NASA’s SETPath Mission: Living With a Star (LWS) Space Environment … · 2002-08-01 · Materials • Spacecraft Charging/Discharging Perform applications research on environment

NASA’s SETPath Mission: Living With a Star (LWS) Space Environment

Testbed (SET) Pathfinder

Ken Ken LaBelLaBelNASA/GSFCNASA/GSFC

[email protected]@gsfcgsfc..nasanasa..govgovJanet Janet BarthBarth, NASA/GSFC, NASA/GSFCDana Brewer, NASA/HQDana Brewer, NASA/HQ

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Presented by Ken LaBel, NASA/GSFC at the SEE Symposium in Manhattan Beach, CA on Apr 23, 2002

OUTLINE

• What is LWS?• SET Overview• SETPath

– Overview– Architecture– Experiments– Implementation

• SETPath Implementation • Summary

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LWS Program Architecture

UNDERSTANDING

Science with Utility

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How Does LWS Science Reach Customers?

Science MissionsTMDA Program SETs

Customer NeedTools to Mitigate

Space Weather Effectson Technologies

Customer* Goal• Increase Capability• Decrease Hardware

Development Costs

SolutionUse

New Technologies& COTS**

ProblemSystems are vulnerable to space environments.

(Space Weather)

*NASA Missions, NASA Life Support Systems, University Smallsats , DoD, Spacecraft Industry, Aircraft Industry

** Commercial-off-the-Shelf

Define the Environment Define the Response

Inputs for ModelsSpecification, Nowcasting, Forecasting

Inputs for ToolsGround Test Protocol Validation, Interaction Models

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SPACE ENVIRONMENT TESTBEDS (SET) PROJECT OBJECTIVES

Understand Environment InteractionWith Flight Components

Atmosphere

Plasma

Debris &Meteoroid

SpaceRadiation

Microelectronics • DetectorsMaterials • Spacecraft Charging/Discharging

Perform applications research on environment interactions with instruments & spacecraft

Purpose: Improve performance & reliability and reduce costs of instruments & spacecraft by measuring & understanding the effects of space weather on technology

Benefits the entire scientific and aerospace community by providing much-needed early data to reduce the uncertainty in mission design, flight qualification of test methods for critical hardware & reduce mission costs

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The SEE Symposium Event 2002

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What is SET comprised of?• SET is comprised of three prime elements

– The mining of existing solar-variant flight data for engineering purposes such as tool development

• Results of the first award of NASA Research Announcement (NRA) winners may be found at http://see.msfc.nasa.gov

– The development of engineering infrastructure to support flight experiments

• This is called a carrier or carrier-plus– Provides electrical, power, etc interfaces to experiments

as well as a central interface to the host spacecraft• Correlative environment monitors (CEMs) allow in-situ

measurements versus technology performance– Flight experiments designed to investigate and/or validate solar-

variant environment interaction with technology• Microelectronics, photonics, sensors/detectors, materials, etc

– Models, test protocols, prediction techniques, mitigative methods

• Provided via NRA or by partners– Experiments are not required to use the carrier if they already

have flight accommodations

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SET Products

Reduce design margins? Increase use of space environment

“tolerant” technologies? Increase the fraction of resources

for payload? Reduce launch vehicle

requirements? Enable routine operations above

Low Earth Orbit (LEO) (above 2000 km) for LEO cost.

Improve operational guidelines

? Reduce unnecessary shutdowns

? Lower the risk of anomalies

? Reduce the number of failures

Define space environment effects and mechanisms

? Detector/sensor degradation and failure mechanisms

?Methods to control/eliminate plasma effects

?Methods to control/eliminate deep dielectric charging effects

?Materials degradation mechanisms and rates

?Methodologies to improve microelectronics performance

LWS/SETResearch to Reduce

Impacts of Solar Variabilitye.g., Space Weather

Test & flight validate test methods forenabling technologies

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Looking For a FewGood SET Partners!

• SET is a partnered program– We seek partnering at all levels (free is good!)

• Launch Opportunities• Spacecraft• Systems• Engineering Support• Experiments

– May still have to propose via NRA– Fuller partners may not have to propose

» Ex., provide a launch opportunity for free• We are restricted on exchange of funds with international

partners, but still highly seek their contribution and participation

• Advocacy is also highly sought (I.e., SET is a GREAT idea!)

