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Combining Discrete Element Modeling, Finite Element Analysis, and Experimental Calibrations for Modeling of Granular Material Systems Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:43:27.000ZThe current state-of-the-art in DEM modeling has two major limitations which must be overcome to ensure that the technique can be useful to NASA engineers and the commercial sector: the computational intensive nature of the software, and the lack of an established methodology to determine the particle properties to best accurately model a given physical system. The proposed work will address both of these limitations. We will look at two approaches to overcome the particle count limitations of DEM: investigate the scaling up of particle size; and combine FEA and DEM to look at problems of densely packed solids. We will explore regimes where DEM and FEA are applicable and establish a coupling methodology that can be further developed during phase II. To address the lack of an established methodology to determine the particle properties to best accurately model a given physical system, we will investigate several small scale experiments that can be used to characterize DEM models. The proposed work will advance the state-of-the-art in DEM. At the end of phase I we will show the feasibility of developing modeling approaches to overcome the main limitations of DEM.
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Robust Optimal Fragmentation and Dispersion of Near-Earth Objects Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:31:30.000Z<p> During the past 2 decades, various concepts for mitigating the impact threats from NEOs have been proposed, but many of these concepts were impractical and not technically credible. In particular, all non-nuclear techniques require mission lead times larger than 10 years. However, for the most probable impact threat with a warning time less than 10 years, the use of high-energy nuclear explosives in space becomes inevitable for proper fragmentation and dispersion of an NEO in a collision course with Earth. However, the existing nuclear subsurface penetrator technology limits the impact velocity to less than 300m/s because higher impact velocities destroy prematurely the detonation electronic equipment. Thus, an innovative space system architecture utilizing high-energy nuclear explosives must be developed for a worst-case intercept mission resulting in relative closing velocities as high as 5-30km/s. An advanced system concept is proposed for nuclear subsurface explosion missions. The concept blends a hypervelocity kinetic-energy impactor with nuclear subsurface explosion, and exploits a 2-body space vehicle consisting of a fore body and an aft body. These 2 spacecraft bodies may be connected by a deployable boom. The fore body provides proper kinetic impact crater conditions for an aft body carrying nuclear explosives to make a deeper penetration into an asteroid body. For such a complex mission architecture design study, non-traditional, multidisciplinary research efforts in the areas of hypervelocity impact dynamics, nuclear explosion modeling, high-temperature thermal shielding, shock-resistant electronic systems, and advanced space system technologies are required. Expanding upon the current research activities, the Iowa State Asteroid Deflection Research Center will develop an innovative, advanced space system architecture that provides the planetary defense capabilities needed to enable a future real space mission more efficient, affordable, and reliable.</p>
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High Interactivity Visualization Software for Large Computational Data Sets Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:17:34.000ZExisting scientific visualization tools have specific limitations for large scale scientific data sets. Of these four limitations can be seen as paramount: (i) memory management, (ii) remote visualization, (iii) interactivity, and (iv) specificity. In Phase I, we proposed and successfully developed a prototype of a collection of computer tools and libraries called SciViz that overcome these limitations and enable researchers to visualize large scale data sets (greater than 200 gigabytes) on HPC resources remotely from their workstations at interactive rates. A key element of our technology is the stack oriented rather than a framework driven approach which allows it to interoperate with common existing scientific visualization software thereby eliminating the need for the user to switch and learn new software. The result is a versatile 3D visualization capability that will significantly decrease the time to knowledge discovery from large, complex data sets. Typical visualization activity can be organized into a simple stack of steps that leads to the visualization result. These steps can broadly be classified into data retrieval, data analysis, visual representation, and rendering. Our approach will be to continue with the technique selected in Phase I of utilizing existing visualization tools at each point in the visualization stack and to develop specific tools that address the core limitations identified and seamlessly integrate them into the visualization stack. Specifically, we intend to complete technical objectives in four areas that will complete the development of visualization tools for interactive visualization of very large data sets in each layer of the visualization stack. These four areas are: Feature Objectives, C++ Conversion and Optimization, Testing Objectives, and Domain Specifics and Integration. The technology will be developed and tested at NASA and the San Diego Supercomputer Center.
