Alpha Magnetic Spectrometer Alpha Magnetic Spectrometer – 02 Phase III PSRP / SRP Electronics Summary January 12, 2010 Timothy J. Urban / ESCG / Barrios Technology
Jan 13, 2016
Alpha Magnetic Spectrometer
Alpha Magnetic Spectrometer – 02
Phase III PSRP / SRP
Electronics Summary
January 12, 2010
Timothy J. Urban / ESCG / Barrios Technology
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 2
• Electronics updates since Phase II– Baroswitch Electronics (BSE)– Cryomagnetic Pilot Valve Switch (CPVS) Box
• Upstream Power Inhibits• Power Circuit Protection
– Wire sizing– Component de-rating
• High Voltages– Component accessibility– Corona testing
• Grounding– Electronics– Thermal Control System Blankets
• STS IVA Volume Hardware – Digital Data Recording System
AMS02 Electronics SummaryOutline
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 3
• Baroswitch Electronics (BSE) – Design Evolved– Uses STS Standard Switch Panel 28VDC (less than one amp).– When STS PLB pressure < 15 mbar, a baroswitch closes.– This is a trigger to open a series of valves which opens the AMS flight
vent, allowing LHe boil-off vapor to exhaust from the LHe tank, maintaining LHe temperature below the super-fluid Lamda point.
– Time-tagged (180 seconds) STS Back-up Flight Computer Discrete Output Low (DOL) is a redundant trigger to this valve open operation.
• Redundant trigger is “Or’ed” by the BSE.
• The DOL, if later, will not undo the baroswitch trigger, and vice-versa.
– Nominally occurs during powered ascent to prevent LHe contact on porous plug: Mission Success only – No safety implication.
– Back-up plan would be for payload commands to open vent during an STS Orbiter +X maneuver.
AMS02 Electronics SummaryElectronics updates since Phase II
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 4
• Cryomagnetic Pilot Valve Switch (CPVS) Box – New Addition– Boosts the trigger power from BSE to meet specifications / requirements
of the valves.– Powered by payload Uninterruptible Power Supply (UPS) during ascent.– UPS power bus isolated from all other payload power buses.
AMS02 Electronics SummaryElectronics updates since Phase II
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 5
AMS02 Electronics SummaryElectronics updates since Phase II
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 6
AMS02 “Global” Interfaces
Upstream Inhibits(first level)
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 7
AMS02 Electronics SummaryUpstream Power Inhibits
Connector TYPE Voltage Max Current
Inhibit #1
Inhibit #2
Connector
Type/Feature
EVA
Automated
HIGH POWER CONNECTORS
EVA Connector
Power
AMS-02 120V DC
(ISS)
~19 A ISS RPC
SPDA S3-1A4B, II 4B-E (A9), SPDA S3-3A,
II03A-E(A2)
Demate UMA
(Optional use of DDCU P1-3A and DDCU S1-4B)
NZGL06G2525LN7SN
EVA
ROEU GFE 120V DC
(APCU)
~19 A APCU OFF APCU Power Source Off GFE Provided Auto/ EVA Capable
ROEU GFE 28V DC ~ 5A Disable SSP2A Switches S16 Primary, S18
Secondary
Disable SSP 2ACircuit breaker CB4.
GFE Provided Auto/ EVA Capable
UMA GFE 120V DC
(ISS)
~19 A ISS RPC
SPDA S3-1A4B, II 4B-E (A9), SPDA S3-3A,
II03A-E(A2)
Vehicle Discretion as to location of second inhibit to power. To be addressed in ISS EPS 309 (Boeing Integrated Report)
GFE Provided Auto/ EVA Capable
PVGF GFE 120V DC
(ISS)
~15 A (depends on location on ISS)
Vehicle Discretion as to location of second inhibit to power. To be addressed in ISS EPS 309 (Boeing Integrated Report)
GFE Provided Auto/ EVA Capable
LOW POWER CONNECTORS
EVA Connector Data – 1553
Talkback
AMS-02 14V PtP (1553)
<=5 V DC
Very Small – Signal
<<1 A
ISS RPC SPDA S3-1A4B, II 4B-E (A9), SPDA
S3-3A, II03A-E(A2)
NZGL06G1515N35PA-1
EVA
EVA Connector Fiber Optic/Talk Back
AMS-02 <=5 V DC <<1 A ISS RPC SPDA S3-1A4B, II 4B-E (A9), SPDA S3-
3A, II03A-E(A2)
NZGL06G1717N13PN
EVA
Highlighted elements are GFE hardware and controlled by the supporting vehicle programs.
