Solar Terrestrial Probes

Space Environment Testbeds Carrier System Cover Page Living with a Star (LWS) Program

Sun Earth Connection SEC Advisory (SEC) Science Theme Subcommittee (SECAS)

LWS Program

Science Theory & Space Missions Modeling Environment Testbeds (SET) Solar Dynamics Partners Observatory Yearly (SDO) Research Opportunities SET-1 Radiation Mappers SET-2 Ionospheric Mappers Defines environment in the absence of the SET-3 Solar Sentinels spacecraft Partners Defines environment Performs basic science interaction with investigations to achieve spacecraft B.Patschke 2 understanding Small Satellite Conference Logan Utah LWS Overview Human Radiation Exposure

- Space Station Living with a Star (LWS) - Space Exploration Program Science Research - High Altitude Flight to Reduce - Space Utilization & Impacts of Solar Variability Colonization

Impacts on Technology Impacts on Life & Society

- Space Systems - Global Climate Change - Communication & Navigation - Surface Warming - Ground Systems - Ozone Depletion & Recovery

B.Patschke 3 Small Satellite Conference Logan Utah Introduction – (What is SET?)

• One of three three elements that comprise LWS • Science Missions • Theory and Modeling

Space Environment Testbeds (SET) Project. To improve the engineering approach to accommodate and/or mitigate the effects of solar variability on observatory/spacecraft design and operations so that new technologies can be infused to space missions without adding risk.

The SET Project is comprised of two key components • Flight Investigations. A series of technology validation and data gathering missions, each mission consisting of a compliment of science investigations/experiments from scientists and technologists, that will be implemented as a piggyback or secondary payload and flown on a host spacecraft. • Data Investigations. The analysis of data from past and present space missions for scientific analysis, theory, and improvement of engineering environment models, tools, and databases for reliable spacecraft design and operation.

B.Patschke 4 Small Satellite Conference Logan Utah Space Environment Testbeds (SET) Project

Goal

Improve the capability to accommodate or mitigate the effects of solar variability on spacecraft and instrument design and operations

Need to replace empirical models of space environment effects Microelectronics, Detectors, Materials, with physics-based models Spacecraft Charging/Discharging

B.Patschke 5 Small Satellite Conference Logan Utah SET Mission Concept

• SET missions will be manifested as secondary or piggyback payload on a host spacecraft.

• SET requires power, command, and a telemetry interface from a host spacecraft.

• Carrier architecture is standard, and scaleable for flight investigations (experiments), but flexible and customizable for host spacecraft interfaces.

• Carrier experiment accommodations will support 3U (100mm x 160mm), 6U (223mm x 160mm) cards, and/or separate box experiments.

• Mission unique command/telemetry configurations are configured through on-board table driven command sequences. Not a real time system.

• SET science operations are typically between 1-2 years, missions once every 2 years

• Flight investigation funding ~$250K per experiment.

B.Patschke 6 Small Satellite Conference Logan Utah SET Mission Approach

• Collect a number of flight-ready experiments designed to support pertinent science investigations – (NASA Research Announcements) NRA – Partnerships – Previously peer reviewed experiments (SETpath experiments) • Design carrier avionics to act as an intermediary between experiments and a TBD host spacecraft. The carrier provides: – Standardized interface to flight experiments – Generic, but adaptable interface to a host spacecraft • Acquire a launch and limited services from a spacecraft that offers excess mass, power, and data capability (a ‘ride’) – Currently negotiating our first SET mission launch opportunity with New Millennium Program, Space Technology 8 (ST8) Mission.

B.Patschke 7 Small Satellite Conference Logan Utah SET Carrier Concept • Provide mechanical, electrical, & thermal interfaces for a collection of small flight investigation experiments with a host spacecraft.

• A standard experiment interface • Standard interface that allows experiments to be developed independent of a particular spacecraft interface. SET Experiment Accommodations and Requirements Specification (SEARS) Document • Standard power, data, command/telemetry formats, mechanical, thermal services. • A customizable host spacecraft interface. • Flexible design to accommodate likely host spacecraft. • Modular and scalable to adapt to the resource budgets and accommodations provided for a particular flight opportunity.