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SET Schedule and Plans• Periodic NRAs for data mining/tools• Flight opportunities on roughly a 2-year interval starting in

2004 with SETPath– NRA for first set of SET experiments is due out by early summer– Funds experiment development, but not ground test, test method

development, etc.• Experiments will have to have partnering for this portion

• Carrier development for first full SET mission has begun– The Johns Hopkins University/Applied Physics Laboratory (APL)

and NASA/GSFC are providing core development• Carrier-plus definition has begun

– Partnered effort with the Defense Threat Reduction Agency (DTRA)

– Currently defining requirements and architectural needs unique to sensor/detector technologies

• NASA, DTRA, Aerospace Corp, and APL are the planned prime participants

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Space Environment Testbed Pathfinder(SETPath)

Objective:• Collect data in space on the performance

of categories of microelectronics in the space ionizing radiation environment

• Use the data to flight validate ground test protocols and performance prediction models for microelectronics in the space ionizing radiation environment

Approach:• Fly slightly updated versions of

microelectronics testbed experiments that were designed for the Space Test Research Vehicle 1-d (STRV 1-d) spacecraft

– Data were not taken due to a spacecraft communications failure

• Use partnered secondary access to space– No carrier needed: PROBA II would be carrier

• Results: product improvement & technology infusion performed by protocol & model developers

Candidate Access to Space:PROBA II (ESA) testbed pending successful ESTEC proposal

Launch Vehicle: Ariane V or Indian (ESA-provided)

Predicted Launch Date: May 2004Customers: Spacecraft designers

Authorization to proceed received from NASA HQ on 4/12/02

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SETPath Goals

• Demonstrate SET feasibility & utility for fast access to space

• Provide early opportunity for investigators & early flight data return (2004)- STRV 1-d experiments previously selected by NASA and

BMDO (now MDA)

• Reduce risk & increase reliability for future LWS missions

- Reduce needed design margins to account for uncertainty in the space environment & effects due to solar variability

• Help future missions by validating guidelines & ground test protocols for microelectronic devices in the space radiation environments

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SETPath OverviewSETPath Candidate Experiments:

– Digital COTS with FPGA Add-on– Optocouplers– Linear Enhanced Low Dose Rate Sensitivity (ELDRS)– Linear Single Event Transients (LSET)

Experiment Details• Experiments were selected by a peer team for STRV1-d

- STRV1-d did not return flight data due to a spacecraft communications system failure

- Experimenters have been contacted - Host Spacecraft/Launch: A partnered accommodations opportunity

is being sought for the experiments- A partnered ESA opportunity on the PROBA II spacecraft is being

pursued with NASA as a co-Investigator- Ali Mohammadazadeh and Petteri Niemenen (ESA) are proposal coordinators- Proposal includes CNES, QinetiQ, as well as Belgian and German

representatives- Provides correlative environment data for technology experiments

- Other opportunities being investigated for carrier & experiments as well- Mission goal of 2 years (1 year minimum)- Desired orbit is a geotransfer (GTO)

- Rad hard designs required (100 krad)

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Space Environment Testbed Pathfinder (SETPath) Interface Requirements Concept

NASA SETPath

P/LP/L

P/L P/L

Power

PROBA-Provided Access to Space

PROBA Carrier &Interface Requirements

P/L = Payload

Correlative Environments Measurements

From PROBA-2 Partners

Partnering

Partnered

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Schedule Comparison: STRV-1d & SETPath

ETB TaskFlight Hardware Delivery

Testing

Data Analysis of Testing

ETB Delivery to DERA

Mission Launch

Mission Ends

Q2FY01

Q1Q4Q3Q2FY00

Q1Q4Q3Q2FY99

Q1Q4Q3Q2FY98

Q1

Flight Data Analysis

Q3

STRV-1d Electronics Testbed (ETB) Schedule

SETPath TaskExperiment Delivery

Expt to Carrier I&T

SETPath to Host S/C I&T

Launch Site Support

Mission LaunchOn-Orbit Checkout

Q2FY05

Q1Q4Q3Q2FY04

Q1Q4Q3Q2FY03

Q1Q4Q3Q2FY02

Q1

Mission Data Collection

Q3

Flight Data Analysis

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SETPath:Proposed Architecture for PROBA II