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 8
• Inhibits are used to disable payload power prior to connector mate / de-mate (dead-faced).
• Two upstream inhibits have been identified for all STS and ISS power sources.
• These inhibits are STS and ISS vehicle utilizations that are enacted by flight procedure (OCAD).
AMS02 Electronics SummaryUpstream Power Inhibits
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 9
• All payload power and data wire sizing, for both STS and ISS interfaces, was designed “carrying-through” the wire sizing used on the vehicle side of the interfaces (ICD compliant).
• Payload designed and selected proper materials for integration cabling and circuit protection devices to meet:– NSTS 1700.7B, “Safety Policy and Requirements for Payloads using
the Space Transportation System”– NSTS 1700.7B ISS Addendum, “Safety Policy and Requirements for
Payloads using the International Space Station”– NASA Technical Memorandum #102179, “Selection of Wires and
Circuit Protection Devices for NSTS Orbiter Vehicle Payload Electrical Circuits”
AMS02 Electronics SummaryPower Circuit Protection
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 10
AMS02 Electronics SummaryPower Circuit Protection
SOURCE Wire/Cabling Maximum Current Provided Nominally
Lowest Current Limitation Level
Voltage
STS T0 Power 4 x AWG 12 14.7 A 22A 120 V
STS APCU 3 x AWG 8 14.7 A 22 A 120 V
ITS S3 PAS 2 3 x AWG 8 25 A 27.5 A 120 V
PVGF 4 x AWG 12 15 A 27.5 A 120 V
STS SSP 20 AWG 5 A (SSP Circuit Breaker)
4 A (AMS-02 Fuse)
28 V
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 11
AMS02 Electronics SummaryPower Circuit Protection
PDS Protective Devices – Derating Summary
CIRCUITSPROTECTIVE
DEVICE PART NUMBER MIL SPEC
MINIMUM TRIP THRESHOL
D (Amp)
MINIMUM TRIP DECISION
TIME
MAIN PWR FEED
Local Heaters Fuse P600L-135-7.5 MIL-PRF-23419 7.5 .0008 - 4.0 sec
120 VDC Heater Lines
Fuse P600L-135-3.0 MIL-PRF-23419 3.0 .00010 - 0.3 sec
Fuse P600L-135-5.0 MIL-PRF-23419 5.0 .00010 - 0.3 sec
Fuse P600L-135-7.5 MIL-PRF-23419 7.5 .0008 - 4.0 sec
120 VDC CCEB Line
Solid State Limiting Circuit - - 14 5 - 10 ms
120 VDC CCS Line
Fuse P600L-135-7.5 MIL-PRF-23419 7.5 .0008 - 4.0 sec
Solid State Limiting Circuit - - 3.9 1 - 3 ms
28 VDC 5A Output Lines
Solid State Limiting Circuit - - 7 5 - 6 ms
28 VDC 10A Output
LineSolid State Limiting
Circuit - - 14 5 - 6 ms
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 12
AMS02 Electronics SummaryPower Circuit Protection
CIRCUITSPROTECTIVE
DEVICE PART NUMBER MIL SPEC
MINIMUM TRIP THRESHOL
D (Amp)
MINIMUM TRIP DECISION
TIME
AUX PWR FEED
Local Heaters Fuse P600L-135-7.5 MIL-PRF-23419 7.5 .0008 - 4.0 sec
120 VDC Heater Lines
Fuse P600L-135-3.0 MIL-PRF-23419 3.0 .00010 - 0.3 sec
Fuse P600L-135-5.0 MIL-PRF-23419 5.0 .00010 - 0.3 sec
Fuse P600L-135-7.5 MIL-PRF-23419 7.5 .0008 - 4.0 sec
120 VDC CCEB Line
Solid State Limiting Circuit - - 14 5 - 10 ms
28 VDC 5A Output Lines
Solid State Limiting Circuit - - 7 5 - 6 ms
28 VDC 10A Output
LineSolid State Limiting
Circuit - - 14 5 - 6 ms
PDS Protective Devices – Derating Summary
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 13
AMS02 Electronics SummaryPower Circuit Protection
CIRCUITSPROTECTIVE
DEVICE PART NUMBER MIL SPEC
MINIMUM TRIP THRESHOLD
(Amp)MINIMUM TRIP DECISION TIME
MAIN PWR FEED
28 VDC Input Line (<1 Amp)
Fuse P600L-72-4.0 MIL-PRF-23419 4.0 .00015 - .300 sec
BSE Protective Devices – Derating Summary
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 14
• All payload high voltage sources are potted, and inaccessible; either by sub-system structure or MLI blanket.
