Electronics updates since Phase II Baroswitch Electronics (BSE)

Alpha Magnetic Spectrometer

Alpha Magnetic Spectrometer – 02

Phase III PSRP / SRP

Electronics Summary

January 12, 2010

Timothy J. Urban / ESCG / Barrios Technology


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



• 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



• 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 “Global” Interfaces

Upstream Inhibits(first level)



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)


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)


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.



• 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



• 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




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




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



120 VDC CCEB Line

Solid State Limiting Circuit - - 14 5 - 10 ms

120 VDC CCS Line


Solid State Limiting Circuit - - 3.9 1 - 3 ms

28 VDC 5A Output Lines


28 VDC 10A Output

LineSolid State Limiting

Circuit - - 14 5 - 6 ms




CIRCUITSPROTECTIVE


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




120 VDC CCEB Line


28 VDC 5A Output Lines


28 VDC 10A Output

LineSolid State Limiting

Circuit - - 14 5 - 6 ms

PDS Protective Devices – Derating Summary




CIRCUITSPROTECTIVE


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



• 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




Example of High Voltage Component

Potting. RICH Photo

Multiplier Tube




Example of High Voltage Component Potting.ECAL Photo Multiplier Tube




Coronal Discharge Testing ofTRD High Voltage Straws.




Corona Test Results for TRD UTE



• 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



AMS02 Electronics SummaryPayload Grounding – RAM Electronics

Alo

din

ed m

ech

anic

al li

nks

Gro

und

Str

aps



• Electronics ground strap.





+ 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




• Vacuum case is grounded to USS via 00AWG wires (QTY 2).

VC Bonding Strap 1VC Bonding Strap 2



• MLI Blanket Class S bond wire grounded.




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



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




NOTE: Placards may not represent flight configuration.

Configure Payload Data Interface Panel#1 (PDIP1)




PGSC based “AMS Laptop”

USB/422 Adaptor Box with Integrated PDIP Cable

Electronics updates since Phase II Baroswitch Electronics (BSE)

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