Summary

Description

By examining the occurrence rates and types of actual on-orbit failures, a failure servicing industry can be projected. Similarly, by examining the lifetimes of working or recently retired spacecraft, a lifetime extension servicing market can be characterized. By examining actual historic servicing opportunities and combining this information with consideration of operational uncertainties, it is possible to define a set of servicers that range from low to high in mass, required servicing capability, lifetime risk to the serviced spacecraft, and potential economic return. This knowledge in turn will show how a set of increasingly capable servicers can establish an economically viable on-orbit telerobotic satellite servicing industry. Development of servicer design requirements will serve to identify key technologies. The applicability of these commercial capabilities to Exploration related assets and missions will also be examined.

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The proposed work extends Probability Bounds Analysis to model epistemic and aleatory uncertainty during early design of engineered systems in an Integrated Concurrent Engineering environment. This method uses efficient analytic and semi-analytic calculations, is more rigorous than probabilistic Monte Carlo simulation, and provides comprehensive and (often) best possible bounds on mission-level risk as a function of uncertainty in each parameter. Phase I will demonstrate the capability to robustly model variability (aleatory uncertainty) and incertitude (epistemic uncertainty) during early design. The demonstrated methods will (1) allow rapid, rigorous, and more complete exploration of alternate designs in the mission- and engineering-constrained trade space; (2) provide a rigorous rationale for risk-based margin determination that is robust to surprise; (3) facilitate the incorporation of qualitatively described risks in quantitative risk analysis; (4) support the integration of physics and non-physics based risks in mission-wide risk analysis; and (5) permit sensitivity analysis at the mission, system, subsystem, and component levels that identifies the importance of specific uncertainties to uncertainty at higher levels and allows the rapid exploration of alternate strategies and designs. This suite of capabilities is not currently available to systems engineers and cannot be provided by more traditional probabilistic risk assessment methods.

Summary

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Large scale numerical simulations, as typified by climate models, space weather models, and the like, typically involve non-linear governing equations in discretized form, subject to initial and/or boundary conditions. Large scale simulations may be employed in a coupled manner, with the output of one simulation providing input data to another. Simulation execution may require significant 'wall clock' time to complete, resources such as memory and CPU, and may involve components that are networked and the need for resources such as input data files or temporary local storage of intermediate data products. With collaboratories and the increase in interdisciplinary and multi-investigator scientific projects, there is an increase in distributed, networked, and coupled scientific simulations. Moreover, problem complexity may require that multiple sets of parameters in the problem space be investigated, thus necessitating multiple simulation runs. With simulation runs extending in time, involving networked components, and networked resource usage, setting-up and monitoring these runs is non-trivial and increasingly time intensive. Such activity can waste a researcher's time; yet the simulation runs must be set-up and then monitored, as crashes, missing components, permission problems, network problems, etc., do occur. Our innovation is a self-regulating, autonomic, agent-based framework that can manage simulation runs.

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Timely processing of raw Earth science data for calibration and validation in a highly distributed and networked environment, and its storage at Distributed Active Archive Centers (DAACs) for presentation to the global scientific community is critical in NASA's mission for Earth Sciences. Here we propose to develop a stream processing engine approach to earth science data processing. Our innovation is based leveraging the emerging stream processing engine technology. Traditionally stream processing applications have been built using customized DBMS., which tend to be costly, and hard to change by non-specialist end-users. Our proposed architecture offers several significant benefits. First, an SPE developed application enables the refinement of stream filtering, the rapid development of new stream filtering capability faster than any other database or middleware based solution using StreamSQL , thus improving the maintainability and adaptivity of the system especially by non-specialist end-users. Second, by design, SPE technology offers inherent fault tolerance against asynchronous data input with attendant drop-outs.

