NASA Ames Instrumentation Workshop May 13, 2010

1. Please select the applicable readiness level: Readiness level: • Demonstrated/Existing • ☐ In Development/Mature • ☐ Planned (Future) Readiness level: ☐ Demonstrated/Existing In Development/Mature ☐ Planned (Future) Readiness level: ☐ Demonstrated/Existing ☐ In Development/Mature  Planned (Future) Title of Presentation goes here NASA Ames Instrumentation Workshop May 13, 2010 Images go here • Description goes here • Format. Please use the format provided here. Use bullet points to include details such as: • wavelengths covered, resolution of images, sensitivity and applications of instrument • Challenges to development, e.g. have no clean room available, calibration required • References in the literature, and • Work that would be good to get from the Ames community (e.g. software development) Technology / Application • Name/division/phone/email of Point of Contact(s) e.g. • POC: James Bond, Code SSX • email: j.bond@mi5.gov.uk • phone: +44 007 007 007 • Put proposal history of instrument here. Use this format: • 2006 Idea conception 2007 Proposed to MIDP • Feb 2008 First prototype built • Future work (e.g. next proposal) Funding / Timeline POC

2. Ground Penetrating Radar for Water Detection on Mars (GPRWDM) Readiness level: ☐ Demonstrated/Existing In Development/Mature ☐ Planned (Future) NASA Ames Instrumentation Workshop May 13, 2010 (Fake Example) • Requirement. A requirement exists to detect the presence of water beneath the surface • of Mars on a Rover. We have built a prototype Ground Penetrating Radar to achieve thistask and we hope to have the instrument on the MAX-C Rover, to be launched in 2018 toMars. • The current instrument has been in development for 2 years, and has the followingcharacteristics: • operates at 2GHz • Requires little user intervention • Has a battery life of 2 hours • Can detect water rich layers down to 12m. Technical Readiness. We asses this instrument to be at Techincal Readiness Level 3because the instrument prototype has been built and is operating. • Ames Resources Used. We had the instrument manufactured in the tool shop at N245and conducted calibration in the cool room in building N244. • Challenges to development. We have tried without success to find a developer todesign and build a user inteface to control the GPRWDM instrument. We are still actively looking for support in this area. • If we were able to find scientists at Ames interested in water on Mars to help during field testing next year then this will allow the instrument to reach higher readiness, perhaps even TRL 4.References in the literature. Two papers have been pulished on this instrument: • Bond et al., 2009, ‘GPRWDM Instrument for the MAX-C Rover’ Mars 5, 195 • Bond et al., 2010, ‘Ground Penetrating Radar in White Sands Dune Environment’ Icarus 205, 1976. Technology / Application • 2006 Idea conception 2007 Proposed to MIDP • Feb 2008 First prototype built • Planning to test the instrument in the field at DESERT RATS in 2011 when it Will be integrated on the FIDO rover and interfaced with software for the firsttime • POC: James Bond, Code SSX • email: james.bond@nasa.gov • phone: +44 007 007 007 Funding / Timeline POC

3. Readiness level: • Demonstrated/Existing • ☐ In Development/Mature • ☐ Planned (Future) Infrared Detectors for Space-based Astronomy (Real Example) NASA Ames Instrumentation Workshop May 13, 2010 Images go here Application: Focal planes for mid-IR (5 to 28 microns) cameras andspectrometers for low-background space-based applications, and for near-ir and far-ir imagers. Customer: JDEM,MIRI for JWST, WISE, EXES, possibilities of ASPIRE,SPICA. Technology: 1kx1k and 2kx2k planar hybrid (bump-bonded) sensor chipassemblies with 25 micron pixel pitch for deep-cryo operation at low background flux. ARC role/activities/products: In-house characterization of noiseand responsivity, combined with radiation testing at the UCD cyclotron. Screening Of parts, optimization of clocking, iteration with manufacturer to improve future lots. Technical Challenges: Very low background photon flux at thermal wavelengths, noise measurements in the electrons range, characterize peculiarities In read-out functionality, nonlinear effects, latencies and time constants. Level of success: Highly successful, demonstrated space flight requirements for array performance Technology / Application Test dewar at the UC Davis Cyclotron for Radiation testing for space flight. • POC: Robert McMurray, Code RE • email: robert.mcmurray@nasa.gov • phone: (650) 604-3179 Testing of silicon detectors since 1980s. Radiation testing since 1989. Delivery of flight parts to Spitzer 1999 Tests for MIRI and Wise 2008-9 Currently testing detectors for JDEM Funding / Timeline POC