Exp 1 Exp I/ Power Exp 2 Host Spacecraft Cmd/Tlm Host SET F Monitor I/F Carrier Exp n

Custom Interface Standard/Fixed Interface

B.Patschke 8 Small Satellite Conference Logan Utah Correlative Environment Monitor (CEM)

• Every SET mission will include one or more Correlative Environment Monitors (CEM) as part of the payload complement.

• CEM’s are the primary mission space environment detectors for the detailed measurement of the on-orbit radiation environment.

• The CEM’s selected for each payload complement will be tailored to provide the environment measurements required to validate the exposure of the payload to the space environment.

B.Patschke 9 Small Satellite Conference Logan Utah End-to-End System Block Diagram, Data Flow & Architecture Mission Ground Data System Elements Mission Flight Elements PI GSFC Facilities SET POCC SET Payload SET Data SET Delivery Archive Host System Experiment-1

SET Experiment-2 Local Data Host Processing Storage ITOS Host S/C SET SOCC T CARRIER Experiment-N SE

Mission Mission CEM Planning Planning

Sustaining Mission Network Interface Engineering Planning Laboratory (SEL) Experimenter Element SET Project Element

r tor e a rri

P ETU ITOS Host S/C Element ETU or Sim Ca EX Host S/C Simul *In the event of concurrent missions the architecture will be duplicated for each mission.

B.Patschke 10 Small Satellite Conference Logan Utah Carrier Configuration

CCA = Central Carrier Assembly

Experiments underneath 10 mil aluminum cover

Command/Telemetry Input from Host Carrier Power Input from Host Carrier Power Output to Other RCAs SET Carrier Command/Telemetry Mechanical View to other RCAs Horizontal Configuration

B.Patschke 11 Small Satellite Conference Logan Utah Carrier Architecture System Block Diagram Box CCA = Central Carrier Assembly FFS Experiment 3U CEM = Correlative Environment Monitor 3U 3U CST = Carrier Status Telemetry 3U FFS = Filter, Fusing, and Switch Card Board

PCC = Power Control Card PCC Back Plane Experiment RCA = Remote Carrier Assembly RCA

Box +28VDC FFS Experiment S/C FFS CEM 3U 6U CNTRL 3U 3U 3U 3U Host CMD/TLM 3U Board uPC Board Experiment

S/C CST Back Plane Experiment PCC CST Back Plane RCA PCC CCA

Host Spacecraft Carrier Subassemblies FFS Carrier Power = 10W Carrier Cards 6U Min, 120W max 3U Experiment Hardware 3U Carrier Mass = 8Kg, Board Experiment

40Kg Max. Back Plane Data Rate = 1 Nominal - PCC 4Kbps Max. RCA B.Patschke 12 Small Satellite Conference Logan Utah Carrier to Experiment Capabilities

Mechanical: Thermal: Card Experiments: 0.45 kilograms Card Thermal Interface Experiment thermally Box Experiments: 10.0 kilograms conducted to carrier. Box Thermal Interface Experiment either Power: isolated or conducted to Card Peak Power: 4.0 Watts carrier/spacecraft. Box Peak Power: 10.0 Watts

Power Services: Switched Unregulated Services +28 (+/-6VDC) Other Services: Switched Regulated Services 8 MHz Clock 1 Service Digital Power Services +3.3 Volts Bi-Level Control 2 Services +5.0 Volts (standby, reset) Experiment Analog Two 0-5 Volt monitors Analog Power Services +/- 5.0 Volts Experiment Thermistor 1 Service +/- 15.0 Volts Experiment Dosimeter 1 Service

Command and Data Handling: Experiment Data Storage Up to 500 Kbytes.

Data Interface EIA RS-422 Max Telemetry Rate 1 Kbits/second

B.Patschke 13 Small Satellite Conference Logan Utah Electrical System- Fixed and Standard Carrier to Experiment Interface Experiment electrical interfaces are via a standard 80 pin connector within the CCA/RCA enclosures. Services include power, serial command and telemetry, and various analog services and are defined in the SET Experiment Accommodations and Requirements Specification (SEARS) Document (includes suggested circuit implementation at the interface).

