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There is a defined need for long term earth based testing for the development and deployment of two-phase flow systems in reduced-gravity, including lunar gravity, conditions. The proposed study intends to develop a scaling methodology to meet this requirement. A hierarchical two-tiered scaling approach will be used to obtain scaling relations for an entire system (integral scale), individual components of the system and local phenomena. The final product of the Phase I effort will be a rigorous scaling methodology along with important non-dimensional numbers which can be used for developing earth-based systems to study reduced-gravity two-phase systems and/or phenomena. The feasibility of the approach will be demonstrated in Phase I by using data available in literature that has been acquired in reduced-gravity as well as earth based conditions. As part of Phase II a scaled experimental facility will be designed and confirmatory experiments performed.

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This SBIR program will identify and address the primary technical issues that limit the current precision of replicated CFRP optics. These issues must be resolved to bring this capability to the sub-micron range of precision required by the next generation of flight and ground submillimeter and far infrared projects. Were these issues resolved, this capability would provide reduced cost and risk and improved areal density, thermal stability, and stiffness to the large sub-micron optics required by the next generation of flight and ground submillimeter and far infrared projects.

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High Actuated Primary Mirror to Enable Prime Focus Coronograph Telescope Project

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One of the main attributes contributing to the civil competitiveness of rotorcraft, is the continuously increasing expectations for passenger comfort which is directly related with reduced vibration levels and reduced interior noise levels. Such expectations are amplified in the VIP market where people are used in the acoustic and vibration levels of civil and executive jets. One of the most critical excitations for interior noise in helicopters is the one from the gearbox. Thus, the structure-borne noise path (i.e. excitation propagating from mounting locations through the fuselage structure to the panels of the cabin and to the interior) must be captured in rotorcraft interior noise computations. This proposal addresses the need stated in the solicitation for developing physics based tools that can be used within a multi-disciplinary design-analysis-optimization for computing interior noise in rotorcraft applications. The hybrid FEA method can be used for structure-borne helicopter applications and can be integrated very easily (due to the finite element based model) with models from other disciplines within a multidisciplinary design environment. During the Phase I project the main focus will be in demonstrating the feasibility of the hybrid FEA technology for computing rotorcraft structure-borne interior noise from gearbox excitation. A multi-discipline optimization rotorcraft case study will also be performed for demonstrating how the hybrid FEA facilitates the design of a rotorcraft fuselage based on simultaneous crash landing/passenger safety and structure-borne noise considerations. The new developments will become part of MES' commercial EFEA code and of its implementation within SOL400 of NASTRAN. UTRC will participate in the proposed effort for ensuring relevance of the work to rotorcraft interests and for providing technical consultancy.

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Future instruments and platforms for NASA space applications will require increasingly sophisticated thermal control technology, and cryogenic applications will become increasingly more common. For example, the Single Aperture Far-IR (SAFIR) telescope and other cryogenic telescope missions must provide distributed cooling and multiple heat lift. Also, the management of cryogenic propellants requires distributed cooling through integrated heat exchangers for zero boil-off, densification and cooling of structural members. To address these requirements, we propose to develop a lightweight, continuous-flow cooling loop that can provide cooling and temperature control to multiple, distributed loads. This approach allows relatively simple mechanical and electrical integration and maintains high refrigeration system efficiency. The basis of the loop is a rectifying interface that converts the oscillating pressure that characterizes the operation of a regenerative cryocooler into a quasi-steady pressure difference that can be used to drive a continuous flow of cold gas over distances of several meters. The rectifying interface has the potential secondary benefit of rapid and therefore precise load temperature regulation of multiple sensors or structures using actively controlled throttle valves to regulate the local gas flow.