LSET

ELDRS

COTS 2

FPGA

OPTO

PowerSupplies &DistributionUnit (PSDU)

SREM*

RS-422

RS-422

28V

COTS 1

COTS 2

COTS 3

Data

DOSETEMP

Command

PowerPROBA IISpacecraft

*=Space Radiation Effects Monitor

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SETPath Experiments

Experiment Name

Description

Notes

COTS1 - Linear Enhanced Low Dose Rate Sensitivity (ELDRS) and Single Event Transients (LSETS)

?? Collect data in space to validate ELDRS and LSET performance models and test protocols for linear bipolar devices

?? This is a two-card experiment that explores critical radiation-induced issues with basic building block devices used in virtually every NASA and ESA design.

?? In-flight anomalies on missions such as GOES, TDRS, M AP, Cassini, Galileo, and SOHO have been attributed to these radiation-induced events.

?? ELDRS is a complex issue that can not be adequately simulated or modeled via ground irradiation only. MPTB flight experiment demonstrated the existence of this effect, but did not have sufficient correlative environment monitoring to fully interpret the data set.

COTS2 - Digital COTS with FPGA Add-On

?? Collect data in space to validate single event effect (SEE) & total ionizing dose (TID) performance models for:

?? – Commercial fuzzy logic processors;

?? – Static random access memories (SRAM); – Field programmable gate array (FPGA) logic devicesThis is a two-card experiment developed jointly by NASA, CNES, ONERA, and TIMA that explores technology models and environment-tolerant approaches relevant to systems from NASA, ESA, and CNES.

?? Radiation issues associated with these technologies have been noted in-flight. These missions include SOHO, SAMPEX, XTE, HST, TDRS, Cassini, and others. Science data was compromised during solar events in many instances.

COTS3 - Optocouplers

?? Collect data in space to validate single event effect (SEE), total integrated dose (TID), and device displacement damage (DDD) performance models & test protocols for optocouplers

?? - Model is also applicable to high-speed fiber optic links

?? This is a one-card experiment developed by NASA on a common building block for electrical systems throughout NASA and ESA.

?? In-flight anomalies have been observed on HST, TERRA, TOPEX/Poseidon, and IRIDIUM.

?? Displacement damage portion of the experiment, for example, will help validate non-ionizing energy loss models for III-V materials used in spacecraft instruments and in solar cells.

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SETPath Investigations:Map to Space Weather Effects

Novel fault tolerance techniques using fuzzy logic (COTS-2)?Move to on-board autonomy (Mars Rovers)

Digital programmable technologies (COTS-2)?Understand effect of reduction of semiconductor feature and

power supply voltage (all NASA missions)COTS memories (COTS-2)?Understand how to reduce system data loss and increase data

integrity (all NASA Missions)Optical technologies (COTS-3)?Resolve problems with transients (noise) and lifetime

degradation (all flight instruments)Building block technologies (linear bipolar microelectronics) (COTS-1)?Increase system reliability (long-life DoD missions)

Define Space Weather Effects on …

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SETPath Experiments:Investigated Effects and In-Flight

Observations

Radiation

Effect

NASA SET Experiment

Partial list of related In-flight observations

Single event effects (SEEs)

?? COTS1 ?? COTS2 ?? COTS3

?? Data loss: SOHO, XTE, GOES, SOHO, TRACE, ACE, GPS ?? Attitude system anomalies: TERRA, GEO communications, SMM, NOAA, TDRS ?? Operational constraints or errors: HST, MAP, TDRS, QuikSCAT, Cassini, EUVE, DE-1 ?? Increased error rates during particle events: DoD solid state recorders (SSRs), SeaStar,

SOHO, GOES, multiple star trackers, SSRs, and imaging systems ?? System loss: ERS-1

Total ionizing dose (TID)

?? COTS1 ?? COTS2

?? Premature mission failure or compromise: AMPTE/CCE, Hipparcos, Galileo ?? Observation of microelectronics degradation: MPTB

Displacement damage dose (DDD)

