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To date there are several approaches for incorporating sensing capabilities into RFID. Active tags use batteries to power their communication circuitry, sensors, and microcontroller. Active tags benefit from relatively long wireless range and can achieve high data and sensor activity rates. However, the batteries required by active tags are disadvantageous for device cost, lifetime, weight, and volume. In contrast, passive sensor tags receive all of their operating power from external RF transmitting sources and are not limited by battery life. One attractive feature of passive sensor tags is the prospect of permanently embedding them in objects for structural monitoring. Another is their suitability for applications in which neither batteries nor wired connections are feasible, for weight, volume, cost, or other reasons. A limitation of purely passive sensor tags is the requirement of proximity to a RF transmitter. Since lower power consumption is one major trend in RF circuit design, a self-powered system by means of energy harvesting becomes very attractive. It can serve as the enabling technology for novel applications such as ambient intelligence. Using a power harvesting technique for wireless rechargeable battery smart sensor and enhanced RFID are the key elements for successfully distributing sensors across sensor networks.

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We propose to investigate the feasibility of developing a low noise, two-side buttable, 64x64 readout multiplexer with the following key design features: 1- By far the largest readout array developed for far IR detectors to date. Four of these readout can be butted together to form a >16k-pixel mosaic array satisfying the need of the next generation of astronomical instruments. 2- Optimized for use with far infrared detectors requiring low bias levels. The unit-cell design will maintain constant bias across the detector during the integration eliminating non-linearity and detector debiasing. The design will also minimize the pixel-to-pixel DC variation which improves the bias uniformity across all pixels of the array. 3- Capable of operation at cryogenic temperatures at least as low as 1.6K. Advanced monolithic cryo-CMOS technology will guarantee deep cryogenic operation with minimal impact on noise performance. 4- Offers the potential of being directly hybridized to IR detector arrays using indium-bump technology. This technology has been identified by NASA as well as the science and astronomy community as key for future far IR astronomy. It fits well within the scope of the SBIR Subtopic S1.04 and will be a benefit to many large and small NASA missions including SAFIR/CALISTO and SOFIA.

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The Cognitive Gauge (CogGauge) tool aims to develop a portable gaming application that assesses cognitive state of astronaut crew members with the goal of determining probable causes of observed cognitive deficits. CogGauge, while engaging astronauts in an entertaining experience, combines predictive tools for assessing cognitive workload with metrics that assess performance decrements. CogGauge uses a hybrid approach combining predictive workload values with behavioral/performance-based workload assessment across a number of task difficulty levels. This comprehensive approach takes into consideration learning effects across a number of cognitive tasks (i.e., mini-games in the gaming context) and derives assessment of performance decrements related to cognitive deficits to identify probable causes of cognitive decrement. Feedback from CogGauge may be provided to astronauts and/or flight surgeons to determine impact on space flight and missions.

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Impact Technologies, in collaboration with the Georgia Institute of Technology, proposes to develop and demonstrate an innovative flight envelope estimation and protection system for aircraft under damage upset conditions or severe flight variations. Through the integration of advanced fault detection (IVHM) algorithms, real-time system identification of the damage/faulted aircraft and flight envelop mapping, real-time decision support can be executed autonomously for improving damage tolerance and flight recoverability. The core tasks to complete of this proposed workscope include: 1) Development of a strong-tracking health identification algorithm for assessing the dynamics and performance limitation of impaired aircraft; 2) Development of the adaptive flight envelope estimation process; 3) Development of the envelope protection algorithm based on adaptive neural networks that can learn the generated online dynamic models; and 4) Demonstration of the proposed technologies under realistic flight control actuator and propulsion fault conditions. A core innovation of this program is the use of the on-line, adaptive learning neural networks that are capable of generating the dynamic models and operational envelop in real-time, which can then be used to estimate limits on the controller commands while preventing envelope exceedances. The developed techniques will be demonstrated in Phase I using an integrated aircraft model that uses the NASA MAPSS propulsion model and Generic Transport Model (GTM), with eventual demonstration using the NASA Flight Simulator at NASA Langley.

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Over-the-horizon communications and information networks are beginning to produce sustainable capabilities for Earth science operations using advanced unpiloted vehicles. There is a growing need for affordable desktop access to globally deployable data acquisition and data processing sensor-web networks on board these airborne platforms. Central to meeting this need is further miniaturizing on-board computing, data acquisition, and satellite network communication equipment. With current technology, the associated on-board components weigh several pounds. We propose to reduce the weight to mere ounces while also lowering cost and power consumption. This will greatly expand the deployment of this technology to new-generation ultra-small unmanned air vehicles, other space and weight-constrained airborne systems, and a wide range of terrestrial applications.