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Rapid Electrochemical Detection and Identification of Microbiological and Chemical Contaminants for Manned Spaceflight Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:40:47.000Z<p>A great deal of effort has gone into the development of point-of-use methods to meet the challenge of rapid bacterial identification for both environmental monitoring and clinical applications.&nbsp; Unfortunately, most of the methods developed rely on Preliminary Chain Reaction (PCR) and face inherent limitations because of the requirement for enzymatic components and thermal control.&nbsp; Other methods based on surface plasmon resonance, quartz crystal microbalance, and fluorescence has been reported with good detection limits, but, these methods are immunological and cannot provide genetic-level information.&nbsp; Further, they require labeled markers, complicated fluid handling systems, and sensitive optics that drive up cost and complexity and preclude them from outside the laboratory.&nbsp; Recent work by a group at the University of Toronto has focused on developing an electrochemical platform that combines ultrasensitive detection, straightforward sample processing, and inexpensive components to create a cost-effective, user-friendly device for detection and identification of microorganisms.&nbsp; The platform combines an electrical cell lysis chamber, and electrochemical reporter system, and nanostructured microelectrodes (NMEs) to detect specific nucleic acid sequences.&nbsp; The nucleic acid sequences are unique to a given type of microorganism and can be used to identify the microorganisms present in a sample.</p><p>From the perspective of the anticipated prototype device &nbsp;(Lam, et al. 2012. <em>Polymerase Chain Reaction-Free, Sample-to-Answer Bacterial Detection in 30 Minutes with Integrated Cell Lysis</em>. Anal. Chem. <strong>84(1)</strong>: 21-5), detection of microbial contaminants will begin with a lysis chamber designed to release DNA and RNA from microorganisms present in the sample using ultrasonic or electrochemical technology.&nbsp; The DNA and RNA mixture is then passed into an analysis chamber containing an array of nanostructured microelectrodes (NMEs).&nbsp; The surface of the NMEs will be functionalized with probe molecules for DNA or RNA sequences specific to the bacteria being targeted.&nbsp; Binding of the DNA or RNA to the appropriate detection probe on the NME surface in the presence of an electrochemical reporter system will change the electrochemical properties of the NMEs.&nbsp; A potentiostat is used to measure the current at each individual electrode before and after addition of the DNA and RNA mixture.&nbsp; The difference in current before and after addition of the mixture to the NMEs is compared against a pre-determined threshold to check for the presence of target bacteria in the sample.&nbsp; The process for detection of chemical contaminants is very similar.&nbsp; The lysis chamber would be bypassed and the sample would flow directly into the analysis chamber.&nbsp; The NMEs will be functionalized with molecules to selectively bind the desired targets (analytes) and the change in the electrochemical response of each NME can again be used to detect and quantify the contaminants.&nbsp; Depending on the analyte of interest, it may be possible to directly measure analyte binding on the surface of the NMEs without the use of an electrochemical reporter system. The overall project will focus on optimization of the individual aspects of the detection platform in preparation for construction of a prototype for a flight experiment.&nbsp; The scope of the work in this proposal is limited to characterization and optimization of the lysis step/sample preparation, probe selection, and NME structure.&nbsp; Lysis conditions will be optimized by evaluating parameters associated with the oscillation frequency and lysis time for ultrasonic techniques and applied voltage for the electrochemical techniques.&nbsp; Cell viability, as determined by fluorescent detection of DNA or R
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Prognostic Fault Detection and Isolation for EMA and EPS Systems Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:10:33.000ZIn response to NASA SBIR topic X1.04, Ridgetop Group will extend and adapt RingDown: an innovative system for the non-invasive prognostic monitoring of the health of electromechanical actuators and related power systems. This comprehensive solution provides both advanced hardware sensors to monitor the systems and prognostic health management algorithms to interpret the signals available in them. RingDown will significantly improve the reliability of and confidence in these critical NASA systems by alerting NASA personnel to impending failures well before they occur, averting disaster and improving confidence in the health of the systems. Electromechanical actuators (EMAs) are comprised of a complex system-of-systems: a high-power switch mode power supply to power the EMA's servo drive, a lower-voltage switch mode power supply to power the EMA's logic controller, power inverters, and the EMA itself. The sensors and algorithms provided by Ridgetop will allow NASA to monitor the health of?and anticipate failures in?all of these systems. In addition, these algorithms will be applicable to other switch mode power supplies (SMPSs), which are a very common component in NASA's electrical systems. Ridgetop's goal in this SBIR program is to transition these EMA prognostic health management technologies into fielded systems. In Phase I, Ridgetop will extend the RingDown sensors developed under previous NASA SBIRs to monitor additional components in the EMA system-of-systems. Ridgetop will also prototype the algorithms to interpret the data from those sensors in this Phase. In Phase II, Ridgetop will implement additional functionality for these algorithms and then field-test the combined algorithm and sensor solution. In a future Phase III or other commercialization program, a final version of this comprehensive solution will be demonstrated in-flight and then transitioned into actual system usage.