Summary

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This SBIR project will develop and deliver revolutionary driver technology with intelligent fault protection for driving long-pulse (> 2msec), quasi-CW laser diode arrays (LDAs) at high power with improved performance and lifetime. A critical issue with operating LDAs for long discharge pulses is localized diode heating leads to current and optical instabilities, which irrevocably damage emitters resulting in LDA failure. SRL has demonstrated that diode instabilities can be detected and eliminated. As a result, integrating SRL's proprietary fault diagnostics into diode drivers increases laser diode lifetimes by more than a factor-of-40 over unprotected drivers. In addition, in Phase 1, SRL will acquire data demonstrating that our fault-mode circuitry can be used as a diagnostic to a priory determine which LDA's will have long lifetimes. In Phase 2 we will deliver a fully engineered compact driver for powering NASA LDAs and screening their suitability for use in flight hardware. The Phase 2 driver will have specific power ratings up to 7 kW/liter, which is 4 times higher than existing laser diode drivers. The combination of fault diagnostics for increased laser diode performance and lifetime and compact packaging, makes the SRL driver an important technology for powering LDAs for NASA flight systems.

Summary

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Various Earth Science fields require well-calibrated field radiometers whose calibrations must be tracked and verified in the field. NASA has long recognized the need to monitor and maintain calibrations of in-situ radiometric instruments. However, the light sources that have been developed for calibration monitoring typically require high power, are bulky and difficult to use in the field, and do not work with all types of radiometers. We propose a next-generation portable, ultra-stable, lightweight and highly versatile light source based on light-emitting diodes (LEDs). Recent advances in LEDs include higher power, efficiency, and a wider range of wavelengths (from UV to IR). These advances, coupled with LEDs' inherent suitability for electronic feedback stabilization, make them excellent candidates for more compact and power-efficient calibration sources. During Phase I we will identify and test LED devices, measurement and stabilization techniques, and physical configurations for use in one or more calibration sources. In Phase II we will build prototypes and implement a program for test and evaluation in cooperation with recognized calibration laboratories. At the conclusion of Phase II we will be ready to produce and sell a commercial version.

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This Small Business Innovation Research Phase I effort will establish the feasibility of developing a fiber coupled, high power, electro-optically controlled, space qualified, phase modulator for the NASA Laser Interferometer Space Antenna (LISA). Specific to the LISA project is the use of three spacecraft, spanned by vast distances, to make gravitational wave measurements. A central aspect in maintaining system performance is inter-spacecraft communications which require the use of frequency modulated, high power 1.06 mm light. AdvR's proposed approach offers phase modulation of a high power continuous wave 1.06mm laser signal with modulation capability of 1.9 to 2.1 GHz and 10% modulation depth. The key innovation is the use of a waveguide embedded in a non-linear optical material suitable for high optical power handling combined with patented micro-electrode technology for high speed modulation. To operate properly in space, the phase modulators used for LISA must be rugged to survive the journey to space and must perform optimally in a radiation environment. To achieve this goal, the proposed phase modulator development will include a fiber-in-fiber-out design that meets the space qualification requirements for mechanical stability of the package and radiation damage resistance of the non-linear optical material.

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This proposal addresses Item #2 of Topic X7.04 Aeroassist Systems and proposes innovative heat shield thermal protection systems (TPS) designs for human-rated aeroassist vehicles returning to Earth from the Moon and Mars. The proposed designs 1) utilize concepts with and without outer ablator materials, 2) employ outer refractory composite material rib-stiffened aeroshells with low emissivity foils on their internal structure to trap the heat and act like a high thermal resistance material, similar to multi-layer insulation but which have the potential to be less complex and less dense, and 3) make use of re-usable refractory composite materials that will be non-parasitic and structurally functional within the heat shield, thereby offering the promise of significantly reducing TPS mass fraction. The following will briefly describe the base heat shield used in Apollo Command Module and discuss the two alternative concepts and why they are advantageous.

