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<p> The workshop will have three main objectives. The first will be to inventory the signatures and measurements that are desirable to make using submillimeter active systems. The second will be to derive the minimum requirements that would make such measurements competitive relative to the present state of knowledge. The third and final one will be to compare what is needed relative to the presently available capability to determine where immediate opportunities are, where short term investment could generate opportunities and areas where breakthroughs are still necessary before suitable systems could be built. There is a great deal of expertise distributed between various groups doing different kinds of research that does not generally lead to a discussion of possibilities outside the research area. The workshop will bring these diverse groups together with the intention of exploring the entire parameters space of scientific and technical possibility. Some potential applications include characterization of aerosols and particulates in atmospheres, dust in the solar system, molecules in atmospheres or exospheres, materials characterization, non-invasive inspection and remote surface characterization. The workshop will collect potential advocates and align them with those developing technology to illuminate areas where technological advances would lead to systems and to areas with systems leading to new science could be proposed using existing technology.</p>

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<p> Develop advanced on-board processing to meet the requirements of the Decadal Survey missions:<br /> advanced instruments (hyper-spectral, SAR, etc) require advanced on-board processing to facilitate the timely conversion of ES “data” into ES “information”<br /> mission enabling technology to reconfigure/adapt on the fly; detect and react to events; produce data products on-board for direct downlink, quick look, and “first responder” real-time awareness; enable “sensor web” multi-platform collaboration; and perform on- board “lossless” data reduction by moving “ground” functions on-board<br /> <br /> SpaceCube 2.0 will directly support ACE, DESDynI, GEO-CAPE, HyspIRI, ICESat-II, LIST, SCLP, SMAP, SWOT, and 3D-Winds.<br />  </p>

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<p>The objective of this study was to identify and estimate the cost of one or more approaches of utilizing waste hydrogen for power generation. To simplify the scope of the problem, this study was limited to the boiloff source of the run tank at one test stand which consistently produces 500 gallons of hydrogen gas every day. This study used the results of several previous studies that also examined different ways of allaying the waste hydrogen problem. Using literature from these previous efforts as a starting point, a market review was conducted to find potential systems of hydrogen-fueled energy generation that are currently available. Candidate systems were considered based upon their compatibility with requirements dictated by the test stand and related infrastructure. These requirements were developed from technical data and drawings and supplemented with knowledge gained during a site visit to the test stand.</p><p>The market review revealed only a single viable option: a hydrogen-fueled 4.9-L reciprocating engine and generator set.</p><p>A high-level design of the supporting infrastructure was carried out in order to conduct a reasonably accurate cost analysis once a prime mover and generator system was selected. Gas and water piping systems were developed, electrical equipment needs were identified, and a general site layout determined. Cost estimates were then made for materials, equipment, installation labor, maintenance and prime contractor expenses.</p><p>With the performance of the power generation system, capital and variable expenditures known, life cycle cost analysis metrics were calculated. Impacts of the developed system on the environment were also assessed.</p>

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<p> We had two objectives in this task: 1. Develop effective single low-mass, low-power piezoelectric drive that can actuate rotary-hammer samplers through walls. 2. Determine design sensitivities and investigate Acoustic Mechanical Feed-throughs (AMF) using acoustic mode conversion with emphasis on extension to rotary. In our earlier studies, we were able to excite rotation from longitudinal vibrations but, without sufficient analytical foundations, it has been a challenge to get consistent results. Therefore, we focused our efforts on the modeling, analysis and optimization of configurations that effectively convert longitudinal forces to torque and rotation. The task consisted of conceiving drive configurations and optimizing them thru finite element and harmonic analysis, as well as producing and demonstrating the physical mechanism. The analytical task provided tools and data to select highly efficient mechanisms that use piezoelectric materials to generate elastic waves that wirelessly transmit power through a metallic wall. We produced a resonant breadboard system that converts high frequency micron-size displacements to macroscopic rotary and linear motions. The developed mechanism uses the converse piezoelectric effect as a means of generating elastic waves, which is transmitted in the form of elastic waves, was used to excite rotation through a wall and establish a basis for a systematic capability to design wireless actuation, manipulation, and deployment thru walls. Efforts were made to optimize the location of the nodal plane of the transducer and difficulties were encountered since the nodal location of the transducer is not necessarily a plane. Through our analytical studies, we were able to produce Acoustic Mechanical Feed-throughs (AMF) capability that consistently and efficiently induces rotation. We established sufficient data and analysis to allow submittal of a credible proposal for further development of the concept.</p>

