety hazard 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 107
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02CSP Block Diagram
May 21, 2007 Timothy. J. Urban / ESCG 108
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Uninterruptible Power Supply (UPS)
• 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 45A 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 109
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Uninterruptible Power Supply (UPS)
• Battery is designed 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”– JSC 20793, “Manned Space Vehicle Battery Safety Handbook”
• JSC EP3 Battery Safety Form
May 21, 2007 Timothy. J. Urban / ESCG 110
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02CAB to UPS Block Diagram
May 21, 2007 Timothy. J. Urban / ESCG 111
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Uninterruptible Power Supply Components
May 21, 2007 Timothy. J. Urban / ESCG 112
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02UPS Battery
May 21, 2007 Timothy. J. Urban / ESCG 113
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02UPS Battery “Bricks”
May 21, 2007 Timothy. J. Urban / ESCG 114
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02UPS Battery Management System (BMS)
• 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 32VDC.
• 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 115
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02UPS BMS Electronics
May 21, 2007 Timothy. J. Urban / ESCG 116
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Other Power Components
• Cryocooler Electronics Box (CCEB):– 120VDC 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• Maximum 2500 V
May 21, 2007 Timothy. J. Urban / ESCG 117
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Avionics Overview
Payload and Integration Cables
May 21, 2007 Timothy. J. Urban / ESCG 118
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Payload and Integration Cables
• 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 119
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Payload and Integration Cables
• Wire sizing is designed 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 #TM 102179, "Selection of Wires and Circuit Protection Devices for NSTS Orbiter Vehicle Payload Electrical Circuits"
May 21, 2007 Timothy. J. Urban / ESCG 120
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Payload Avionics Universal Interface Diagram
May 21, 2007 Timothy. J. Urban / ESCG 121
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Payload and Integration CablesTracking Matrix – reference only
May 21, 2007 Timothy. J. Urban / ESCG 122
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Avionics Overview
Integrated Payload Avionics Testing
May 21, 2007 Timothy. J. Urban / ESCG 123
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Integrated Payload Avionics Testing
• Integrated Payload testing:– Functional– Beam– TVT– EMI: SSP30237 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 124
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Integrated Payload Avionics Testing
May 21, 2007 Timothy. J. Urban / ESCG 125
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Integrated Payload Avionics Testing
May 21, 2007 Timothy. J. Urban / ESCG 126
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Integrated 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 127
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02Integrated Payload Avionics Testing
PLANNED
• Suitcase Test Environment for Payloads Testing (June ‘07)– PLMDM file transfer protocol
• Electrical Power Quality Test (JSC EPSL) Early FY2008• 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