+28VDC (Unregulated) +3.3 VDC Digital (Regulated) +5 VDC Digital (Regulated) +/-5VDC Analog (Regulated) +/-15VDC Analog (Regulated) SET RS-422 CMD/TLM SET Carrier Experiment Avionics 8 MHz Clock Bi-Level Reset (5V) Bi-Level Standby (5V) Analog (-5 to +5V Monitors) x2 Temperature Monitor RADFET Monitor

B.Patschke 14 Small Satellite Conference Logan Utah Mechanical System • The carrier housing consists of an aluminum 6061-T6 machined enclosure with covers/lids for the carrier backplane, and experiment bays. Enclosure may support 3U cards, with slot 3/4 able to accommodate a 6U card. • Board experiments are mounted on the top, while carrier system cards are mounted underneath. Experiment boards are mechanically supported along the edge with several fasteners, and each bay is machined to provide a Faraday cage to reduce the propagations of Electromagnetic Interference (EMI). 10 mil lids cover the experiment cards.

• Orientation of the enclosure on the host spacecraft can be either vertical or horizontal to minimize the mounting footprint requirements, increasing the potential for accommodations when surface space on a host is restricted.

B.Patschke 15 Small Satellite Conference Logan Utah Mechanical Views – Cross Section, Experiment Envelope Experiment Card

BOTTOM SIDE

Carrier Boards Envelope

Carrier Enclosure

B.Patschke 16 Small Satellite Conference Logan Utah Mechanical Views – Carrier Components and Experiment Assembly

B.Patschke 17 Small Satellite Conference Logan Utah Electrical System- Generic Host Spacecraft to Carrier Interface

SET carrier to host electrical interface design is flexible to meet typical host spacecraft interfaces, but can be tailored to meet specific host requirements, by developing a separate 3U host interface card. The generic carrier to host interface supports a redundant 28V +/- 6V input power, bi-level control, RS-422 serial data interface, and Carrier Status Telemetry (CST) lines.

+28VDC Primary & Heater Power (A&B)

SET RS-422 CMD/TLM Host Carrier Avionics Spacecraft Bi-Levels (0-10VDC)

Housekeeping Telemetry (CST)

B.Patschke 18 Small Satellite Conference Logan Utah Host SET Configuration – Block Diagram S/C to Carrier Interface Candidate Payload Complement with 1 CCA and 1 RCA (9 experiments)

+28VDC Power Primary & Heater Power RS-422 CEM +28VDC Filter, Power Experiment 1 Fusing uProcessor & Switch Card Command Back & Telemetry Experiment 2 RS-422 plane CCA Power Experiment 3 Control S/C Real Card Time Monitors Experiment 4 Carrier Status Telemetry (CST)

+28VDC Power Box RS-422 Primary & Heater Power Experiment Filter, Fusing Experiment 5 & Switch Back plane Power RCA Control Experiment 6 Card Experiment 7

To additional RCA’s B.Patschke 19 Small Satellite Conference Logan Utah CCA/RCA Representative Power Distribution

Host Host S/C Backplane S/C Control Power Control Control Card (PCC)

+28V Primary Carrier +28V 3.3VD Power from Power DC/DC CCA 5A FET

5V +28V D FET DC/DC Primary Heater Power In Power From CCA 5A FET +/-5VA DC/DC Filter Card

Host S/C +/-15VA Control DC/DC

To +28V Subsequent 6.25W Strip Heaters (2) T-Stats RCA’s

Experiment 3.3VD (x4) Experiment 5V (x4) CCA/RCA Power Distribution D Experiment +/-5VA (x4) Max Power Carrier + Experiments = 30W Experiment +/-15VA (x4) Experiment +28V (x4) 1 Amp