?? COTS3

?? Solar cell degradation: SOHO, GEO communication satellites, Japan’s ETS-6, GOES ?? CCD degradation: XMM, Chandra, SOHO ?? Optocoupler failures: TOPEX/Poseidon

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ELDRS in Space:Microelectronics and Photonics TestBed

(MPTB)

This is flight data from the Microelectronics and Photonics TestBed (MPTB) for a linear device. This data illustrates the effect of true space dose rates have when compared with traditional ground test data. The filled in circles represent the actual flight data for a device parameter (IIB) versus cumulative dose received. These data points overlay fairly nicely on the open circles which are a very lose dose rate ground test performed on this device type. The traditional higher dose rate ground tests (the open triangle and the square) show less damage at a given TID than the flight or low dose rate data. Thus, the traditional ground test methods would provide misleading results potentially leading to premature mission failure. Data is courtesy of NASA COTS-1 experiment co-investigators at NAVSEA Crane.

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COTS-1:Linear Single Event Transients (LSET)

Purpose• Collect data in space to validate

single event transient (SET) performance models & test protocols for linear bipolar devices

NASA Benefit• Provide more consistent performance

& lifetime; lower likelihood of LSET anomalies as observed in Cassini, MAP, & TDRSS

NASA Application• Linear bipolar devices are common in

comparators and operational amplifiers -- basic building blocks in all NASA spacecraft & instruments

History• Designed for STRV 1-d; will be built

by Aerospace Corp

Partners• Aerospace Corp., NASA’GSFC,

NAVSEA-Crane, Vanderbilt University, JPL, DoD, Industry, RLP

Leveraging• The NASA Electronics Parts &

Packaging (NEPP) and DTRA supports development of ground radiation tests, protocols, & prediction models

– Ground test protocol will be issued in FY 2002 (Poivey/GSFC)

• Devices provided by industry (NSC, et al?)

Development Path• Modification of existing design (Koga

& Crain/Aerospace Corp) Delivery Date: February 2003Risk of Schedule Slip• Low; based on existing design

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An LSET ( Analog SET – ASET) in Action

Overlayed laser data with simulation –described in a later talk at this symposium

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COTS-1 LSET Products: PreliminarySETPath

Experiment Product(s) Dissemination Methods Product Resources User Impact

Linear Single Event Transient (LSET)

NASA (NEPP) and Defense Threat Reduction Agency (DTRA) are developing guidelines for ground-based test protocols and predictive techniques (FY02/03). Flight data is used to validate these guidelines. Guidelines will be modified based on flight results.

Guideline documents will be available via NEPP (and LWS) websites (<1 year post-launch). Military/industry guidelines are being planned via established test societies (JEDEC, ASTM, SPWG) – 1.5 years post-launch for community agreement. Further dissemination via technical papers at engineering conferences. Guidelines will be referenced in GIDEP (government industry data exchange program) lessons learned document (Agency Action notice) to ensure flight project notification (<1 year post-launch). Concurrent with GIDEP, the data is fed into NASA approved parts list (former Mil-Std-975). Modules for inclusion in industry-standard radiation codes would be expected ~ 2 years post-launch. Data would be available to ESA and international partners for inclusion in ESA guidelines.

Data reduction: LWS NRA NASA Test Guidelines: NASA NEPP Predictive Codes: NASA NEPP, LWS NRA Military Guidelines: DTRA JEDEC Guidelines: NEPP, DTRA GIDEP Notices: NASA NEPAG Other: ESA Websites: LWS, NEPP

Provides knowledge-base to space systems designers, parts and radiation engineers to avoid the types of in-flight anomalies observed on MAP, TDRSS, Cassini, and HST. These types of device are used in every known spacecraft.

