Summary

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Phoenix Integration will develop a collaborative simulation and design environment that will seamlessly integrate the people, data, and tools required for analyzing and designing complete vehicle systems. This next generation environment will help NASA to accurately assess and trade-off competing air vehicle concepts early in the design process. Working within the environment, geographically distributed team members will be able to easily construct large multi-disciplinary multi-fidelity system simulations from a custom library of reusable analysis components. A key feature of the environment will be "numerical zooming", i.e. the ability to incorporate numerical analyses of varying levels of fidelity in the simulation. Interfaces and tools will be provided that will allow users to configure the system simulation and securely execute it using heterogeneous computing resources. A simulation data library will allow users to share models, results, and conclusions with one another, and will serve as a searchable information repository. The expected results of the Phase I research will be a working prototype that will demonstrate key aspects of the proposed design environment. The Phase II program will result in a comprehensive framework environment that will help NASA achieve Fundamental Aeronautics Program goals for a broad range of air vehicles.

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This is a proposal to develop an electronic, focusing schlieren system for flight research based on electronic cameras and spatial light modulators as dynamic programmable masks. Schlieren methods are widely used to visualize turbulence and shock phenomena. Focusing schlieren systems are ideal for applications requiring a large field of view, and are the preferred methods for outdoor schlieren systems. One schlieren technique for large field studies is the use of focusing schlieren with background grids. Recently, schlieren systems that use the sun as a background source have been developed for studying shock waves for aircraft in flight. The application of both schlieren techniques is restricted by the capabilities of fixed schlieren cut-off masks. Liquid crystal spatial light modulators afford greater flexibility, as the correct cut-off mask can be programmed and updated electronically. Since the spatial light modulators can be updated at video rates or faster, there is also the possibility of using the SLMs to correct for changes in the background. In addition, we will incorporate state of the art electronic cameras.

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The overall technical objective of the proposed Phase II program is to complete a system-level demonstration to show the capability and benefits of integrating this backup radiator/Variable Conductance Heat Pipe (VCHP) with the Advanced Stirling Radioisotope Generator (ASRG). The Phase I project developed a feasible VCHP radiator design that can be integrated with the ASRG. In Phase II, a trade study will be conducted to optimize the VCHP design. A superalloy heat pipe will be fabricated from Haynes 230, which has good strength at the 850<SUP>o</SUP>C operating temperature and long term life tests with alkali metals. In addition to the VCHP, a General Purpose Heat Source (GPHS) simulator and a Heater Head simulator will both be designed and fabricated. Testing of the VCHP with the GPHS and Heater Head simulators will verify the ability of the VCHP to provide backup cooling for the Stirling convertors. The goal at the end of the program would be to bring the concept to Technology Readiness Level 5: Component Validation in a Relevant Environment.

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In response to the need for motors, actuators and sample acquisition system that can operate in the harsh Venusian environment for extended periods of time, on the order of several hours to days, Honeybee Robotics proposes development of high temperature scoop and joint; and continued development of an extreme temperature brushless DC motor and a resolver. All hardware will be demonstrated in simulated Venus surface conditions. During Phase I, a first-generation prototype BLDC motor and resolver were designed, built and tested in Venus-like conditions (460<SUP>o</SUP>C temperature, mostly CO2 gas environment). The Phase I tests demonstrated the feasibility of the design through verification that the motor and the resolver can operate at 460<SUP>o</SUP>C for an extended period of time. A further developed and optimized version of this motor and resolver could be used to actuate sample acquisition systems, robotic arms, and other devices outside of an environment-controlled landed platform on the surface of Venus. The motor and resolver's capability to survive for hours (and potentially longer) in that environment is a major benefit to future Venus science missions since it would allow time for communication ground loops to optimize sample target selection and allow for multiple samples to be acquired from the surface. The extreme temperature motor and resolver would therefore revolutionize the exploration of Venus. In Phase II, an extreme temperature resolver and a suite of different size of extreme environment brushless motor will be developed to TRL 6. High temperature scoop and joint will also be developed to TL 6. Aside from Venus exploration, other potential NASA and non-NASA applications for an extreme temperature motor include actuation of fluid pumps, gimbals, robotic joints and manipulation systems, as well as turbine, expendable launch vehicle and furnace tending system components.