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Robust Flow Control For Radically Enhanced Natural Laminar Flow Wings Project

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The proposed work focuses on implementing fast-response pressure-sensitive paint and Surface Stress Sensitive Films for measurements of unsteady pressure and skin friction in rotorcraft applications. Significant rotorcraft problems such as dynamic stall, rotor blade loads in forward flight, and blade-vortex interaction all have significant unsteady pressure oscillations that must be resolved in order to understand the underlying physics. Often these unsteady pressures are difficult to resolve in the rotating frame due to difficult installation of pressure transducers, and data is available only at discrete points. Pressure-sensitive paint formulations have been developed to provide surface pressure information in situations such as this, but conventional PSP formulations have slow response times. Conventional skin friction measurements, for example oil flow, do not offer significant frequency response. In order to improve the frequency response characteristics of PSP, sprayed porous paint binders have been developed for measurement of unsteady pressures. Fast-responding Surface Stress Sensitive Films provide both quantitative skin friction and qualitative flow visualization measurements. These techniques can provide high-spatial-resolution, time-resolved pressure and skin friction information that will provide unparalleled insight into the physical mechanisms driving certain rotorcraft problems. Both of these techniques will be demonstrated in Ohio State's unique 6"x22" transonic wind tunnel, where an airfoil may be tested for dynamic stall simulation in compressible flow. Successful demonstration of fast-responding PSP and S3F on a dynamic stall test in the 6"x22" tunnel will serve as a proof of concept that will allow transition of the technologies into larger-scale wind tunnels at NASA and elsewhere.

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The new exploration initiative, and the planned new antenna types to be developed in support of that initiative will increase the number and complexity of missions to be supported by the NASA Space Communications infrastructure. In a new concept, the communications architecture will evolve from the present centralized system to one where user/missions will be given direct control of communication schedules, allowing them to directly change requests, while working with other user/missions to solve scheduling conflicts in a collegial environment. A radically new user interface paradigm will be needed to support this new approach. It is our contention that such an interface is best designed using intelligent agent technologies, resulting in an intelligent space communications scheduling agent for each user/mission. In Phase 1 we demonstrated the feasibility of using the Distributed, Collaboration and Interaction (DCI) intelligent agent software to support key activities of user schedule representatives of the Deep Space Network (DSN). These agents used models of mission preferences for preparing requests and posting notifications, and took actions on the part of the user to resolve schedule conflicts and take advantage of unexpected asset availability. In Phase 2 we will extend our prototype agents to support the full range of user scheduling activities, to add capabilities to support multi-user conflict management and to design them to integrate with DSN Service Scheduling Software as it evolves to support user/missions. We will also investigate the potential of using software agents to support the space and ground networks.

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Thermacore Inc. proposes an innovative titanium heat pipe thermal plane for passive thermal control of individual cells within a fuel cell stack. The proposed technology eliminates actively pumped liquid coolant loops, which improves system efficiency, reliability, safety, simplicity, life cycle as well as saves weight and volume. Although the main purpose for this technology is thermal management of fuel cells for space applications, the same technology can be applied for electronics cooling: heat spreaders and heat sinks, where thin design is required. The proposed titanium heat pipe thermal plane will be reliable passive heat transfer device with the following parameters: bulk density: under 3 grams per cubic centimeter, thickness: less than 0.050 inches, effective thermal conductivity: in excess of 2,000 W/(m K), electrical resistivity: less than 0.2 ohms-cm, operation against gravity: 4 inches

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Cytometer on a Chip Project

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We propose to develop a compact portable longwave camera for astronomical applications. In Phase 1, we will develop and deliver the focal plane array (FPA) - a crucial camera component. In Phase 2, we will integrate the FPA with electronics and optics into a compact package and deliver the resulting camera to NASA for field testing.

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Fuel Cell/Li-ion Battery Hybrid Power System for Space Suits Project

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Makel Engineering, Inc. (MEI) and the Pennsylvania State University (Penn State) propose to develop and demonstrate a microchannel methanation reactor based on nanofabricated catalysts. Sustainable/affordable exploration of space exploration will require minimization of re-supply from Earth by implementation of In-Situ Resources Utilization (ISRU) strategies. For exploration of the Moon, one of the most significant resources is the lunar regolith, which is a complex mix of minerals with large oxygen content in their composition. Oxygen finds its main uses as a propellant, and for life support systems. There are currently many technologies being developed addressing the production of oxygen from lunar regolith, including carbothermal processes. The key to sustainability is to make sure any consumables carried from Earth are recycled to the maximum extent possible, minimizing the need of re-supply. In the case of carbothermal based oxygen production, carbon oxides must be converted to methane for reintroduction in the carbothermal system. This proposed program specifically addresses topic X3.02 Oxygen Production from Lunar Regolith, by developing a methanation system that will efficiently convert mixed carbon oxides and hydrogen to methane and water.

