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- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:41:30.000Z
The NASA application requires a system that can generate 3D images of non-metallic material when access is limited to one side of the material. The objective of this proposal is to demonstrate the feasibility of developing and build a new, practical, potentially portable, battery operated, self-contained Compton x-ray backscatter 3D imaging system by using a specially designed automated rotationally movable x-ray source, a 2D x-ray detector with a highly collimator system and the development of a suitable 3D processing computer model. In the proposed x-ray imaging system, the primary technical advance will be to extend methods that normally supply a 2D projected image through a sheet of material, to a 3D image with more complicated features at different depths, such as voids, cracks, corrosion or delaminations. The portability of the proposed imaging system will allow bringing it to the object to be imaged. Phase 2 will be conducted with a focus on technology transition and an understanding of what it will take to demonstrate and qualify the proposed method in a prototype for use in an actual imaging system and a realistic environment. Also in Phase II, time reduction in setup, data image acquisition, and 3D-image reconstruction analysis will be realized by remote automated control of the operation and movement of a brighter x-ray source and a state-of-the-art digital flat panel detector in conjunction with a highly collimator system.
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:24:49.000Z
To meet the design challenges of tomorrow, NASA and industry require advancements in the state-of-the-art for physics-based design and analysis frameworks. In particular, NASA needs the ability to make more use of physics-based models earlier in the design process. This will allow engineers to more accurately capture the complex coupling between engineering disciplines and to more accurately simulate the complex behavior of novel design configurations. Key technical barriers include long execution times, model and data complexity, and geometry management. In the Phase II project, Phoenix Integration will expand on the successful Phase I prototypes to develop new technologies and user interfaces that will help overcome these barriers. This project will focus on (1) the development of a flexible capability for implementing Multi-Disciplinary Analysis and Optimization (MDAO) strategies (such as multi-fidelity) in ModelCenter, (2) the creation of a flexible geometry visualization and monitoring capability for high-fidelity system models, and (3) the extension of Phoenix Integration's "Plug-In" infrastructure to better support a wide range of high-fidelity analysis and geometry management tools (CAD/CAE tools, meshing tools, mesh morphing tools). These technologies will combine with other NASA funded technologies to create a robust physics-based design and analysis framework for designing next generation air vehicles.
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:03:54.000Z
There are uncertainties in the interpretation of data from any one of the instruments (KuPR, KaPR, and GMI). By using data from multiple instruments, further constraints on the solution of precipitation structure improve the final product.The purpose of 3CMB is to give a daily and monthly accumulation of the 2BCMB precipitation product. The 3CMB product is a daily and monthly accumulation of the 2BCMB orbital combined product at two grid sizes, 5 x 5 degrees (G1) and 0.25 x 0.25 degrees (G2). Grid G1 contains the following physical measurements of general interest, among others. Grid G2 contains the same groups, but it is on the ltH x lnH grid and does not have the surface type (st) dimension or the histograms (see dimension definitions below). Below, conditional products represent means based upon precipitating areas only; unconditional products represent means for raining and non-raining areas combined. Probabilities represent the number of raining observations divided by the total number of raining and non-raining observations. precipTotRate (Group in G1)- Conditional mean rate for all precipitation phases (ice, liquid, mixed-phase). * count (4-byte integer, array size: ltL x lnL x ns x hgt x rt x st): Count. * mean (4-byte float, array size: ltL x lnL x ns x hgt x rt x st): Mean, mm/h. * stdev (4-byte float, array size: ltL x lnL x ns x hgt x rt x st): Standard deviation for the monthly product. Mean of squares for the daily product, mm/h. * hist (4-byte integer, array size: ltL x lnL x ns x hgt x rt x st x bin): Histogram. precipLiqRate (Group in G1) - Conditional mean rate for liquid precipitation. * count (4-byte integer, array size: ltL x lnL x ns x hgt x rt x st): Count. * mean (4-byte float, array size: ltL x lnL x ns x hgt x rt x st): Mean, mm/h. * stdev (4-byte float, array size: ltL x lnL x ns x hgt x rt x st): Standard deviation for the monthly product. Mean of squares for the daily product, mm/h. * hist (4-byte integer, array size: ltL x lnL x ns x hgt x rt x st x bin): Histogram. precipTotWaterContent (Group in G1) - Conditional mean water content for all precipitation phases. * count (4-byte integer, array size: ltL x lnL x ns x hgt x rt x st): Count. * mean (4-byte float, array size: ltL x lnL x ns