B.Patschke 20 Small Satellite Conference Logan Utah

n o i t u b i r t s Di a t Da 2 2 4 RS- r e i r r Ca SET

SET Carrier RS-422 Data Distribution

There are ten RS422s available from the processor card FIFO 5 Meg Digital • 1 for generic carrier interface to host spacecraft Storage • 8 RS-422s for PCCs (assuming 4 PCCs – max (Conceptual Only) capability)

RS-422 One to each PCC housekeeping telemetry. One to each PCC for the muxed RS-422 experiment streams (split into 4 RS-422 uProcessor PCC in CCA RS-422 RS-422 within each PCC so each experiment has RS-422 Exp 1-4 Mux RS-422 RS-422) RS-422 Select mux to experiments by

RS-422 communicating to PCC PCC in RCA #1 RS-422 • One spare for potential future storage RS-422 RS-422 Exp 5-8 Mux RS-422 RS-422

RS-422 RS-422 40ms time slots (25 Total)

C P

PCC in RCA #2 -

Generic RS-422 R

A RS-422 A

C Carrier C

RS-422 C

Exp 9-12 C

P RS-422 P

–

- To Host Mux -

RS-422

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5 e

i 1 e

M r

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r p RS-422 r

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C PCC in RCA #3 C RS-422 RS-422 RS-422 Exp 13-14 Mux 1 sec

Number of Experiment = 25 - (3 CCA uP + 2 PCC) – (2 RCA1 PCC) – (2 RCA2 PCC) – (2 RCA3 PCC) Timeslots

B.Patschke 21 Small Satellite Conference Logan Utah SET Flight Software

• The carrier embedded flight software is resident on UTMC UT80196KDS.

• Flight Software provides a Consultative Committee on Space Data Systems (CCSDS) compliant telemetry, a command interface with the host spacecraft, and a Time Data Multiplexed experiment serial interface.

• Experiments provide predefined Command Sequences that issue experiment science or power mode change commands and request telemetry.

• The experiment data that is returned to the SET Flight Software is packetized and queued for output to the host spacecraft.

• Command Sequences can be configured to 1) execute at periodic intervals (up to a 1 Hz frequency), 2) execute in chained sequences, and 3) be preemptive and execute when environment monitors detect specific radiation levels or experiment safety parameters exceed specified limits.

• These features allow the experimenter the ability to obtain, format and respond to science data without implementing their own microprocessor and its associated code within their experiment.

B.Patschke 22 Small Satellite Conference Logan Utah Carrier Mode of Operation Flowchart

Boot mode is a predefined Safe Mode is a predefined, state that initializes the minimum power configuration in carrier by loading flight which power to experiments is software from non-volatile removed and carrier functionality Low Power memory, and resetting all is minimized. The carrier parameters to default values, maintains minimal, but sufficient and performing built-in capability to communicate with carrier health tests. After the spacecraft, and carrier Boot Safe initialization, the carrier watchdog diagnostics. nominally transitions to Safe Mode.

Maintenance Operation

Maintenance mode is Operations Mode is the only dedicated for patching or mode where experiments are SW Load & loading FSW from the Normal Operation powered, active in science ground, and for Diagnostics data collection, and providing performing carrier system science telemetry to the diagnostics. carrier.

B.Patschke 23 Small Satellite Conference Logan Utah Parts Engineering

• The carrier flight electronics is comprised of EEE, Grade 3 parts that meet radiation requirements of 100 Krads-si for Total Dose, 37 MeVcm2/mg for single event effect (SEE) soft errors and 80 MeVcm2/mg for SEE hard errors. Exceptions are evaluated on a case-by-case basis.

• SET investigations/experiments are required to select EEE parts that will ensure their mission success (i.e., design will function in space long enough to gather enough data to meet mission success objectives). The use of plastic, commercial devices is prohibited, unless approved by SET Project.

• Specific launch/orbit information may be unknown at the time of experiment development; therefore, to optimize launch opportunities, experimenters are encouraged to use parts selection guidelines similar to the Carrier. The total dose requirement could be less than 100Krads-si if mission success objectives can be achieved by collecting data in a relatively short period (a few months vs. 2 years) or other mitigation steps are incorporated into the design.