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To address the NASA Earth Science Division need for spatial filter arrays for amplitude and wavefront control, Luminit proposes to develop a novel polarization-preserving Integrated Spatial Filter Array (iSFA) comprising 36 x 36 waveguides and two microlens arrays in a hexagonal configuration. Each waveguide acts as a polarization maintaining single-mode fiber and is precisely mapped to a pair of input/output lenslets. The 36 x 36 waveguides have identical fast and slow polarization axes and can be mass-fabricated to reduce cost and enhance placement accuracy, uniformity, throughput and reliability. The iSFA will be hermetically packaged in a 1 cubic inch box to withstand high radiation and temperature extremes in space. In Phase I, we will demonstrate the feasibility of iSFA, which will reduce the development risk of a Phase II 36 x 36 prototype iSFA. The demonstrated results will offer NASA enhanced nulling coronagraph imaging for detection of planets beyond our solar system with the Terrestrial Planet Finder.

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The objective of this proposal is to demonstrate the feasibility of producing an integrated starting model for gas turbine engines using a new physics-based combustion dynamics model that accurately simulates flow interactions among the compressor, combustor, and turbine. Replacing conventionally costly guess-and-test techniques, this new process for starting system analysis, design, and optimization promises a new generation of predictive capability that will allow system engineers to design engines with higher fidelity and eliminate the need for multiple iterations and testing cycles found in current industry practice. EcoPro Technologies' physics-based starting model is built from an innovative solution algorithm which solves the 1-D speed-dependent conservation equations of mass, momentum, and energy for each starting system component. From this integrated algorithmic model, we will be able to achieve predictive capabilities for the most vital engine dynamics, including starting/transient instabilities of combustor flameout, compressor surge and over-temperature shutdowns. Our integrated design tool allows for complex starting simulations, thus enabling successful engine design and modeling with rapid determination of sensitivities with respect to all engine design variables and constraints. This empowers engineers to choose optimized design directions without violating constraints and make appropriate design changes to engines prior to costly manufacturing and testing.

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Studying the isotopic composition of materials is an established method to obtain detailed insight into formation and evolution processes in our Universe. Water may play a dominant role in unraveling these processes. Isotope hydrology applied in situ on the Moon and other planets might develop into the key method to understand the history of our Solar system. The Moon provides unique opportunities to study trapped volatile compounds, like water, due to the special conditions at its poles. These conditions enable the long term storage of volatiles and preservation of their isotopic composition. A compact, precise isotope hygrometer operated on the Moon will be an invaluable tool if abundant water sources are found on the Moon in upcoming missions. This project seeks to develop a highly sensitive, portable water isotope ratiometer for precisely measuring water samples in situ on the Moon. The optical sensors developed on this project will have unique features including fast response, high precision and strong species selectivity. Design criteria such as a small footprint, low weight, low power consumption and continuous sensor health monitoring will be implemented to optimize the sensors for application to the Moon. An absorption approach using modulation techniques will be implemented on a lunar mission suitable platform.

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The exploration of space requires that new technologies be developed for long-term cryogenic propellant storage applications in-space, on the lunar surface, and on the Earth. The Altair ascent stage requires LO2 and LCH4 storage durations of up to 14 days in LEO and up to an additional 210 days on the lunar surface. Long term storage (224 days) of LO2 cryogenic propellant on the lunar surface is required to support space power systems, spaceports, spacesuits, lunar habitation systems, robotics, and in situ propellant systems. Long term storage (6 months) of LO2/ LH2/ LCH4 cryogenic propellants in 1-g on the surface of the Earth with minimal propellant loss is required to support launch site ground operations. Thus, this proposed project will focus on improving the strength of aerogels, which are the lightest weight and best cryogenic insulation material known. Improvements in the strength of aerogels would allow these materials to be used as advanced non-compacting insulation materials capable of retaining structural integrity while accommodating large operating temperatures ranging from cryogenic to elevated temperatures. The properties of the aerogels will be tailored by controlling their densities and strengthened by reinforcing them with fibers and with organic polymer crosslinking agents.