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SSCI proposes to develop innovative algorithms for the integration of Health Monitoring (HM) subsystem with the existing FLARE (Fast on-Line Actuator Reconfiguration Enhancement) system that achieves rapid stabilization of the closed-loop flight control system in the presence of flight-critical failures. While both systems generate on-line estimates of the failure-related paramaters, the HM system can generate false failure information, while the FLARE system may result in poor performance in subsequent flight regimes if its parameter estimates are far from their true values. The main idea is to combine the failure parameter estimates from the HM and FLARE systems to assure robustness to false alarms, missed detections and detection delays in the HM system, and to use the combined estimate in the adaptive reconfigurable control law to assure the desired closed-loop performance. In order to achieve the project objectives, we plan to carry out the following tasks in Phase I: (i) Modify F/A-18 aircraft simulation to test the feasibility of the proposed approach; (ii) Develop the IHM-FLARE architecture and algorithms; and (iii) Evaluate the performance of the flight control system under false failure information. Phase II will result in algorithm enhancements, and implementation and testing using high-fidelity and piloted F/A-18 simulations. Boeing Phantom Works (Mr. James Urnes, Sr.) will provide technical and commercialization support throughout the project.

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AeroAstro proposes to develop a low-power, low-volume and lightweight, state-of-the-art digital radio capable of operating in a wide variety of bands, from VHF through Ka microwave, with data transceive capabilities of voice, telemetry, and high-resolution video. This device is intended for use in manned extra-vehicular activities (EVAs) in deep-space environments, on lunar and planetary surfaces, and in the links and networks involved in end-to-end data flow. This radio is innovative in several aspects: in its size and power, in its modularity that allows the ability to handle different bands, in its use of software radio technologies, in its automatic adaptability to varying transmission environments, and in its reliability and fault-tolerant performance. This technology is paramount to the safety and success of manned missions in space, where unpredictable environments are present and where reliability is absolutely critical.

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NanoSonic has developed revolutionary nanostructured, yet macroscale, multifunctional Metal Rubber<SUP>TM</SUP> films. In support of NASA's Vision for Space Exploration, low cost Metal Rubber<SUP>TM</SUP> freestanding or conformal skins would be optimized as protective coatings for human and robotic space exploration. Specifically, ultra-lightweight, nanostructured coatings with protection against electrostatic charging, abrasion and radiation over a wide range of mechanical and thermal fluctuations are offered. Metal Rubber<SUP>TM</SUP> is fabricated via layer-by-layer, molecular self-assembly, which enables thickness and placement control over multiple constituents for true nanostructured multifunctionality (nm scale); while advanced polymers have allowed scale-up to free-standing thick films (several mm thick, at < 1 g/cc). Metal Rubber<SUP>TM</SUP> is not a conducting polymer or a sputter-coated polymer film. It is a freestanding nanocomposite formed in situ by chemically bonding each monolayer of nanostructured constituent, thereby eliminating residual stress between each component. New, ultra-low modulus Metal Rubber<SUP>TM</SUP> can be strained to > 1000% elongation while remaining electrically conductive; and returns to its original shape and nominal conductivity when released. Bulk resistivity (as low as 10-5 Ω∙cm), and mechanical moduli (0.1 MPa to 500 MPa) have been demonstrated. Metal Rubber<SUP>TM</SUP> requires less than 1 vol% of metal, allowing the manufacturing a cost effective, advanced material

Summary

Description

Planning and scheduling (P&S) is an essential task for managing current and future NASA missions. P&S systems are used in many areas of spacecraft operations including science planning, flight dynamics operations, and space and ground network scheduling. Typically, different tools are used by different users, possibly in different locations, for each of these functions because current tools are not suited to addressing all of a mission's P&S needs. There is thus an additional need to integrate the results of all these scheduling efforts, which increases mission cost, complexity, and risk. To address these issues, Emergent Space Technologies (Emergent) is proposing to develop a prototype plug-and-play P&S system that allows for heterogeneous, distributed scheduling of activities to occur simultaneously without conflict. The unique qualities of the proposed P&S system that will make it an innovative solution are the nature of how newly developed resources, tasks, and scheduling algorithms can easily be added to the system, how it will have an openly available and well-defined application programming interface (API) for developers to use, and how it will operate in a distributed environment as a resilient peer-to-peer architecture with no single points of failure. With these innovations in place, P&S implementations for flight dynamics, automation and autonomy, system monitoring, science planning, or any other activity can be developed and operated in remote locations and still be a fully-integrated solution.