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Lightweight, high performance thermal insulation is critical to NASA's next generation Exploration spacecraft. Zero or low cryogenic propellant boiloff is required during extended missions and lengthy on-orbit times. Multilayer insulation (MLI) is currently the insulation of choice for cryotank insulation. MLI's high vacuum performance exceeds alternative insulations by a factor of ten. However, heat flow through MLI is usually the largest heat leak in cryogenic systems, so improvements in thermal performance are desirable. Integrated Multi-Layer Insulation (IMLI) is an innovative new technology using a micro-molded polymer substructure integrated with radiation barriers to provide an ultra-high performance thermal insulation system. IMLI was proven a viable concept in Phase I work, reaching TRL4 with component validation in the laboratory. Prototypes were built and tested, demonstrating equal to lower thermal conductivity than MLI, and layers attached to each other in a snap-together assembly with controlled layer spacing. The Phase I IMLI prototype had a thermal conductivity of 1.8 W/m2, with the Celcon polymer used for these prototypes still outgassing. The IMLI thermal conductivity was calculated to be 63% that of MLI, which would provide improved long term cryogenic propellant storage. This improved insulation can provide lower thermal conductivity, vacuum compatibility, layers inherently attached to each other that support themselves, and efficient assembly. IMLI may also provide inherent structural benefits, including improved strength and integrity over current MLI. This proposal is to further develop IMLI toward commercialization. Tasks proposed include a next generation design improving on what was learned in Phase I, for material selection, fabrication methods for seams and corners including interleaving and layer thermal matching, and building and testing prototypes in realistic environments such as a 500 liter cryotank.

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Illuminex Corporation proposes a NASA Phase I SBIR project to develop high performance, lightweight, low-profile heat pipes with enhanced thermal transfer properties enabled by utilizing copper nanowire arrays as the wick material in the heat pipe. Thermal management is a critical issue for advanced electronic and optical systems as current cooling techniques are being rapidly outpaced by the heat load of new technologies. Superior thermal control technologies are needed both for NASA's science spacecraft components and commercial products such as computers and medical lasers. The incorporation of nano-structured materials in heat pipe manufacturing will allow the development of thermal management devices with increased heat dissipation efficiency and a reduced size and weight profile as compared to currently utilized cooling approaches. Illuminex will develop processes to engineer the nanowire wick directly onto the heat pipe package, and using this approach, it s envisioned that heat pipe systems can be manufactured directly into the housings of devices requiring advanced thermal management. This nanotechnology enabled miniaturization can be further size reduced to near the MEMS level for cooling micro-electronics and sensors. Phase II will lead to full commercialization and manufacturing of high performance, low profile, and lightweight heat pipes.

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In this Phase II effort Toyon will increase the state-of-the-art for video/image systems. This will include digital image compression algorithms as well as system level integration, encompassing the image sensor all the way to compressed imagery data transport. To accomplish these goals Toyon will design a complete FPGA-based video compression system. The novel aspect of this design lies in the dynamically reconfigurable hardware IP cores that will interface to an embedded processor. Similar to a software defined radio (SDR) system where separate RF waveforms are loaded at runtime, Toyon aims to reload separate image compression encoders. This enables the use of several different image/video compression standards, all on the same hardware platform. The dynamically reconfiguring architecture of this system enables a single image sensor and hardware platform to handle the two most common space video camera applications, while still maintaining low power consumption in a highly integrated package. First, H.264 for high framerate, real-time video for situational awareness and surveillance. Second, lossless JPEG200 encoding for scientific and research post-processing. However, due to limited funds for this Phase II design, we will most likely work with a purchased H.264 IP core along with a standard JPEG compression core, which Toyon developed on the Phase I of this program. Providing the capability to reconfigure for both motion video and still image compression will provide near-term utility and demonstrate feasibility for Phase III development. Toyon will target the solution to a custom fully radiation hardened hardware platform. Potential radiation hardened components include a Xilinx FPGA, Xilinx PROM, Atmel SRAM memory, Aeroflex voltage regulators, and a Cypress CMOS image sensor paired with space-ready optics.