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One of the highest priorities in Environmental Control and Life Support (ECLS) for longer missions is to recover and process wastewater to provide clean water. There is an important need for a total organic carbon (TOC) sensor to assure that the organic chemical content of water environment of the astronaut crew habitat falls within acceptable limits, and that the chemical life support system is functioning properly. For longer missions, water monitoring requires sensitive, fast response, online analytical sensors. Lynntech has successfully developed a novel regenerative TOC analyzer for real-time monitoring of water quality with an operational lifetime of 5 years with no maintenance required and no need to supply reagents. In addition, the TOC analyzer was flight-qualifiable and microgravity-compatible. This proposal concerns further development of the TOC analyzer as a compact online analytical sensor utilizing (i) electrochemical components producing two key elements in TOC analysis, acid and oxidant; (ii) photolysis/photocatalysis for the complete oxidation of organic carbons to carbon dioxide; and (iii) mesofluidic design. During the Phase I effort, the feasibility of the proposed system and approach will be demonstrated. A prototype will be designed, fabricated, tested, and delivered to NASA during the Phase II project.

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The innovation proposed here is a digital array gas radiometer (DAGR), a new design for a gas filter correlation radiometer (GFCR) to accurately measure and monitor CO2, CO, CH4, N2O and other key trace gases in the boundary layer from space, aircraft or ground-based platforms. GFCR is a well-known and proven technology for trace gas detection and monitoring. However, its effectiveness in downlooking applications has been limited, primarily because variations in surface albedo degrade the performance. Our DAGR approach builds on traditional GFCR concepts and combines several new key elements: two-dimensional detector arrays, pupil imaging (imaging the aperture), and a novel calibration approach. With these enhancements and appropriate signal processing, the DAGR design overcomes the historical limitations of GFCR in downlooking applications. In addition, this design significantly boosts the sensitivity and expands the dynamic range traditionally available to these sensors. Finally, the innovation provides a calibration technique that nearly eliminates errors due to detector drift effects. The result will be a compact, static, robust system that can accurately measure important boundary layer species from a variety of platforms.

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We propose to implement novel physics mining algorithms with analytical capabilities to derive diagnostic and prognostic numerical models from multi-source observational data. These techniques yield higher-resolution measures than ever before of environmental parameters by fusing synoptic imagery and time-series measurements. These techniques are general and relevant to observational data, including raster, vector and scalar, and can be applied in all earth and environmental science domains. Because they can be highly automated and are parallel, they scale to large spatial domains and are well-suited to change and gap detection. This makes it possible to analyze spatial and temporal gaps in information and facilitates within-mission re-planning to optimize the allocation of observational resources. As a demonstration project, we have selected a standard climatological metric and will show that we can generate an analogue of this metric by using our method. In particular, we will use the MineTool algorithms to derive an analogue for Palmer's Drought Severity Index. We will compute this index for a region of the western United States using a set of archival terrestrial products (e.g., Landsat, AVHRR, Aqua/Terra) and a set of weather and climate products (e.g., NOAA satellites, federal, state, local hydrological time-series). Then, using the same dataset, we will produce a physics-based model from the MineTool analysis of the data.

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Both pyrolysis and oxidation steps have been considered as the key solid waste processing step for a Controlled Ecological Life Support System (CELSS). Pyrolysis is more amenable to handling mixed solid waste streams in a microgravity environment, but produces a more complex product stream. Oxidation (incineration) produces a simpler product stream, but the oxidation of mixed solids is a complex unit operation in a microgravity environment. Pyrolysis is endothermic and requires no oxygen, while oxidation is exothermic and requires oxygen. A previous NASA SBIR Phase I and Phase II project has successfully integrated pyrolysis of the solid waste and oxidation of the fuel gases into a single, batch processing prototype unit. This Small Business Innovation Research Phase I project addresses the feasibility of integrating pyrolysis, tar cracking, and oxidation steps into a compact, efficient system for processing of spacecraft solid wastes. This integration will result in a reduction in energy consumption, an overall reduction in system complexity, and a lower Equivalent System Mass (ESM). The objective of the Phase I study is to demonstrate the feasibility of this integration process using bench scale experiments. This will be accomplished in three tasks: 1) design and construct integrated bench scale unit; 2) laboratory studies using simulated solid waste sample; 3) evaluation of laboratory results and preliminary design of Phase II prototype.