Summary

Description

This project will develop a sensitive and specific biosensor worthy of field deployment for autonomous operations. The underlying technology will enable in situ detection of terror agents in the cargo space of an aircraft or in airports and thereby reduce vulnerability of the Air Transportation system. There is a critical need for sensitive, rugged biosensors capable of performing assays under harsh conditions with minimal crew attention for decreasing the time and cost of analyses. Toward that goal, tasks have been designed in this Phase I proposal to develop a biosensor using molecularly imprinted polymers - a class of synthetic receptors that can be tailored to selectively interact with analytes for which recognition molecules of biological origin may not be available. The feasibility of a sensor array will be demonstrated by using nerve agent simulants. A prototype sensor array device, and smart signal processing algorithm will be developed in Phase II. For Phase III manufacturing engineering and Phase III follow-on funding, discussions have been held with two potential partners. A highly proficient engineering team, with a cumulative 70 person-years of experience in materials science and optical sensors, is in place to develop the biosensor.

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Significant improvements in photovoltaic materials and systems are required to enable future exploration missions. This SBIR project, involving two innovative organizations: CFD Research Corporation (CFDRC) and University of California Riverside (UCR), has two major objectives: 1) develop and provide reliable, validated computational tools for assessment, design, and optimization of novel nanostructures based on Quantum Dots (QD) for future nano-devices for space applications; 2) investigate, design, and demonstrate new photovoltaic (PV) structures based on QD nanotechnology, with improved efficiency and radiation hardness. The inherently radiation tolerant quantum dots of variable sizes maximize absorption of different light wavelengths ("multicolor" cell), which dramatically improves PV efficiency and diminishes the radiation-induced degradation. Phase I includes development of numerical tools for modeling electron-phonon transport in QD superlattices for photovoltaic applications, using experimental data from UCR Nano-Device Laboratory for validation and calibration of the new tools, and computational proof-of-concept. In Phase II, the new QD models will be integrated into CFDRC's advanced photonic-electronic device simulator. Novel QD photovoltaic nano-engineered materials and designs will be down-selected for further development to the point of testable prototypes. They will be fabricated and provided to NASA for electrical characterization and radiation testing.

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For detecting leakage of cryogenic fluids in spaceport facilities and in spacebound vehicles, this project proposes to demonstrate the feasibility of an all-optical sensor that can be fitted into narrow orifices around plumbing junctions. Fast response time and complete reversibility in the detection range of 1 ppm to 100% for hydrogen will be demonstrated in Phase I. This technology will support NASA goal of reducing vehicle and payload cost, and increase safety of ground and flight operations by measuring hydrogen in real-time and in situ. The sensor's thermal shock resistance when exposed to cryogenic fluids will also be tested in Phase I. A prototype device will be engineered, field-tested and delivered to NASA in Phase II. Successful discussions have been conducted with industrial partners for commercialization support including Phase III follow-on funding for this project. One major U.S. aerospace company has expressed strong interest in the proposed technology by providing a letter of support. A technical team having 70 years of cumulative experience in developing commercially viable products has been assembled for this project.

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NASA requires advanced high power primary lithium batteries for ultra low temperature applications. The key component that limits the performance at low temperature is the battery electrolyte. Proof-of-concept experiments have shown that Covalent's new non-aqueous electrolyte formulations greatly enhance low temperature primary battery performance while preserving its long shelf life. At temperatures as low as -100<!DOCTYPE html PUBLIC "-//W3C//DTD XHTML 1.0 Strict//EN" "http://www.w3.org/TR/xhtml1/DTD/xhtml1-strict.dtd"> <sup>o</sup> C, our new electrolyte demonstrates superior transport properties due to minimal triple ion formation. Accelerated storage tests revealed no voltage delay indicative of a stable passive film formed on the lithium anode. When coupled with a high energy density cathode material such as carbon monofluoride (CFx), our new electrolyte formulations will enable primary lithium primary performance over a broad spectrum of ultra low temperature applications. Specifically, Li/CFx batteries incorporating the new Covalent electrolytes will deliver more than 30% of their room temperature capacity at temperatures as low as -100<sup>o</sup> C at practical discharge rates.