• All high voltage cables have been properly selected and de-rated (COTS equipment).
AMS02 Electronics SummaryHigh Voltages
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 15
AMS02 Electronics SummaryHigh Voltages
Example of High Voltage Component
Potting. RICH Photo
Multiplier Tube
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 16
AMS02 Electronics SummaryHigh Voltages
Example of High Voltage Component Potting.ECAL Photo Multiplier Tube
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 17
AMS02 Electronics SummaryHigh Voltages
Coronal Discharge Testing ofTRD High Voltage Straws.
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 18
AMS02 Electronics SummaryHigh Voltages
Corona Test Results for TRD UTE
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 19
• The AMS-02 payload structure is mechanically grounded, depending on mission phase, as follows:– STS – via the payload mounting trunnions– SSRMS – via the SSRMS / PVGF interface– ISS CAS site – via the PAS guide vane pins
• Payload grounds are designed for DC component of Class R (< 2.5mOhm), so the intent will meet Class H.
• Payload structure riveted joints have been measured in compliance with this – will repeat after integrated TVT to demonstrated no thermal relaxation.
• Electronics are assembled with Alodined links that ground them together – then bond straps ground them to the radiators, which are ground strapped to the USS.
AMS02 Electronics SummaryPayload Grounding
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 20
AMS02 Electronics SummaryPayload Grounding – RAM Electronics
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anic
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Gro
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Str
aps
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 21
• Electronics ground strap.
AMS02 Electronics SummaryPayload Grounding
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 22
AMS02 Electronics SummaryPayload Grounding
+ X (RAM)
+ Y
+ ZISS
+ Z
+ X
+ Y
ORBITER
VC Bonding Strap 1
• Vacuum case is grounded to USS via 00AWG wires (QTY 2).
ORBITER
+ X (RAM)+ Y
+ Z
ISS
+ Z
+ X
+ Y
VC Bonding Strap 2
VC Bonding Strap 2
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 23
AMS02 Electronics SummaryPayload Grounding
• Vacuum case is grounded to USS via 00AWG wires (QTY 2).
VC Bonding Strap 1VC Bonding Strap 2
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 24
• MLI Blanket Class S bond wire grounded.
AMS02 Electronics SummaryPayload Grounding
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 25
Non-grounded interior MLI blankets will require EMEP TIA:• TRDGB (XE & CO2 tanks, Valve block bootie• TTCS tubing lines• Cryocooler evaporators
AMS02 Electronics SummaryUngrounded MLI Blankets
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 26
Digital Data Recording System (DDRS)• Records back-up of down-linked science data on-board STS• Provides contingency STS crew capabilities:
– Limited payload systems health monitor
– Limited payload command (worked with MCC-H and POCC)
• Materials and flammability assessment complete• Full scope of EMI testing complete (susceptibility and emissions)
AMS02 Electronics SummaryIVA Habitable Volume Equipment
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 27
AMS02 Electronics SummaryIVA Habitable Volume Equipment
NOTE: Placards may not represent flight configuration.
Configure Payload Data Interface Panel#1 (PDIP1)
Alpha Magnetic Spectrometer
January 12, 2010 Tim Urban / ESCG 28
AMS02 Electronics SummaryIVA Habitable Volume Equipment
PGSC based “AMS Laptop”
USB/422 Adaptor Box with Integrated PDIP Cable