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Ultra Wide band Water Sensor Project

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Develop a Compact Transmitter Module (CTM) capable of operating at 1.26 5m, 1.57 5m and at 2 5m complete with all drive and control electronics for the TEC and the laser diode itself reducing size, weight and power while improving performance and reliability. The first part of the approach is to incorporate the electronics within the same hermetically sealed enclosure with the laser chip and associated optics. EM4 will take this basic design and make modifications to reduce size, weight and power consumption using thin film thermoelectric coolers (nano-coolers) to replace conventional TEC. Weight reductions will be realized by using alternative which are composites of Aluminum Silicon (AlSi) and Aluminum Silicon Carbide (AlSiC)

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With NASA's exploration initiative to return to Lunar Exploration and eventual human exploration of Mars, NASA has an increased need for an Autonomous Rendezvous and Docking (AR&D) solution. First generation rendezvous sensors used video guidance and required extensive human intervention and ground control. Data latency in these systems is problematic and has uncovered the need for an autonomous rendezvous and docking system. Scanning Ladar and stereo video have significant shortcoming and have not proven they can provide a solution to reduce the reliance on human interaction during proximity operations. ASC's Flash Ladar video cameras can provide the 6 Degree-of-freedom data in real time, not available in any other video system. Advanced Scientific Concepts Inc. (ASC) is a small business that has developed a number of 3D flash LADAR systems. Flash Ladar Video Cameras (FLVC) are 3D vision systems that return range and intensity information for each pixel in real time. The ASC camera with its 128x128 3D array is the equivalent of 16000 range finders on one chip. This allows the sensor to act as a 3D video camera with functionality well beyond just range finding. Its small size, low power and fast range data frame rate (30Hz) allows the sensor to be configured for a variety of rendezvous and proximity missions.

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Development of Tantalum Carbide for Microgravity Containment Cartridges Project

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Recent advances in propulsion, aerodynamic, and noise technologies have led to a revived interest in supersonic cruise aircraft; however, achieving economic viability for these vehicles requires dramatic improvements in cruise efficiency. Optimization of inlet performance offers a potent method for achieving this goal, and a range of conceptual flow control systems are available to address critical problems like blockage, boundary layer bleed, duct length, and flow distortion. By exploiting High Temperature Smart Memory Alloy (HTSMA) technologies, these concepts can be mechanized into robust, compact and lightweight devices, enabling actuators suitable integration into the inlets of supersonic aircraft. The proposed effort leverages prior successful development of solid state smart structures by the investigators in developing of small scale surface-mounted flow control devices as well as large scale actuation systems for inlet ramp mechanisms actuated via HTSMA technology. The proposed Phase II will build upon the Phase I proof of concept study to further develop a fully integrated active supersonic inlet system, including active inlet ramp and deployable flow control devices, as well as the aero/thermo/structural analysis models required to design such systems and subcomponents. In addition, Phase II will be the continued refinement and characterization of actuator-ready HTSMAs.

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ElectroChem proposes a Phase II program to advance its very successful SBIR Phase I technology effort to the point of minimum hydrogen loss through the electrolyzer membrane, while the high proton conductivity necessary for high efficiency water electrolysis is maintained. In Phase I, ElectroChem demonstrated that its concept of adding clay to a Nafion proton conductive membrane would significantly reduce the penetration of hydrogen gas through the membrane. In Phase II, a comprehensive technology effort (aimed at optimization) will be carried out which uncovers the microscopic changes that occur within the membrane as a result of the clay addition. The objective of this effort is first to correlate the microscopic morphology that occur within the Nafion-clay nanocomposite membranes with the reduction in hydrogen penetration produced by the clay addition. A second objective is to control the microscopic morphology and establish a process to develop the most effective Nafion-clay nanocomposite membranes, leading to advanced MEAs. The final objective is to evaluate the Nafion-clay nanocomposite membranes under high pressure Commercial Electrolyzer conditions. Successful completion of this effort will enable NASA to meet its requirement for an electrolyzer that will operate very efficiently both at low current densities and at high pressures.