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In Topic X1.03 NASA (JPL) is seeking to extend and implement long distance exploratory surface rover missions to gain knowledge of surface topology and roughness. The benefit is to identify suitable sites for future landings of human or robotic missions and to aid in pinpoint landings. High resolution millimeter wave radar sensors provide a low cost, reliable way for a Moon or Mars Rover to detect hazards and negative obstacles (i.e. holes and drop-offs) while moving or stationary. A radar sensor is effective as a stand-alone sensor, or as a complement to the stereo vision based and laser line systems used on previous successful rover missions. The low computer overhead and inherently rapid response of a radar sensor enables a rover to rapidly traverse extremely rugged terrain without risk of falling into a hole or being otherwise trapped. The rapid traverse speed provides a wider area for collection of science data, and reduces the fraction of limited mission time spent on moving, as opposed to measurement. The overall objective of the proposed program is to develop a practical rover radar sensor for negative and positive obstacle detection.

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The fabrication of very large optical telescopes for space astronomy can be prohibitively costly due to the immense weight and size of monolithic primary mirrors. The cost of these telescopes can be reduced by the use of a segmented primary mirror. The next generation of large segmented mirrors must have little or no edge exclusion. The Zeeko Precessions polishing is a sub-aperture process that has been developed for the control of form and texture in the production of aspheric and other optical surfaces. The Precessions process is deterministic and provides dramatic reductions in production time due to its high removal rate and repeatability. Similar to other processes, the Precessions process can produce an edge effect due to the polishing spot changing when in extends beyond the edge of a part. Currently, the control software assumes no change in the spot size or shape when it moves beyond the edge. The primary goal of this Phase I project is to understand process differences at the edge and develop an approach to minimize them. Results from Phase I will provide better understanding of the polishing influence function which will serve as a foundation for a Phase II study on power spectral density (PSD) control and production of prototype optics that demonstrate advancement of the state-of-the-art in minimizing edge exclusion.

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NASA's future Earth-Sun System missions require the rapid development of small, low-cost remote sensing instruments for the analysis of chemical and physical properties of planetary atmospheres. The objective of the proposed project (Phases I and II) is to research, develop, and demonstrate the first space-qualifiable digital correlation spectrometer on a single chip which, if successful, will reduce the risk, cost, size, and development time of microwave spectrometers and will enable space-science observations measurements that were not previously possible. The innovative approach proposed for achieving the objective consists of a synergistic combination of the following: (a) a unique parallel architecture that will reduce the operating clock frequency, relative to a single-stream architecture, by a factor of 2 and consequently will lower significantly the power consumption, (b) novel differential analog and digital circuits that will improve robustness while operating in the presence of total dose natural radiation found in the space environment, and (c) an advanced 0.13 um CMOS fabrication process with cooper interconnect, available at relatively low-cost through the MOSIS fabrication facility from IBM, for manufacturing high-performance, low-power, reliable, and robust (total dose radiation and latch-up resistant) space-qualifiable chips.

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NASA needs a cryogenic refrigerator for the 15-25K range for receiving arrays of ground-based antennas that will serve the telecommunications needs of future space exploration. We propose to develop a 15-25K Static-Helium Regenerator/Double Pulse Tube Cooler for receiving arrays. Our SHR/DPTC combines two of our technologies that have potential to enable pulse-tube coolers to operate efficiently in the 15-25K range: (1) our Static-Helium Regenerator (SHR) technology, which uses static helium for the regenerator's thermal mass; and (2) our Double Pulse Tube Cooler (DPTC) technology, which uses a recuperator (instead of regenerators) to transfer heat between two pulse-tube sub-cycles that operate in parallel and out-of-phase. In Phase I, we will perform system trades and generate a preliminary design of a 15-25K SHR/DPTC that minimizes life-cycle costs for receiving arrays. In Phase II, we will: develop and test SHR/DPTC components; integrate the SHR/DPTC components with cooler components we have already developed; and test the integrated cooler. In Phase III, we will build and sell SHR/DPTCs to the government and private sector.