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Busek proposes to develop a radio-frequency discharge, gridded micro ion engine that produces 5N level of thrust precisely adjustable over a wide dynamic thrust range. Rf discharge was chosen to eliminate the life-limiting internal cathode of a dc discharge ion engine. Thrust actuation on the order of 0.035N resolution is proposed with a closed-loop control system. This controlling scheme can be achieved by varying only one parameter: the rf power with a feedback from the beam current. Uniquely, the rf ion engine can also produce enough thrust for coarse constellation corrections or reconfigurations. Argon will be the base-lined propellant to ease concerns of propellant condensing on optics or other cryogenic surfaces. This feature can be critical for close formation flying as micro-thrusters such as field emission electric propulsion (FEEP) and colloids could potentially coat neighboring spacecraft. The proposed rf ion engine, combined with Busek's space-qualified carbon nanotube field emission cathode (developed for the ST7 DRS mission) as a neutralizer, will create a new opportunity in precise thrust actuation. Further implementation of a simple propellant feed system and power electronics will create a compact, low power, high performance spacecraft propulsion system.

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Life on Earth is unique in many ways; one of its great mysteries is that the building blocks of life on Earth (amino acids, nucleotides, sugars) are all chiral. One optical isomer of each amino acid or nucleic acid was selected by evolution. In our pursuit of finding life on Mars and beyond (Triton, Europa, etc.), it is likely that one of the clues to extant or extinct life could be the detection of non-racemic chiral molecules. This proposal describes the development of a highly miniaturized and ultrasensitive lab-on-a-chip polarimeter that will meet the NASA need to measure chirality in very small volumes of samples at very high sensitivity. The proposal builds on a novel technology that is based on a proprietary design, in which a modulated liquid crystal variable retarder (LCVR) enhances sensitivity and reduces size without sacrificing performance. This detection principle with a long-path-length microfluidic flow cell allows for the measurement of chirality in microliter volumes of samples. The Phase I effort has conclusively demonstrated the technical feasibility of the detection principle. A miniaturized polarimeter with microfluidic flow cell was designed and fabricated. The polarimeter was calibrated and tested with samples. In Phase II, we will build, fully characterize, and deliver a miniature polarimeter with optimized performance, enhanced mechanical stability, and integrated fluid handling capability. The primary goals are to further improve the polarimeter's sensitivity, accuracy, size, weight, reproducibility, measurement speed, and power needs, conduct extensive testing, and deliver a robust prototype, engineering drawings, software, and test results to NASA.

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This topic is designed by NASA lead agency Ames Research Center to address technologies that would enable a safer and more reliable space transportation capability. NASA is seeking innovative technologies including sensors and communication which expedite launch range clearance. Needed is equipment that will provide real time situation awareness for safe range operation from processing to launch and recovery. Proposed herein is a very small, low cost, high resolution, dual-mode lightweight sensor for remote detection, recognition, and identification of persons and objects that have intruded into areas of the identified range. The dual-mode sensor combines high resolution millimeter radar with high resolution electro-optical sensor. The proposed sensor is low cost and compact, meeting size, weight, power, and stability requirements for a variety of platforms, including unmanned vehicles, buoys, and high altitude air ships.

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This Small Business Innovation Research Phase I project will develop a compact, rugged, rapidly and widely tunable laser based on a quantum cascade diode laser at mid-infrared wavelengths. The key innovation in this effort is the use of an engineered electro-optic tuning element in an external cavity laser to provide control of the laser wavelength through an applied voltage. AdvR has previously demonstrated the feasibility of large tuning range matching that of mechanically tuned lasers, yet also offering low cost, smaller size, robustness, portability, and tuning speed that is faster by six orders of magnitude. The Phase I effort will investigate adapting the external cavity tuning techniques to quantum cascade lasers to generate tunable wavelengths for mid-infrared spectroscopy.