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COTS-1:Linear Enhanced Low Dose Rate Sensitivity

(ELDRS)Purpose• Collect data in space to validate

ground test protocols for linear bipolar devices that exhibit ELDRS

- ELDRS is failure at a lower cumulative total ionizing dose in space compared to traditional accelerated ground test dose rates

NASA Benefit• Provide more consistent

performance & lifetimeNASA Application• Linear bipolar devices are common

in comparators and operational amplifiers -- basic building blocks in all NASA spacecraft & instruments

History• Early experiment concept successfully

flown on MPTB by NAVSEA-Crane (SET experiment developer)

Partners• NAVSEA-Crane, Vanderbilt

University, NASA/GSFC, JPL, DoD, Industry, RLP

Leveraging• The NASA Electronic Parts &

Packaging Program (NEPP) delivers a ground test & technology guideline in FY 2002 (Johnston/JPL)• Devices provided by industry

(NSC, et al) Development Path• Modification of existing design by

NAVSEA-Crane (Turflinger, et al) Delivery Date: February 2003Risk of Schedule Slip• Low; based on flight-heritage

design

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COTS-1 ELDRS Products: Preliminary

SETPath Experiment

Product(s) Dissemination Methods Product Resources User Impact

Linear Enhanced Low Dose Rate Sensitivity (ELDRS)

NASA (NEPP) and DoD are developing test methods to evaluate this issue on the ground. Test methods have and are being generated with no flight data. Flight data will be used to determine the accuracy of ground-based accelerated test methods. Products are guidelines for NASA flight projects for testing as well as industry/military standards.

Guideline documents will be available via NEPP and LWS websites (<1.5 year post-launch). Military/industry guidelines via established test societies (JEDEC, ASTM, SPWG) will be validated or modified – 0.5 to 2 years post-launch for community agreement. Further dissemination via technical papers at engineering conferences. Guidelines will be referenced in GIDEP (government industry data exchange program) lessons learned document (Agency Action notice) to ensure flight project notification (<1 year post-launch). Concurrent with GIDEP, the data is fed into NASA approved parts list (former Mil-Std-975). Data would be available to ESA and international partners for inclusion in ESA guidelines.

Data reduction: LWS NRA NASA Test Guidelines: NASA NEPP Military Guidelines: DTRA, NAVSEA JEDEC Guidelines: NEPP, DTRA, NAVSEA GIDEP Notices: NASA NEPAG (NASA EEE Parts Assurance Group) Other: ESA Websites: LWS, NEPP

The ELDRS issue may impact severely the expected lifetime of fielded systems (premature mission failure). By having a validated test protocol on the ground, lifetime reliability will increase significantly (i.e., greatly reduced chance of premature mission failure). These types of device are used in every known spacecraft.

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COTS-2:Digital COTS


single event effect (SEE) & total ionizing dose (TID) performance models for:

– Commercial fuzzy logic processors;– Static random access memories

(SRAM); &– Field programmable gate array

(FPGA) logic devices

NASA Benefit• Reduce design margins &

provide more consistent performance in space

NASA Application• Fuzzy logic: Robotics, docking, &

constellation management applications

• SRAMS: Solid state recorders• FPGAs: Replace custom solutions

Partners• NASA/GSFC, CNES, ONERA, TIMADevelopment Path• Modification to existing STRV 1-d flight

card for PROBA II interface (NASA/GSFC)

Delivery Date: February 2003Risk of Schedule Slip• Low; existing hardwareGround data availability• Heavy ion & proton data in hand

from Orsay, FranceHistory:• Built for STRV 1-d but not flown

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COTS-2:FPGA Technology Concept Validation

Purpose• Collect data in space to validate single

event effect (SEE) and total ionizing dose (TID) performance models & test protocols for COTS and environment-hardened FPGAs

NASA Benefit• Provide more consistent performance

in spacecraft electronics systems.NASA Application• Replace custom solutions in

electronics system design at a fraction of the cost in virtually all NASA spacecraft; save power, weight, volume, & schedule

History• Designed for STRV 1-d by

NASA/GSFC; devices will be updated to state of the art

Partners• NASA/GSFC, DoD, Industry, (is TIMA

interested?)Leveraging• The NASA Electronics Parts &

Packaging Program supports development of ground test protocols, guidelines, & technology development

• Devices provided by DoD & industryDevelopment Path• Existing design (Katz - NASA/GSFC)

with mission-specific modificationsDelivery Date• February 2003Risk of Schedule Slip• Low – existing design with

experienced flight designer

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COTS-2 Products: Preliminary

SETPath Experiment

Product(s) Dissemination Methods

Product Resources

User Impact

Digital COTS with FPGA Add-On

The international collaboration for this experiment (NASA, CNES, et al) provides a wide-base for product development. Reports will be developed comparing and contrasting the fault tolerance techniques, as well as the various differing radiation-induced performances by commercial and hardened options. The data will feed into the development of lessons learned for development of modern digital electronic systems as well as novel fault-tolerant techniques.