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Miniaturization of mass spectrometers is restricted almost exclusively by the ability of small vacuum pumps to remove gas loads during operation of the instrument. Our answer to this dilemma is a specialized interface that focuses a parallel beam of ionized gas molecules through an orifice that is at least 10 times smaller than ever before achieved in a mass spectrometer inlet. Our recent patent application describes this interface. Not only can we use this interface to radically reduce the pumping requirements within the mass spectrometer, but it should also enable an unprecedented cooling and focusing of the ion beam. This in turn will enable attaining mass resolutions of over ten thousand in a phase I instrument which uses a linear time of flight tube of only 10 cm. A small overall instrumental footprint (probably 1.5 cubic feet including pumping and electronics) should be attainable in a phase II effort.

Summary

Description

Many UV photon-counting and imaging applications, including space-borne astronomy, missile tracking and guidance, UV spectroscopy for chemical/biological identification, and UV medical imaging, demand very high performance in detector sensitivity, speed, resolution, and background noise. This proposal is directed toward the development of innovative high-efficiency UV photocathodes based on the wide bandgap III-nitride semiconductors for reliable operation in space missions.

Summary

Description

NASA seeks highly efficient, long life solar dynamic power conversion systems. The requirements for these missions emphasize low mass and high conversion efficiencies. A reliable and highly efficient Stirling convertor would provide mission planners with less costly spacecraft power options than currently exist. Current Stirling technologies have demonstrated a beginning of life specific power level of 4.2 W/kg, and a useful life greater than 10 years. The proposed effort will result in the preliminary design for an innovative multiple-cylinder alpha free-piston Stirling engine (AFPSE) for high power applications. The program approach minimizes development risk by combining proven technologies, experiences and innovative concepts of Sunpower Inc. and Global Cooling BV (GCBV) with AFPSE. The proposed system is a compact, highly efficient, long life, low mass Stirling machine for a high power conversion system. This configuration having multi-pistons in separate cylinders connected by rejector and acceptor is not only very simple due to one moving part in one cylinder with no displacer, but also highly adaptable due to its versatile shape. This machine is very innovative because it is anticipated to achieve a specific power greater than 100W/kg as well as a heat input to electrical output conversion efficiency greater than 30%.

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We propose the development and space-qualification of a 1.06 micron ultrastable fiber laser source that fully satisfies the requirements of this SBIR opportunity (Laser Technologies for Gravitational Wave Detection). Our recommended approach builds on extensive experience developing and using single-frequency laser sources in the near infrared, both for aerospace and commercial applications. Our technical approach is based on emerging technology, spawned by the telecom industry that is only now reaching the maturity level where space qualification can be undertaken. NASA requires ultrastable laser sources for a variety of ongoing and planned missions including LISA and GRACE.

Summary

Description

NVE Corporation will design and build an innovative, low cost, flexible, configurable, radiation hardened, galvanically isolated, interface ASIC chip set that will reduce power consumption, enable high efficiency power conversion management, highly integrate existing discrete solutions, enable precision isolated data conversion and communication, save weight and footprint and be more immune to radiation than the existing optocoupler technology solution. The proposed chip set configurations will interface with many communication protocols and data signaling applications. This flexible configuration enables variant uses of the silicon, increases circuit and application flexibility, allows protected, isolated interfaces between systems, and increases overall system speed and reliability while reducing complexity. A key challenge is to successfully integrate NVE's commercialized Giant Magneto-Resistive (GMR) based post processing IsoLoop<SUP>REG</SUP> technology with radiation hardened or radiation tolerant under-layer circuits. NVE has shipped millions CMOS-based commercial units using this concept. GMR material, configured into magnetically sensitive resistors, is inherently radiation hard. Customers have tested the basic sense element to a dose rate of 1.1E+12 rads(Si)/sec. without failure. NASA Goddard (Robert Reed) tested commercial IsoLoop products to a fluence of 1x107 ions/cm2.and observed no upsets. James Lyke of AFRL/VSEE will advise and assist NVE on the program.