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Advanced Materials Technology, Inc (AMTI) responds to the Topic X9 entitled "Propulsion and Propellant Storage" under subtopic X9.01, "Long Term Cryogenic Propellant Storage, Management, and Acquisition". The proposed program will focus on developing new multifunctional insulation materials that will impact cryogenic systems for space transportation orbit transfer vehicles, space power systems, spaceports, spacesuits, lunar habitation systems, robotics, and in situ propellant systems. These innovative materials will be capable of retaining structural integrity while accommodating large operating temperatures ranging from cryogenic to elevated temperatures conditions. These advanced materials can be incorporated into thermal protection systems (TPS), reducing the amount of TPS and its structure. To meet and exceed the NASA's requirements, we propose to develop multifunctional organic/inorganic nanocomposites foams for structural and insulation applications offering affordable cost, lightweight, and high strength, low thermal conductivity, high thermal stability, and easy processability which will result in improved efficiency and reliability of the cryogenic systems. The approach proposed in this program will provide with more flexibility in designing cryogenic insulators. Once the feasibility of the concept of strong, lightweight cryogenic insulating materials is demonstrated in Phase I, we shall scale-up this concept in a Phase II program to meet the NASA's requirements.

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Environmental control systems for manned lunar and planetary bases will require condensing heat exchangers to control humidity in manned modules. Condensing surfaces must be hydrophilic to ensure efficient operation and biocidal to prevent growth of microbes in the moist, condensing environment. The coatings must be extremely stable and adhere to the condensing surface for many years. We propose an innovative coating that has proven to be highly biocidal, hydrophilic, and stable. In Phase I we have proven feasibility by developing methods to apply the coating to prototypical materials and demonstrating hydrophilic and biocidal performance under prototypical conditions. In Phase II we propose to optimize the coating and demonstrate the performance of prototypical condenser surfaces designed to meet requirements for future lunar and planetary bases.

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The objective in this project is the development of a monochromatic x-ray source for a small x-ray Photoelectron Spectrometer (XPS) suitable for NASA missions. This instrument will allow in situ elemental and chemical state measurements in off-earth NASA missions. The need for these measurements is for understanding resource availability, toxicity, and chemical issues like oxidants on Mars. The small XPS developed in a previous SBIR, NNC04CA20C, has a mass of 15 Kg and will reduce to 7 kg as refined for flight. It will operate with about 10 watts. This tool needs a monochromatic x-ray source for the capability to understand the chemistries expected on NASA missions as called out in Future Space Science Enterprise (SSE) missions. In Phase I for this proposal we designed a combination of sources that will accomplish this need. It uses both a monochromatic and a non-monochromatic x-ray source to provide the quality data needed at a data rate suitable for potential missions. It uses low power, has a small mass and has some redundancy to reduce risk. Non-NASA applications will be process monitoring for semiconductor, polymer films and bioprocesses manufacturing. This application will be made available by the small size

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We propose to build and evaluate NDIR Analyzers that can be used to observe Eddy Covariance Flux and Absolute Dry Mole Fraction of CO2 from stationary and airborne platforms for a great range of environments. Both open- and close-path analyzers are to be evaluated. Phase I succeeded in building a fast CO2 analyzer with 100 Hz modulation frequency and sensitivity within a factor of two of the target value of 100 ppb. For Phase II, we propose upgrades to the technology that are designed to reach that target sensitivity. We are further proposing individual projects within restricted airspace that will demonstrate the potential of the technologies for significant kinds of observations for Observational Climate Change. Two robotic platforms are to be utilized, the Unmanned Airborne Vehicle (UAV) and The Portable Tower Observatory (PTO). The PTO will provide fluxes and eddy spectroscopy of CO2. The UAV will give CO2 eddy spectroscopy that can be compared for a range of practical heights (5- 30 m) of the PTO. Samples of air are to be dried, and the site is chosen to minimize the impact of H2O vapor on this first deployment of the technologies.