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<p>Lobster X-Ray Imaging technology gives high sensitivity and source localization.</p><p>The project consist of the following:</p><p>Demonstrate angular resolution and sensitivity. Successful lab demonstration of ISS leak checking, using nitrogen, electron beam, and Lobster x-ray optic.</p>

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Micro-Instrument Accommodation Survey Project

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<p>Using a set of accurate analytic Variation of Parameters (VOP) equations for orbit propagation, and a method for defining and ‘mixing-and-matching’ various mission constraints, the tool will allow flight projects to e.g. quickly determine launch opportunities, and explore the effects on these of relaxing mission constraints.</p><p>The basic concepts involve taking advantage of the geometric notion of an orbit, the definition of a 'perturbation', and idea of 'geometric proxies'. Let us take these concepts in turn to better describe what SWM does.  The notion of an orbit is predicated on the use of Keplerian orbit elements to describe the trajectory of the spacecraft as if it were a 'bead on an elliptically-shaped wire'.  That is to say that the semi-major axis and eccentricity describe the shape and size of the wire; the inclination, right-ascension of ascending node, and argument of perigee describe the wire's spatial orientation; and the true anomaly describes where on the wire the bead can be found.  The concept of perturbation allows us to think about this elliptically-shaped wire as slowly changing its shape, size, and orientation as the spacecraft 'feels' a variety of environmental effects such as higher-order terms in the geopotential, luni-solar gravitational pull, solar radiation pressure, and atmospheric drag.  Note that the application of delta-Vs are accomplished by discontinuously changing the orbit using standard methods.</p><p>These two concepts are traditional 'textbook' ideas.  The distinguishing trait of SWM is the marriage of these ideas with the notion of a geometric proxy.  To illustrate the idea of a geometric proxy, consider a typical space science mission that wants to place spacecract in situ in the Earth's geomagnetic tail.  The geomagnetic tail lies in or near the shadow of the Earth.  In SWM, the orbit is then mapped into a geometric coodainte frame which moves as the Earth moves about the Sun such that one of its axes always lies along the Earth-Sun line and another of its axes lies along the ecliptic pole.  In this frame the Keplerian elements are 'moving' such that the line-of-apsides advances like the hands of a clock.  The action of the perturbations serves to either enhance or retard this motion. Thus the orbit's motion can be mapped into this frame where the geomagnetic tail and the shadow cast by the Earth are essentially fixed.  The final step is then use the geometric properties of the orbit and the geometric properties of the geomagnetic tail and the shadow region to simply predict the how much time is spent in the tail compared with the time spent in shadow.  Using the geometric proxies, the mission desing space can be quickly explored and, with a few more steps to describe how this orbit is established from launch, a launch window can be generated.</p><p> </p>

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<p> The TOAST instrument is an open-loop processor of GPS navigation signals. The electronics fits on a single 10 cm square card with RF components and digital components on opposite sides. A dime-sized programmable chip (FPGA) acts as a signal processor for the GPS signals of up to 10 satellites. This FPGA is under the control of a very low-power Linux CPU which handles all of the tracking models for very weak GPS signals transecting the atmosphere. Unlike typical GPS receivers, TOAST tracks without tight phase-locked loop tracking of the received carrier phase. For any given GPS satellite to be observed, TOAST generates a precise 3rd order range and phase model and only updates the FPGA every 1 - 10 seconds. This allows the processor to be loosely coupled with the signal processing to the point where, given sufficient ground to space bandwidth, TOAST can be controlled by a ground-based CPU. However, in this implementation, a Linux CPU will accompany the RF and FPGA logic to provide real-time data.</p>

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<p>Doppler measurements from a rapid moving platform, such as spacecraft, or radars using fast scanning antennas have been especially challenging due to spectrum broadening and rapid decorrelation between successive pulses.</p>

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<p>To characterize the IR optical properties of the metal-coated hollow waveguide ensemble; configure the Hollow Waveguide FTS (HWFTS) chip in such a way that we maximize signal-to-noise; carry out full radiometric testing of this implementation and acquire spectra of standard gas cells.</p>