x hgt x rt x st): Mean, g/m3. * stdev (4-byte float, array size: ltL x lnL x ns x hgt x rt x st): Standard deviation for the monthly product. Mean of squares for the daily product, g/m3. * hist (4-byte integer, array size: ltL x lnL x ns x hgt x rt x st x bin): Histogram. precipLiqWaterContent (Group in G1) - Conditional mean liquid water content. * count (4-byte integer, array size: ltL x lnL x ns x hgt x rt x st): Count. * mean (4-byte float, array size: ltL x lnL x ns x hgt x rt x st): Mean, g/m3. * stdev (4-byte float, array size: ltL x lnL x ns x hgt x rt x st): Standard deviation for the monthly product. Mean of squares for the daily product, g/m3. * hist (4-byte integer, array size: ltL x lnL x ns x hgt x rt x st x bin): Histogram. precipTotDm (Group in G1) - Conditional mass-weighted mean particle diameter. * count (4-byte integer, array size: ltL x lnL x ns x hgt x rt x st): Count. * mean (4-byte float, array size: ltL x lnL x ns x hgt x rt x st): Mean, mm. * stdev (4-byte float, array size: ltL x lnL x ns x hgt x rt x st): Standard deviation for the monthly product. Mean of squares for the daily product, mm. * hist (4-byte integer, array size: ltL x lnL x ns x hgt x rt x st x bin): Histogram. precipTotRateDiurnal (Group in G1) - Conditional mean total surface precipitation rate indexed by local time. * count (4-byte integer, array size: ltL x lnL x ns x st x tim): Count. * mean (4-byte float, array size: ltL x lnL x ns x st x tim): Mean, mm/h. * stdev (4-byte float, array size: ltL x lnL x ns x st x tim): Standard deviation for the monthly product. Mean of squares for the daily product, mm/h. surfPrecipTotRateDiurnalAllObs (4-byte integer, array size: ltL x lnL x ns x st x tim): Number of total observa...
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:24:37.000Z
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.
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:17:22.000Z
The process known as double bag vacuum assisted resin transfer molding (DBVARTM) was developed by NASA to help deplete by products. To date, the NASA DBVARTM process has reduced void content to approximately four to five percent. This number has fallen short of the goal of two percent. During the Phase I effort, San Diego Composites (SDC) was able to reduce the void content to 0.8 percent to 1.5 percent. There are three primary technical objectives to the Phase II effort. The first objective is to perform a trade study to evaluate and optimize the effect of stitched performs. Stitching has had a large effect on the void content in the laminate and several different stitching variables will be evaluated. The second objective is to transition the work done in Phase I to larger components. These components will consist of larger plates and structures will be evaluated using non destructive testing along with mechanical testing. At the end of the Phase II effort, a full scale component will be fabricated, evaluated using non destructive testing, and then the component will be tested. The final objective is to transition the technology to Boeing Phantom Works. This objective will demonstrate that the process developed in a laboratory can be reproduced at any facility. By the end of the Phase II program, the Technology Readiness Level (TRL) is expected to be 5-6.
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:39:40.000Z
<p>The purpose of this project is to develop state-of-the-art, green precision cleaning technologies for NASA&rsquo;s 21<sup>st</sup> Century Launch Complex thus eliminating long-term environmental costs to the Program.&nbsp; Precision cleaning is of critical importance in the aerospace industry.&nbsp; Failure to clean to specified levels may result in problems ranging from impaired performance to catastrophic failure.&nbsp;</p><p>Of particular concern is the cleaning of systems containing strong oxidizers such as liquid oxygen (LOX) or hypergolic fuels.&nbsp; Currently, precision cleaning at Kennedy Space Center is performed using dual-solvent process in which the first solvent, Vertrel MCA, is used to clean the component and a second solvent, HFE-7100, is used as a final rinse and analytical test fluid.&nbsp; Highly fluorinated compounds such as those used in Vertrel MCA are extremely persistent in the environment and are potent greenhouse gases. Continued use of this or similar solvents will lead to high remediation costs that must be carried by the Program for years to come.</p><p>Historically, precision cleaning has used chlorofluorocarbons (CFCs), such as Freon, because it was non-toxic and performed extremely wll.&nbsp; When Freon, and other CFCs, were banned due to their harmful environmental effects, new solvents were identified that were similar compounds but were not yet regulated.&nbsp; Eventually, these solvents also become regulated and unavailable for use.&nbsp; This project specifically did not consider halogenated solvents in order to find solvents or technologies that would not face future environmental regulations.</p>
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:17:45.000Z