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The Grain Boundary Engineering (GBE) approach, successfully demonstrated in Phase I, that microstructural optimization provides a very significant improvement in reducing susceptibility to intergranular crack initiation and growth in conventional wrought Inconel 718. The principal objective of the Phase II research development program is to extend the applicability of the GBE technology from conventional wrought superalloys to more advanced powder metallurgy (PM) alloys, and in particular, the Low Solvus High Refractory (LSHR) developed by NASA. In addition, the program also includes a limited effort to optimize the GBE process for application to wrought Inconel 718Plus. The phase II program will build upon the success of the phase I effort, and will have the following specific technical objectives: (1) develop and optimize GBE processing strategies for optimizing the bulk microstructure of an advanced PM disk alloy developed by NASA (i.e., LSHR) and Inconel 718Plus, (2) develop a cost-effective GBE processing strategy for locally optimizing the microstructure of the PM alloy (i.e., LSHR) at the near surface, and (3) evaluate the mechanical properties of the GBE-processed alloys and benchmark with properties of their conventional counterparts.

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Creare proposes to develop a novel, laser-assisted, pre-finishing process for chemical vapor deposition (CVD) coated silicon-carbide ceramics. Our innovation will enable the affordable single-point turning of CVD silicon carbide from a near-net shape blank to a pre-finished aspheric optic. We will use our extensive experience and expertise in the advanced machining of ceramics to establish the parameter space for the production of high-quality, pre-finished aspheric optics from near-net shape blanks. Our innovation has a material removal rate (MRR) that is two orders of magnitude higher than current pre-finishing options including diamond grinding, ductile-regime machining, reactive atom plasma processing, or standard laser micromachining. In addition, our approach has demonstrated that these high MRRs can be achieved with no surface or sub-surface damage, which is key to minimizing the cost of the subsequent finishing operation. Our novel solution is readily integrated with existing or new ultra-precision machine tools. Thus, our innovation is effective, affordable, and flexible.

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The objective of this proposal is to study and demonstrate novel GaAsNP/GaP/AlGaP technology for use in extreme photovoltaic (PV) energy conversion. NASA and the scientific community are interested in solar missions that go as far as Saturn or even into near sun conditions. Such missions present a challenging problem for PV technology. In addition to the requisite high efficiency and reduced solar cell payload mass, these missions require a PV technology that can withstand the increased solar intensity, radiation and temperature. We propose studying two possible solar cell designs: The first design utilizes novel, wide gap GaP-based materials to provide bandgaps well suited for high-temperature operation and to enhance function in high radiation and near sun missions. Such an approach will enable solar cells to operate at and above 450 Celcius with the highest possible efficiency. As part of this study we would investigate the deposition of AlGaP on GaP to provide materials with bandgaps at or above 2.4 eV. The second design we will investigate uses more standard materials that EpiWorks has already developed for different applications. This design would employ InAlP (2.4eV bandgap) lattice-matched to GaAs as the key wide gap material. We will study the expected temperature dependence and other key thermal properties of such a design and compare to the GaP-based approach.

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The principal Phase II objective is to refine and further develop the prototype PCHP into a useful thermal management tool. The Phase I program established the feasibility of thermal control an axially-grooved heat pipe with a variable-volume reservoir. The follow-on Phase II program will address control system optimization, component longevity, reductions in mass and power, and show that the device can be flight qualified. It is expected that the Phase II results will bring the PCHP to TRL 6: Prototype Demonstration in a Relevant Environment.

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Long range, RF space communications do not meet anymore the bandwidth requirements or power constraints of future NASA missions. Optical communications offer the potential to dramatically increase the link bandwidth and decrease the emitter power. High-bandwidth, long-range optical communications require reliable high-gain, photon-counting detectors operated at moderate cooling with high detection efficiency, large aperture, sub-nanosecond temporal resolution, low intrinsic noise, and capability to handle large optical background. These requirements have not been met yet by single detector designs. We propose to develop a novel large area, photon-counting detector in infrared, operated with moderate cooling, gain greater than 10^6, detection efficiency greater than 50%, 100 MHz saturation counting rate, at least 500 MHz bandwidth, and configurable area. The approach is to develop compact, photon-counting detector arrays based on designs processed in high-volume manufacturing with validated reliability and infrared converters processed on large silicon wafers. This innovation provides a simple solution to high-bandwidth ground-space and space-space optical communications by mitigating optical aperture ? additive noise requirements. In Phase I, we will investigate the integration of the infrared converter into the photon detector processing flow, and will develop the electronics to increase the detector bandwidth and its saturation-counting rate.