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<p>Our objective is to apply CVD and non-CVD carbon nanotubes to complex shapes that numerous scientists have requested for stray light control.  Currently, CVD nanotubes can only be grown on flat surfaces due to limitations in line-of-sight physical vapor deposition techniques such as e-beam evaporation.   For CVD our adhesion and catalyst layers must be applied on the on the component with extreme uniformity to a thickness of 1 to 2 nm for ideal performance.   Then the component must be placed in the thermal reactor furnace flow in a way that allows uniform exposure to the carbon bearing gas.  Our first focus area is to utilize atomic layer deposition (ALD) to apply our adhesion and catalyst layers conforming to the desired substrate surface.  This will allow fabrication of components that are dark on all surfaces instead of just on one surface.</p>

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<p> Develop a compact, efficient 2µm pulsed laser for a lidar instrument to make accurate, high-resolution atmospheric CO2 column measurements in support of the ASCENDS mission.<br /> Develop a pulsed 2µm laser that is based on a Thulium fiber-laser pumped Holmium (Ho) solid state laser in a Master Oscillator Power Amplifier (MOPA) configuration.<br /> Demonstrate 65mJ at 50Hz needed for the space  Integrated Path Differential Absorption (IPDA) instrument in a robust prototype format.</p>

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<p>The objectives of the project is the development of single emitter and multiple emitter injectors for doped kerosene; to develop a fundamental understanding of droplet transport, evaporation, and mixing in the complex swirling flow fields required for meso-scale flame stabilization; and the system integration of meso-scale thrust chamber with electrospray fuel injection system. A single emitter electrospray configuration will be developed and the performance benchmarked using Phase Doppler Particle Analysis to determine the droplet size distribution as a function of flow rate. The nature of droplet transport and evaporation at the meso-scale will be studied using non-intrusive laser based techniques. The electrospray injector will be integrated into the existing heat regenerating thrust chamber and fired with kerosene/H2O2.</p>

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<p> ? Develop the technology for a compact, space-qualifiable laser transmitter for a lidar operating at 1.65 5 to enable Earth observation CH4 measurements.<br /> ? Reduce the risk, cost, size, mass and volume of the CH4 lidar instrument by scaling the laser power of the existing laboratory breadboard.<br /> ? Demonstrate and validate simultaneous, high sensitivity, methane and CO2 measurements using the proposed methane lidar and an operational CO2 lidar.</p>

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<p>This design uses regular drinking water that is pumped through two filters to produce, in minutes, sterile, ultrapure water that meets the stringent quality standards of the United States Pharmacopeia for Water for Injection (Total Bacteria, Conductivity, Endotoxins, Total Organic Carbon). The device is 2.2 lbs (1kg) and 10L x 5W x 3H inches (25L x 13W x 7.5H cm) in its storage configuration. This handheld device produces one liter of medical-grade water in 21 minutes. Total production capacity for this innovation is expected to be in the hundreds of liters.</p><p>The device contains one battery powered electric mini-pump. Alternatively, a manually powered pump can be attached and used. Drinking water enters the device from a source water bag, flows through two filters, and final sterile production water exits into a sealed, medical-grade collection bag. The collection bag contains pre-placed crystalline salts to mix with product water to form isotonic intravenous medical solutions. Alternatively, a hypertonic salt solution can be injected into a filled bag. The filled collection bag is detached from the device and is ready for use or storage. The entire system can then be flushed, sealed, and radiation-sterilized.</p>

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<p> Achieve scalability of a 1.26 µm fiber Raman amplifier (FRA) to 5W with an optical-to-optical efficiency of >50%, that is compatible with ITT’s modulated CW Laser Absorption Spectrometer (LAS) in support of the ASCENDS mission.<br /> Advance the retrieval/software tools to demonstrate the retrieval of dry air mixing ratio of CO2 using simultaneous active O2 and CO2 integrated column measurements.<br />  </p>