Guideline documents will be developed by NASA and partners for reliable technology insertion into flight projects (<1.5 years post-launch). Investigators at NASA and CNES routinely teach classes at their respective organizations on design techniques. This data will be included to ensure improved flight project performance and reliability. All guidelines and documents will be available on NEPP and LWS websites.

Data reduction: LWS NRA Technology Guidelines: NASA NEPP, CNES Websites: LWS, NEPP

Digital designers routinely use the memory and FPGA technologies considered by this experiment. Reliable design methods validated here provide a method of safely reducing cost and schedule to flight projects. Fuzzy logic techniques yield potential direct benefits to robotics (rovers), autonomous docking, etc.

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COTS-3:Optocouplers


single event effect (SEE), total ionizing dose (TID), and device displacement damage (DDD) performance models & test protocols for optocouplers

- Portions of the models may also be applicable to high-speed fiber optic links

NASA Benefit• Reduce design margins &

increase reliability- Anomalies on HST, TERRA, &

TOPEX/Poseidon)NASA Application• Used to isolate electrical signals

between spacecraft sub-systems & instruments; ex., power converters

History• Designed for STRV- 1d by

NASA/GSFC; new optocouplers will be utilized for SETPath

Partners• NASA GSFC, JPL, DoD, IndustryLeveraging• The NASA Electronic Parts &

Packaging Program (NEPP) and DTRA deliver a ground test & technology guideline in FY 2002 (Reed/GSFC)

• Devices provided by industryDevelopment Path• Existing design; mission-specific

interface modifications & newer devices (Buchner – GSFC)

Delivery Date: February 2003Risk of Schedule Slip: Low; based

on an existing designGround data availability• Heavy ion & proton data in hand;

all new ground data to be funded by NEPP

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Optocoupler SETs –Unlike Traditional Si Microelectronics

Proton ionizationtracks or reactionrecoils generatecharge in detectors.

p+

Lmax

i

i0

i1

ith

This “0” maybe corrupted

“1” is notcorrupted

This “0” iscorrupted

TimeDecision Points

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COTS-3 Optocoupler Products:Preliminary

SETPath Experiment

Product(s) Dissemination Methods Product Resources User Impact

Optocouplers NASA (NEPP) and DTRA have partnered to develop models for radiation effects on optocouplers as well as test methods and predictive techniques. This is a new method not traditionally used with “standard” integrated circuits. A first method for bounding the issue based on no flight data (order of magnitude) will be released in FY02. This precision may limit science instrument and spacecraft subsystem operation capabilities and lifetimes. Flight data will validate or provide critical input to reduce design margins in this method.

Guideline documents will be available via NEPP (and LWS) websites (<1 year post-launch). Further dissemination via technical papers at engineering conferences. Guidelines will be referenced in GIDEP (government industry data exchange program) lessons learned document (Agency Action notice) to ensure flight project notification (<1 year post-launch). Concurrent with GIDEP, the data is fed into NASA approved parts list (former Mil-Std-975). Data would be available to ESA and international partners for inclusion in ESA guidelines.

Data reduction: LWS NRA NASA Test and Technology Guidelines: NASA NEPP Predictive Codes: NASA NEPP, LWS NRA Military Guidelines: DTRA JEDEC Guidelines: NEPP, DTRA GIDEP Notices: NASA NEPAG Other: ESA Websites: LWS, NEPP

Provides knowledge-base to space systems designers, parts and radiation engineers to avoid the types of in-flight anomalies observed on HST, Cassini, and Terra (and Iridium). These types of device are used in virtually every known spacecraft.