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The recent performance increases in graphics processing units (GPUs) have made graphics cards an attractive platform for implementing computationally intense applications. With their numerous parallel computational pipelines and SIMD architecture, modern GPUs can outperform high-end microprocessors by one to three orders of magnitude, depending on the problem. Most work to date at EM Photonics and elsewhere has focused on accelerating specific applications by porting core engines onto the GPU. In this project, we propose the development of general purpose computational libraries capable of solving numerous core numerical functions on commodity graphics cards. These solvers will be based on accepted, industry-standard interfaces and will be easy to integrate with current and future applications. The result will be a GPU-based numerical coprocessor capable accelerating a wide range of computationally intense functions, thereby reducing processing times in applications where numerical computations are the primary bottleneck.

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This proposal is for a flexible navigation system for deep space operations that does not require GPS measurements. The navigation solution is computed using an Unscented Kalman Filter that can accept any combination of range, planet chordwidth, and angle measurements using any ce- lestial object. The UKF employs a full nonlinear dynamical model of the orbit including gravity models and disturbance models. The filter will estimate both states and parameters. The integrated system employs a sensor that uses novel image processing to extract planetary chordwidths. The extra-solar system body sensor will employ band limiting imaging with the band selected to maximize reliable autonomous object identification.

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NASA often must deal with the issue of protecting EMI sensitive payloads and instrumentation from damage due to radiated energy. Many of these EMI sensitive payloads can be damaged by seemingly benign sources such as communication networks or microwave ovens. The problem becomes more difficult when these sensitive payloads and instrumentation require movement from one location to another. It is extremely difficult and time consuming to identify and characterize the potential threat to these payloads with current tools and techniques. Soneticom proposes to utilize a small network of sensors to quickly and efficiently identify and locate sources of EMI radiation. Once the source is located Soneticom will utilize available signal parameters such as Received Signal Strength (RSS) at each sensor to estimate the signal strength at any point within the network's coverage area. Figure 2.1 is a conceptual diagram of how this innovation might look once displayed on a map. Soneticom will utilize the existing Lynx Geolocation platform which has the capability to identify and locate an EMI radiation source in the 20 MHz - 30 GHz range. The Lynx system will provide the hardware platform to develop algorithms required to estimate the signal strength across the network's coverage area

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In this proposed SBIR project, we seek to implement the Adaptive Chemistry methodology in existing CFD codes used to investigate the emissions performance of gas turbine engine combustors. We will demonstrate the feasibility of integrating Adaptive Chemistry algorithms to current CFD codes. We will also further develop the Adaptive Chemistry method to take advantage of species reduction enabling even larger CPU speedups. The value of the technique is enhanced predictive capability and computational efficiency of existing CFD codes for reacting flows such as gas turbine engine combustion systems. The successful completion of this project will produce the first CFD numerical code that is able to model detailed chemical kinetics as well as fluid dynamics. The end results allow the user to easily and transparently control the balance between computational efficiency and solution accuracy.

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The potential benefits of Large Eddy Simulation (LES) for aerodynamics and combustion simulation hvae largely been missed, due to the complexity of generating grids for complex topologies, and the requirement for boundary fitted grids which reduce the accuracy of the method. The Phase 2 Program builds on the Cartesian grid LES flow solver developed under Phase 1, and includes new techologies such as immersed boundary conditions, multigrid code acceleration, compressibility, and advanced subgrid scale models for turbulence and combustion. Experimental validation cases using NASA-sponsored experiments, and using actual aeroengine combustor hardware will be performed, comparing the LES flow solver results with experimental combustor exit temperatures, and with other code predictions, providing a unique opportunity for validation of the flow solver.