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NASA space exploration projects require avionic systems, components, and controllers that are capable of operating in the extreme temperature and radiation environments of deep space. To design wide-temperature radiation-hardened (rad-hard) electronics and predict characteristics and reliability in space, advanced models and simulation tools are required at multiple levels. Analog and mixed-signal circuits for space have not been adequately addressed so far. This project aims to design, develop, validate, and demonstrate novel Radiation Hardened By Design (RHBD) analog/mixed-signal integrated circuits (ICs) aimed for the extreme environments of space. In Phase 1, CFDRC in collaboration with Georgia Tech will: (1) enhance and demonstrate the CFDRC's unique physics-based mixed-mode simulation tools (NanoTCAD coupled with Cadence Spectre) for predicting extreme-wide-temperature and transient radiation response of analog/mixed-signal ICs based on silicon-germanium (SiGe) BiCMOS technologies; (2) perform first-ever mixed-mode simulation-based investigation of single-event effects (SEE) in SiGe analog, mixed-signal, and radio-frequency (RF) circuits in wide temperature range, and provide important understanding of currently unexplained physical phenomena behind the experimental radiation/temperature data collected under the NASA Exploration Technology Development Program (ETDP); and (3) develop preliminary RHBD concepts for SEE hardening. In Phase 2, we will demonstrate and validate the improved physics-based models for temperature range from -230<SUP>o</SUP>C to +130<SUP>o</SUP>C, and apply them to evaluate and develop RHBD designs over the expected operating range. New RHBD devices and analog circuits will be fabricated in prototype chips and tested at wide temperatures and radiation, and delivered as a component library to NASA.

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Los Gatos Research proposes to develop a powerful new technology - next generation Micro-Capillary Electrochromatography - a high performance and low power consumption microfluidic sample separation device suitable for separating organic molecules as signatures as past and present life on Mars. In this Phase II effort, we will refine this enabling new microfluidic technology that we have successfully demonstrated in Phase I in order to integrate with NASA Mars Organic Detector.

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Active Signal Technologies and its subcontractor Moog propose to develop a high-frequency actuator driven valve intended to achieve TRL 6 by the end of Phase II. This active control component will be capable of modulating fuel flow at multiple injection locations with minimum fuel pressure drop and thus enable critical improvements in aerospace vehicle turbine engine combustion dynamics, notably mitigation of thermo-acoustic instabilities. These instabilities have impeded development of advanced lean-burning combustors for reduction of NOx emissions and improvements in combustion efficiency. While passive approaches to control combustion instability have been successful on particular new engine designs, the ultimate solution is active combustion control where the greatest challenges are the bandwidth (1 kHz) and system temperature requirements. The Phase-I goal is to demonstrate that these are achievable by designing and building a proof-of-principle system complete with high-frequency, high-temperature actuator and valve. Active Signal has selected Terfenol as the most suitable actuator material and will apply 25 plus years of actuator, valve and pump experience to meet the goals. The system will be tested against pressure and flow requirements to demonstrate the effectiveness of this approach before fabricating a prototype suitable for the GRC test stand in Phase II.

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Reduction of noise is critical to the public acceptance and mission suitability of rotorcraft. Accurate prediction of rotorcraft noise is directly related to the ability to predict the highly complicated interaction between the aerodynamic surfaces and their wakes, and while current numerical tools can, in principle, model the complete rotorcraft, they are severely hampered by modeling assumptions or numerical formulation. Consequently, commonly used tools fail to adequately predict the load distribution, and hence noise, of arbitrarily shaped rotors and fuselages. The proposed effort directly supports NASA's mission of assisting the development of advanced rotorcraft by developing an innovative physics-based multidisciplinary tool for predicting rotorcraft aeroacoustics. This tool, consisting of a fully coupled FUN3D CFD code, VorTran-M module and acoustic propagation model, will be able to address interactional aeroacoustics problems unique to rotorcraft, capturing rotor-fuselage interactions that lead to both structural vibration and undesirable interactional acoustics. This effort will build upon recent work addressing critical issues such as numerical diffusion, grid generation, turbulence modeling and rotorcraft noise prediction and reduction at CDI, GIT and elsewhere. The hybrid code will achieve TRL=4 during Phase I and TRL=7-8 by the end of Phase II.

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SiGe Semiconductor Devices for High-Performance Cryogenic Power Electronics Project

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Microcosm will use existing hardware and software from related programs to create a prototype Lunar Navigation Sensor (LNS) early in Phase II, such that most of the effort can be spent in extensive field-testing, making corrections as needed, and critical evaluation of the LNS performance on Earth and projected performance on the Moon. By using NGS survey markers, with centimeter-leve position accuracy, as test sites, we expect to create a truth model for both absolute and relative position measurements that is essentially error free (relative to the LNS accuracy), thus allowing very accurate characterization of both random and systematic errors for both absolute and relative position measurements. This unambiguous characterization of the total error will allow validation (or correction) of the navigation error models and assessment of system performance with a high level of confidence. Additionally, the LNS prototype hardware is sufficiently small (roughly shoebox size with a laptop PC for data collection) and easy to set up (put on a tripod over the NGS marker), that it can easily be taken to multiple test locations. Finally, a detailed technology roadmap will be created showing how the TRL 6 LNS can be raised to TRL 9, ready for flight.