This SBIR Phase-1 project will demonstrate the feasibility of using a novel coaxial counterflow solid-solid heat exchanger to recover heat energy from spent regolith at 1050<SUP>o</SUP>C to pre-heat inlet regolith to 750<SUP>o</SUP>C, either continuously, or in 20kg batches. In granular solids the area of contacts between 'touching' grains is quite small. Thus, solid-solid conduction often plays only a minor role in heat transfer through granular solids (i.e., 'effective' conduction), and when an interstitial gas is present, heat transfer occurs primarily via conduction through the gas. If the granular solid is also flowing, then solids convection becomes a significant factor in overall heat transfer and effective 'conduction'. Under vacuum conditions, and at temperatures above 700<SUP>o</SUP>C, radiation will dominate most heat transfer processes; however, solids convection can also play a very significant secondary role. Utilizing judicious placement of radiation baffles, and a novel counterflow configuration, the approach proposed in this SBIR can accomplish the desired heat transfer between spent and fresh regolith with only one moving mechanical part, by making effective use of both radiative heat transfer and solids convection. Discrete-element simulations of regolith flow will be utilized to refine the concept. Utilization of an existing ~1.4 cubic meter partial-vacuum facility at the University of Florida will facilitate construction of feasibility demonstration prototypes during Phase-1 and/or Phase-2. The Phase-1 project will demonstrate the effectiveness of combining solids convection with radiative heat transfer to rapidly transfer heat from 1050C spent material to heat fresh regolith to 750C under vacuum conditions.
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:12:30.000Z
While VPX shows promise as an open standard COTS computing and memory platform, there are several challenges that must be overcome to migrate the technology for a space application. For the Phase I SBIR, SEAKR investigated the 3u VPX architecture for the space environment for advanced memory and processing systems. The SBIR investigation focused on researching innovative switch fabric architectures, identifying and qualifying the building blocks for a space qualified VPX system, and addressed some of the challenges associated with VPX flash memory modules. The areas of innovation that have been addressed are outlined below: Research and evaluate the basic building blocks required for a high speed switch VPX architecture Explore advanced EDAC and innovative wear leveling techniques for commercially upscreened flash memory for space applications Evaluate different techniques for very high speed flash memory access rates The Phase II SBIR will build on the Phase I study to produce a deliverable engineering model of a 3U VPX flash memory module.
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:23:19.000Z
Ceramic Composites Inc. (CCI) of Millersville, MD in association with Swales Aerospace of Beltsville, MD have evaluated an innovative approach for the design of a Venus probe to maximize the payload volume and mass, while increasing probe lifetime. CCI and Swales have evaluated state-of-the-art materials and concepts to create a combination of thermal management approaches which maximizes value to NASA such as: 1) augmentation of the passive insulation with phase change materials (PCM) and two-phase evaporation cooling to maximize thermal protection at minimal volume and mass, 2) providing system corrosion protection through reverse flow gas balance to prolong vessel, sensor and window life, and 3) replacement of the titanium pressure vessel with a polymer matrix composite to reduce vessel mass and increase payload mass. The analyses conducted in Phase I indicate that the baseline concept will provide a lifetime of approximately 35 earth hours (while also managing a continuous 150W load from the scientific equipment) with a 100kg mass savings compared to a system employing the same thermal management system with a titanium pressure vessel. The Phase II effort will focus on refining the concept; designing, manufacturing, and evaluating a subscale prototype.
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:18:23.000Z
Under Project Constellation, NASA is developing a new generation of spacecraft for human spaceflight. A significant percentage of the structures used in these spacecraft will be made of composite materials, and the Ares V payload shroud will be one of the largest composite structures ever built. This offers many challenges, not only for design and manufacturing, but also for inspection and maintenance. Inspection of large composite structures using traditional NDE methods is time consuming, expensive, and often not possible when access is limited (e.g. covered by a thermal protection system), resulting in a conservative (higher weight) design. Acellent proposes to develop a robust, state-of-the-art structural health monitoring (SHM) system to overcome these concerns. The Phase II will optimize the design and quantify the benefits for SHM on the Ares V payload shroud, and then expand the results to include other Ares V components such as the Altair Lunar Lander Structure, Earth Departure Stage (EDS) payload adapter, forward skirt and intertank, and the Core-to-EDS interstage. The proposed solution will be capable of detecting and quantifying damage with a high probability of detection (POD), accurately predicting the residual strength and remaining life of the structures with confidence, and providing information that will allow appropriate preventative actions on the monitored structure.