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Future planetary exploration missions such as those planned by NASA and other space agencies over the next few decades require advanced chemical and biological marker measurement technologies that will help answer fundamental questions about the composition of the Solar System and the possibility of past and present extraterrestrial life. Electrical/electrochemical array-based systems are highly suited for space and terrestrial applications because of their robustness, high-sensitivity, low-power requirement, inherent miniaturization capability through microfabrication, and diverse transducer mechanisms which permit detection of a broad range of chemical and biological targets. Scribner Associates will leverage its expertise in analytical instrumentation for arrays and impedance spectroscopy to develop an advanced array impedance analyzer for use with existing (e.g., Mars Oxidation Instrument) and future chemical and biological sensor arrays for planetary exploration. The instrument will be versatile: It will be capable of conducting DC and multi-frequency AC impedance measurement of arrays with large numbers of sensing elements. Successful development of the impedance array analyzer will facilitate multiple mission deployments with arrays tailored to specific mission objectives therefore ensuring efficient investment of NASA resources.

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Wireless transceivers used for NASA space missions have traditionally been highly custom and mission specific. Programs such as the GRC Space Transceiver Radio System (STRS) seek to abstract the radio waveform from the hardware platform itself; this is meant to improve flexibility and promote component and subsystem reuse. In this Phase II effort Toyon proposes to perform work that will advance the state of the art in reconfigurable wireless transceivers in order to help realize the vision of STRS. Specifically, we propose to develop a modular, but highly integrated, digital and analog signal processing platform along with a standards-compliant waveform. The space-ready reconfigurable radio will serve a range of NASA missions and can be easily modified or enhanced for future needs. The RF front-end will be direct conversion with high integration of the frequency translation subsystems. For digital processing, we will pursue a system-on-a-chip (SoC) design with both reconfigurable logic and a soft-core processor implemented in a radiation-hardened Xilinx FPGA and PROM. The entire system architecture will leverage an EXP board-to-board connector design developed in Phase I. This system concept was validated in Phase I through Toyon's demonstration of a fully-functional packet-based 500 kbps waveform. In Phase II Toyon will pursue development of a waveform that is standards-based in order to further promote reuse and interoperability. Specifically, Toyon will develop a baseline implementation of the IEEE 802.16a standard. In addition to physical layer connectivity, such a waveform is well suited to IP-based networking, easing integration and increasing portability.

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Astronauts lose approximately 1-1.5% of their bone mass per month during space travel due to a lack of physical stress in the microgravity environment. Although, no effective treatments or prophylactic regimens have yet been defined, it is important to monitor the bone loss process in space. As such, the sensor must be compact and facile to operate. Therefore, OpTech proposes to extend its already successful and patent-pending competitive fluorescence resonance energy transfer (FRET)-aptamer assay technology to the detection of bone loss and formation markers such as osteocalcin fragments, hydroxylysine, hydroxyproline, C-terminal and N-terminal telopeptides. In Phase I, OpTech will develop, clone and sequence aptamers to each of these markers. OpTech will also incorporate fluorophore-labeled dUTP into the sequenced aptamers by asymmetric PCR and complex them to their quencher-labeled bone markers for testing in buffer, animal sera, and urine. Finally, in Phase I OpTech will dry and reconstitute the assays that will be tested using a commercially available handheld, battery-operated fluorometer and validated using OpTech's spectrofluorometer. In Phase II, the FRET-aptamer assays will be optimized and packaged in special leak-proof sealed plastic cuvettes and delivered to NASA along with the handheld fluorometer for testing on the ISS or other space missions.

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Paragon Space Development Corporation proposes to develop a single-loop, non-toxic, active pumped radiator design with robust, reliable operation near stagnation regimes as expected to be experienced by NASA's Orion Crew Exploration Vehicle (CEV), the Lunar Surface Access Module (LSAM) and thermal control systems of the Lunar Base at the lunar pole. This will be achieved through an innovative use of a common terrestrial-application, safe fluid that has lower temperature stalling characteristics over typical space-based radiator fluids. Phase 1 has already shown this fluid to stall per predictions and, through a previous contract, Paragon has demonstrated its capability to perform spacecraft heat rejection. The significance of this work is to understand stagnation behavior, both planned and mitigated, and then design and demonstrate a robust and reliable radiator performance based on this knew found knowledge.