B.Patschke 24 Small Satellite Conference Logan Utah System Development & Test

• Breadboard and Engineering Test Unit (ETU) (November 2003 – December 2004) • Filter, Fusing, & Switching Card, Processor Card, Power Control Card Breadboard Cards • Backplane and mechanical enclosure ETU. • Integrating with EGSE and perform functional and performance tests – card level design verification, environmental testing (EMI, vibration, thermal cycling) • FSW acceptance testing

FSW Testing EGSE Development

Power Control Card Breadboard (Top) uProcessor Card Breadboard (Top)

Power Control Card Breadboard (Bottom) uProcessor Card Breadboard (Bottom)

SET Development Laboratory B.Patschke 25 Small Satellite Conference Logan Utah Mechanical View – CCA with Covers Removed

Single CCA Horizontal Configuration with 10 mil covers removed

B.Patschke 26 Small Satellite Conference Logan Utah Mechanical View - Horizontal Configuration

Single CCA Horizontal Configuration (10 mil covers & external box I/F)

B.Patschke 27 Small Satellite Conference Logan Utah Mechanical View – Vertical Configuration

Single CCA Vertical Configuration

B.Patschke 28 Small Satellite Conference Logan Utah Mechanical View Vertical

SET Carrier Vertical Mechanical Configurations

Single CCA Vertical CCA & RCA Vertical Configuration Configuration

B.Patschke 29 Small Satellite Conference Logan Utah Mechanical Views – Candidate Carrier Configurations for Sensors and Detectors

B.Patschke 30 Small Satellite Conference Logan Utah Summary

•The Living With a Star (LWS) Program has developed a low-cost experiment carrier called the Space Environment Testbeds (SET). The SET carrier will provide applied science and engineering investigators quick access to space to reduce the risk associated with flying new technologies.

•SET project has an infrastructure in place to fund, build, test, deliver and fly multiple investigations on any host spacecraft. The project infrastructure is well defined and structured and close to the implementation phase, with key documents ready for baselining and PDR and confirmation scheduled for this fall.

• The one challenge SET faces is the availability of spacecraft rides.

B.Patschke 31 Small Satellite Conference Logan Utah Acknowledgements

Steve Aloezos - GSFC Zoran Kahric – QSS Scott Appelbaum – Omitron John Kazeva – Swales Chikia Barnes – SGT Mike Kelly – GSFC Janet Barth – GSFC Dave Kobe – Hammers Neal Barthelme – GSFC Ken Label – GSFC Katie Barthelme – Omitron Barbara Milner – GSFC Mary Boloori - OSC Greg Martins - GSFC Richard Bolt - GSFC Carolyn Mariano – GSFC Dana Brewer – NASA HQ Lisa Mryrnsa - Swales Joe Cerullo – ARSC Veronica Otero – Swales Anthony Comberiate - Hammers Joe Peden - SAIC Mike Cuviello – QSS Randy Pensabene – OSC Barbara Davis – Swales Karen Pham – GSFC Mary DiJoesph - GSFC Jim Ritter - SAIC Tom Dixon – GSFC Susan Ritter – QSS Carolyn Ellenes - GSFC Eve Rothenberg - GSFC Angie Evans - GSFC Matthew Samuel - MEI Larry Frank - APL Barry Sherman – GSFC Evan Goldstein – Swales Brian Smith – Stargazer Mike Golob - Swales Geoff Sobering Joe Green - Swales Valerie St. John - Hammers Greg Greer - Hammers Ed Stevens – GSFC Fred Gross – Swales Nick Teti – Swales Doug Hawk – Swales Carroll Trickey - OSC Pat Hennessy - GSFC Michelle Turchet - OSC John Hoge - QSS Hung Tran – MEI Jim Howard – J&T Mike Urban - GSFC Regan Howard – OSC Dave Vavra - Hammers Terry James – Honeywell Luan Vo - QSS Don Jarosz – Swales Dennis Wicks – CSC Shirley Jones - OSC Robert Williams - APL Carl Wu – Hammers B.Patschke 32 Small Satellite Conference Logan Utah