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During initial design studies, parametric variation of vehicle geometry is routine. In addition, rotorcraft engineers traditionally use the wind tunnel to evaluate and finalize designs. Estimation of rotor tunnel blockage is significantly more complex than bluff body corrections as the correction depends on operational characteristics such as rotor RPM and thrust produced. This proposal offers to develop an Integrated Design Environment (IDE) which can simulate a complete rotorcraft with or without wind tunnel walls including all the facility effects. At the heart of the innovation are: 1. An automated hybrid grid generator (viscous grids near the bodies and unstructured Cartesian grid everywhere else). 2. A robust and economical incompressible flow solver for the entire system of grids. 3. Momentum source based rotor model that is suitable and economical for simulating configurations with multiple rotors. In Phase I, the proof-of-concept developed used unstructured Cartesian grid for the model and wind tunnel. In phase II, the tool will be extended to hybrid grid with viscous grid near solid surfaces and will include several tools including a simple CAD like geometry manipulation tool and pre- and post-processing tools all integrated in one environment to facilitate ease of use.

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M4 Engineering proposes to develop a generalized reduced order model generation method. This method will allow for creation of reduced order aeroservoelastic state space models that can be interpolated across a range of flight conditions. This development will be a significant advance to the process of control law development, especially in the design of control systems required to provide flutter suppression, gust load alleviation, and ride quality enhancement. The proposed technique will be an excellent compliment to modern linear and nonlinear aeroservoelastic analysis methods.

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Automation and autonomy are key elements in realizing the vision for space exploration. The NASA Exploration Technology Development Program (ETDP) has been developing several core autonomy capabilities, one of which is called a procedure representation language (PRL). PRL can be automatically translated into code that can be executed by NASA-developed autonomous executives. Another type of automation being developed by ETDP is automated planning aids. These will be needed to increase the number of missions that existing levels of flight personnel must be able to handle. But PRL has few constructs to enable automated planners and schedulers to take advantage of the procedures resulting from PRL. In Phase 1 we developed extensions to PRL to add planning information resource, constraints and sub-procedural information so as to produce code useable by automated planning software. In this project, we propose to develop an interactive planning aid for flight controllers to show that such an aid can process our enhanced PRL files to generate mission plans and to test their feasibility via an execution system. Besides refining our previous modeling efforts, this work will show that the availability of computer-useable planning information can lead to practical applications of NASA's automated planning efforts.

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The digital array gas radiometer (DAGR) is a new sensor design for accurate measurement and monitoring of trace gases in the boundary layer from space, aircraft, or ground-based platforms using scattered sunlight. Target gases include CH4, CO, CO2, N,2O and other species critical to climate science, environmental monitoring and commercial pollution compliance efforts.

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Nanofluid Boiling Module for Precision Cooling of Microelectronics Project

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Mini-Cell Ion Mobility Spectrometer for In Situ Chemical Analysis Project

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Deployable Space Systems (DSS) has developed an ultra-lightweight elastically self-deployable roll-out solar array (ROSA) structural platform that when combined with ultra-thin 33% IMM PV or 29.5% standard ZTJ PV solar-cell flexible blanket technologies can produce a near-term and low-risk solar array system that provides revolutionary performance in terms of high specific power (>500 W/kg BOL with IMM & >225 W/kg with ZTJ), lightweight, high deployed stiffness, high deployed strength, compact stowage volume (>50 kW/m3 BOL), reliability, affordability, and rapid commercial readiness. ROSA's predicted performance metrics are incredible improvements over current state-of-the-art, and in many cases are mission-enabling for future applications. The ROSA technology innovation is applicable to practically all NASA and non-NASA missions as a direct replacement for current solar array technologies. The proposed Phase 2 program has been uniquely structured to methodically develop a feasible scaled-up ROSA solar array system specifically configured for NASA's Outer-Planets mission applications, collaboratively with all the technology stakeholders, and increase technology readiness to TRL 5/6. The successful completion of the proposed program will rapidly ready the mission-enabling ROSA solar array technology for commercial infusion into future programs.

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Microwave Powered Solid Waste Stabilization and Water Recovery Project