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In-Situ Resource Analyzer (ISRA)

In-Situ Resource Analyzer (ISRA). ISRA is a combined XRF/XRD/Imaging Instrument for Lunar Applications XRF: X-ray Fluorescence XRD: X-Ray Diffraction MI: Microscopic Imager ISRA is a Lunar Mission variant of the MICA (Mineral Identification & Composition Analyzer) Instrument

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In-Situ Resource Analyzer (ISRA)

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  1. In-Situ Resource Analyzer (ISRA) • ISRA is a combined XRF/XRD/Imaging Instrument for Lunar Applications • XRF: X-ray Fluorescence • XRD: X-Ray Diffraction • MI: Microscopic Imager • ISRA is a Lunar Mission variant of the MICA (Mineral Identification & Composition Analyzer) Instrument • MICA was originally developed for application at MARS via the Mars InstrumentDevelopment Program (MIDP) • INSTRUMENT “KEY FEATURES” • NO SAMPLE PREPERATION IS REQUIRED --A capability unique to this instrumentXRD/XRF/Imaging all available in a single device • Instrument is useful in a variety of modes and scenarios – For example, canfunction as a Deck Mounted Instrument, or on a Lander/Rover Arm • Low mass with small footprint. Minimal Mass/Volume Impact on Lander/Rover. I made some minor changes to reduce the wording.

  2. In-Situ Resource Analyzer (ISRA) ISRA/MICA Sensor Head Cross Section ISRA Origins • Developed originally for Mars (MIDP) Ideal for lunar environment • TRL --Brassboard/Flight prototype • MIDP goals were to demonstrate functionality of miniature compositional analyzer that could rapidly provide data relevant to resource evaluation, geology and astrobiology Task Leaders Science Direction: Dr. John Marshall SETI institute Technical Manager: Dr. Joe Martin N-Science X-ray Source: Jianping Lu /Xintec FPGA Board: Chris Hodge/Broadreach Engineering Data processing: Larry Mason /N-Science XRD analysis: Don Williamson /Colo School of Mines Electronics: John Waring /N-Science Electrical: Geoff Campbell /N-Science Mechanical: Ludwig Wolfert /N-Science Camera: Dan Scheld /N-Science Thermal: Dan Ladner /N-Science Packaging: Pat Thompson/N-Science

  3. Status ISRA / MICA • Instrument Status • MICA K-9 ROVER TESTING was Complete in Sept of 06 • Instrument Now Resides in Development Lab at LMA Denver • Undergoing some troubleshooting as time and Internal funds permit ISRA Predecessor, MICA in test at AMES (pictured Dr. Joe Martin, N-Science Program Mgr, MICA/ISRA PI, Dr. John Marshall & N-Science Engineer, Patrick Thompson) MICA Up-close & Personal With Mars “rock” at AMES

  4. ISRA – Mission Science • ISRA properly positioned on Lunar Lander Deck will examine upper surface soils deposited on Instrument surface during Landing • No “Deployment” required in this application

  5. ISRA – Mission Science KEY ISRA Mission Science Features • This Mission provides a unique opportunity to Sample and Analyze the Top-Most Layers of the Lunar Regolith • Sample Material will be deposited on the ISRA Analysis Station through Entrainment by Retro Thruster Plume • The Upper Layers of Regolith Fines is the Feedstock Material are Targeted for Lunar Oxygen Production using an In-Situ Resource Utilization (ISRU) Process • ISRU Oxygen production supports Lunar Base for Breathing Gas and Propellant Oxidizer • ISRA analyses are highly effective on samples containing small particles • ISRA will Analyze Lunar Material in several ways • X-Ray Fluorescence (XRF) to determine the Elemental Composition • X-Ray Diffraction (XRD) to determine Mineral Content and Grain Size Information • Microscopic Imager (MI) to provide Visual Context of sample and data on Particle Size Distribution

  6. ISRA – Mission Science ISRA Instrument Features – This Application • Single ISRA Data Analysis Packet: Approx 4.1 Mbyte Visual Image Data: Approx 2.5 Mbyte X-ray Analysis Data: Approx 1.5 Mbyte Instrument Header Data: Approx 0.1 Mbyte (Note: Data can be further compressed if necessary) • ISRA Instrument Parameters MASS: Approx 2.0 kg POWER: Avg 10 Watts for duration of analysis to power x-ray tube/electronics ANALYSIS TIME: 20-90 minutes (depending on requirements) ** **Notes: 1) Experiment time-line includes visual image acquisition, sensor cool-down, x-ray data acquisition, and data packet generation. 2) Assumed MICA design changes to adapt from Mars to lunar environment. For example, the Thermal Electric Cooler (TEC) and associated power supply have been eliminated; CCD cooling for single analysis will be provided via LN2 from a small dewar) • Budget (ROM) • Assumes a 30 month program, provides Qual and Flight Units YR 1 ($2.5 M), YR 2 ($1.5), YR 3 ($0.7)

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