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<p>Kennedy Space Center (KSC) has undertaken a study to find environmentally friendly alternatives for the petroleum and solvent-based corrosion-preventive compounds (CPCs) used to protect flight hardware and ground support equipment. Film-forming CPCs leave either a soft or hard protective barrier that prevents moisture from directly contacting metallic surfaces, whereas thin and ultra-thin wicking CPCs displace moisture in cracks and crevices and leave a residue that repels further moisture. To protect an occluded region, the CPC must either form a barrier over the crevice mount or wick into the occluded region. In both film-forming and wicking CPCs, corrosion inhibitors are often suspended in a mixture of solvents and a base oil or grease. The base oil acts as a carrier fluid for the inhibitors and as a moisture barrier. The solvent, which is intended to evaporate after application, acts as a base oil and disperses the inhibitor. Although CPCs can be effective, the base oils are not environmentally benign and the solvents can be toxic and high in volatile organic compounds (VOCs).</p><p>The candidates tested for use at  KSC were soft-film CPCs, both common petroleum-based and newer environmentally friendly types. For this program, “environmentally friendly” refers to CPCs that are low in VOCs (less than 100 g/L), are not hazardous air pollutants, are nontoxic, and are non-carcinogenic. In Phase 1, the CPCs were applied to various steel and aluminum substrates, which were subjected to atmospheric exposure testing at KSC’s Beachside Atmospheric Corrosion Test Site, as well as to cyclic accelerated corrosion testing. Phase 2 consists of more rigorous testing of the down selected CPCs from Phase 1, new testing of hard-film CPCs, and a study of the failure mechanisms of the different CPC types. Phase 3 testing will determine end use application parameters, including material life cycles, application frequency, and compatibility testing with the specific end uses at the Kennedy Space Center so that they can be incorporated into current applications and future flight hardware and ground support uses. </p>

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<p>The end goal of this project is to develop proof-of-concept infrared detectors which can be integrated in future infrared instruments engaged in remote sensing.  We plan to evaluate several materials for their compatibility and performance.</p>

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Data Concentrator for Modular and Distributed Control of Propulsion Systems (A) Project

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<p>This IRAD proposes to evaluate how stress polishing can be used to extend the application of super-polishing to fast aspheres and freeforms, removing sub-aperture MSF errors, such as tool marks, from diamond-turned aluminum optics.  It will leverage an old technique for manufacturing aspheres—stress polishing with a large tool. The aspheric surface will be generated using small tool manufacturing techniques. After the asphere is generated, a mechanical load will be placed onto the optic to deform the asphere into a sphere, using an interferometer to fine tune the deformation.  After the asphere is deformed into a sphere, the sub-aperture tool marks can be removed by post-polishing using the Goddard super-polishing process, a process limited to spheres and flats due to the fact that it requires the use of a tight fitting large polishing tool.</p>

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<p> Develop a mission simulation and evaluation platform for terrestrial hydrology missions by creating an end-to-end observation system simulation experiment (OSSE) platform by using NASA LIS’ data assimilation, optimization, and uncertainty estimation tools.  This platform will enable:<br /> Quantifying the impact of observations through a variety of OSSE configurations and evaluation metrics related to terrestrial hydrologic science and applications<br /> Improving the use of products for end-use applications and science, and quantifying the mission risks for GPM and GRACE-II</p>

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<p>The WFF 6U deployer will be improved in 11 key areas:</p><p> </p><p>1. Mass & Joint Reduction</p><p>2. Two Stage Release</p><p>3. Door Orientation</p><p>4. Satellite Preload System Improvement</p><p>5. Sounding Rocket Fitment</p><p>6. Quick Disconnect</p><p>7. Launch Vehicle Interface Update</p><p>8. Deployment Verification System</p><p>9. Shear Pin Preload System Improvement</p><p>10. Deployment Spring Interface</p><p>11. Nitrogen Purge System</p><p>Once the improvements have been incorporated into the design, detailed structural analysis will be completed to ensure survival under predicted environmental loading conditions.  A qualification unit of the improved design will be manufactured and undergo functional, vibration, and thermal testing.</p>

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Advanced Supported Liquid Membranes for CO2 Control in EVA Applications Project

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<p>The sensor uses graphene based devices to sense the surface potential of a graphene channel exposed to an analyte. When analyte molecules adsorb onto the graphene surface, they induce a local change in electrical resistance. This effect is very pronounced in graphene due to the high surface area; high electrical conductivity; and inherent low noise, which makes the changes in resistance detectable.</p>

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<p>The objective is to design, build and functionally test a miniature release mechanism for CubeSats and other small satellites. The WFF 6U satellite structure will be used as the baseline design reference. Design goals for the unit include:</p><ul><li>Low cost</li><li>Non-explosive, low release energy</li><li>Packaging height target of 0.25 inches or less</li><li>Two fault tolerance initiation</li><li>Resettable and usable for at least 10 cycles</li><li>Low power</li></ul>