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Solar Terrestrial Probes NASA Goddard Space Flight Center Flight Space Goddard - NASA Goddard Space Flight Center Flight Space Goddard - 1673 - 286 - 301 X: FA 1673 - 286 - 301 X: FA 6092 - 286 - 301 Telephone: 6092 - 286 - 301 Telephone: . nasa @ ke Patsch Robert. gov . nasa @ ke Patsch Robert. gov eer Engin stems Sy SET eer Engin stems Sy SET Patschke W. Robert Patschke W. Robert Logan Utah – Utah Logan ugust 11, 2004 11, ugust A Utah State University State Utah Small Satellite Conference Satellite Small Carrier System Carrier Carrier System Carrier Space Environment Environment Space Testbeds (SET) (SET) Space Environment Environment Space Testbeds (SET) (SET) 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 © 1998 Geoff Sobering 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
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