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General SETPathExperiment Specifications

• With the exception of the existing COTS-2 card, all SETPath experiment cards will have the following general characteristics:– Conform to Eurocard 3U form factor (10cmx16cm)– Weigh ~250g when populated– Draw between 2.5 W (LSET, FPGA, Optocoupler) and 4 W (ELDRS) when

active• Mission power profile dictates that no more than 5W of power be

drawn from SETPath experiments at one time• SEE experiments will alternate orbits

– ELDRS will be biased (< 500 mW) during all other SETPathexperiment active times, then read 1X per orbit

– Have a ESAPMOS4 dosimeter and AD590 temperature sensor• Read by SREM from each SETPath experiment

– Cumulative data rate of SETPath experiments of 50 bits/sec maximum• Electrical interface is ESA standard: TTC-B-01

– PROBA II will have panel cutouts for experiment cards

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SETPath Power ProfilePreliminary

Experiment +5V -5V +15V -15V +3.3V +28V Power in WLSET 0.1 0.087 0.048 2.525Optocoupler 0.41 0.015 0.015 2.5ELDRS 0.11 0.02 0.1 0.1 0.15 4.145Digital COTS 0.075 0.006 0.465FPGA 0.15 0.55 2.565

Total Icc in A 0.845 0.02 0.208 0.163 0.7 0 12.2

• Experiments will be power-switched due to operational constraints (5W)

• The voltages listed above are those that are being planned for support by the full SET Carrier (non-SETPath)– We are considering providing only a subset for SETPath

• + 5V, +/- 15V

• PSDU will be 2 cards (Eurocard 3U) and weigh ~500g– Shielding may be required to meet 100 krad design goal

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SETPathRoles & Responsibilities

• Mission Management: GSFC LWS• Experiments: GSFC (in-house build),

NAVSEA/CRANE, and Aerospace Corporation• Carrier (I.e., PSDU): APL build • Experiment-to-carrier integration & test: At GSFC

jointly with APL & experimenter support• SETPath-to-Host Spacecraft Integration and test:

At Host Spacecraft provider with APL & GSFC support

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SETPathSummary Comments

• Experiments were peer selected using a community consensus– Experimenters were contacted & are ready to proceed

• Carrier conceptual design has been started at APL– Modular design approach permits it to be used for SETPath (if needed) and/or

SET-1

• Host spacecraft has been identified & preliminary discussions are underway (PROBA II)– 1st proposal due April 29th, 2002– Alternatives exist and under investigation

• GSFC LWS Mission manager has been assigned (Ken LaBel)– SETPath units will be treated in the same manner as Shuttle experiments;

limited formal review requirements

• Detailed schedule has been developed • SETPath will return critical flight data to reduce the risk & cost of

future LWS & other NASA missions

http://lws-set.gsfc.nasa.gov

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ACRONYMS

AO Announcement of OpportunityAPL Applied Physics LaboratoryB/L BaselineCDR Critical Design ReviewCME Coronal Mass EjectionCSOC Consolidated Space Operations

ContractD/L DownlinkDTRA Defense Threat Reduction Agency ELV Expendable Launch VehicleEPO Education and Public OutreachEUV Extreme UltravioletFSS Farside SentinelGMDT Geospace Mission Definition TeamIHS Inner Heliospheric SentinelsIM Ionospheric MappersIMDC Integrated Mission Design CenterISAL Instrument Synthesis and Analysis

LaboratoryKSC Kennedy Space CenterLaRC Langley Research CenterLCC Life Cycle CostLV Launch VehiclesLWS Living With a Star

MCR Mission Confirmation ReviewMO&DA Mission Operations and Data AnalysisNBC New Business CommitteeNRA NASA Research AnnouncementNSREC Nuclear and Space Radiation Effects ConferencePDR Preliminary Design ReviewPFM Project Formulation ManagerP/Y Pitch/YawRAO Resource Analysis OfficeRBM Radiation Belt MappersRSDO Rapid Spacecraft Development OfficeRY Real YearSAT Science Architecture TeamS/C SpacecraftSDO Solar Dynamics ObservatorySDT Science Definition TeamSEC Sun-Earth ConnectionSECAS Sun-Earth Connection Advisory

SubcommitteeSERB Space Experiments Review BoardSET Space Environment TestbedSOHO Solar Heliospheric ObservatorySTRV Space Technology Research VehicleSTP Space Test ProgramTMDA Theory/Modeling & Data AnalysisUSEF Unmanned Space Experiment Free Flyer

NASA’s SETPath Mission: Living With a Star (LWS) Space Environment … · 2002-08-01 · Materials • Spacecraft Charging/Discharging Perform applications research on environment

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