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Hybrid High-Fidelity Auscultation Scope Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:08:32.000ZTo address the NASA Johnson Space Center's need for a space auscultation capability, Physical Optics Corporation proposes to develop a Hybrid High-Fidelity Auscultation Scope (AUSCU-SCOPE) based on a unique combination of multiple auscultation mechanisms with a novel sensor-fusion algorithm. This system incorporates a hybridized sensor configuration and novel signal processing algorithm that will separate low-intensity body sounds (<25 dBA) from a noisy background (>70 dBA) experienced in spaceflights with a 20-dB signal-to-noise ratio. The non-invasive and space-qualified AUSCU-SCOPE is safe, easy-to-use for a non-expert crew member and does not require extra training of clinicians to Doppler sounds. Additionally, the system easily connects with space telemetry systems via Ethernet, firewire, USB, and wireless 802.11 for transmitting sound data for distance diagnosis. In Phase I, POC will demonstrate feasibility of AUSCU-SCOPE through system design, simulation, assembly, and testing of a benchtop prototype, which will reach TRL-level 4 by the end of Phase I. In Phase II, POC will develop a fully functional prototype at TRL-6 and demonstrate high-fidelity spaceflight auscultation capability in the presence of a 70-dBA noise. The results will enable NASA to perform spaceflight auscultation even against significant background noise.
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>1,000 W/kg Rad-Hard, High-Voltage PV Blanket at < $50/W IMM Cell Cost Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:31:36.000ZThe innovation is a new type of Stretched Lens Array (SLA) with a much thinner, lighter and more robust Fresnel lens than prior versions. The new lens enables a full blanket-level specific power > 1,000 W/kg, including lenses, the complete PV cell circuit (including cells, encapsulation, high-voltage insulation, and heavy radiation shielding), and waste heat rejection radiator. The new SLA array is cost-effective, with the most expensive array cost element, the IMM solar cell, contributing less than $50/W to the array cost. The new lens is novel in configuration, enabling single-axis tracking for the array even in the presence of large beta angles (e.g., 50 degrees) between the array and the sun. For future high-power arrays (e.g., > 100 kW), including Solar Electric Propulsion (SEP) missions, the new SLA will offer a unique combination of high efficiency (e.g., >35%), ultra-low mass, high-operating voltage (e.g., >300 V), and low cost. SLA technology is a direct descendant of the SCARLET array used to power NASA's Deep Space 1 SEP mission in 1998-2001. SLA recently completed a flight test on TacSat 4 in a very high radiation orbit, and the lessons learned from TacSat 4 led to the new SLA, the subject of this proposal. The new SLA is scalable to multi-hundred-kW array sizes using blanket deployment and support platforms such as DSS's Roll-Out Solar Array (ROSA) or ATK's SquareRigger. The new SLA will typically operate at 4-8X concentration, saving substantially on solar cell area, cost, radiation shielding mass, and dielectric isolation mass. The new SLA will enable the early use of state-of-the-art cells, such as inverted metamorphic (IMM) cells with 4 or 6 junctions, and will enhance the production capacity of cell vendors (e.g., 100 kW per year of 1 sun cells = 700 kW per year of 7X cells). The feasibility of the new SLA will be firmly established in Phase I, and functional prototype new SLA hardware will be fully developed and tested in Phase II.
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Lightweight Materials and Structures (LMS): Minimalistic Advanced SoftGoods Hatch (MASH) Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:35:38.000Z<p>MASH project will collaborate with NASA and industry stakeholders to facilitate design, identify materials, novel fabrication processes, and conduct validation testing and analysis of a lightweight airlock hatch system test article.&nbsp; MASH project will meet its objective through a combination of concept designs and trades, system and conop requirements definition, component development, and system design, fabrication, and testing in conjunction with mission architecture and operations studies.&nbsp; The project will address mission needs, technical challenges, risks related to the use of soft goods materials and structures.</p><p>The MASH project has 2 elements.&nbsp; The first element is a series of trade studies and evaluations that will 1) establish basic requirements and figure of merits (FOM) for the hatch system, 2) evaluate hatch concepts against requirements and FOMs, 3) survey candidate materials for hatch design, and 4) support mission impact studies that will inform the hatch design requirements. &nbsp;&nbsp;</p><p>The second element (WBS 2.2), hatch technology development, uses a building block approach to systematically develop and demonstrate a soft goods hatch system.&nbsp; The approach includes design, analysis, fabrication and testing of first, hatch components and then, an integrated hatch system.</p><p>In FY14, the requirements and FOMs were determined from existing NASA standards for soft good structures and hatch design as well as customer needs. An initial trade evaluation informed the design of the hatch system at the beginning of the project and down selected a minimal set of design options.&nbsp;&nbsp; This minimal set of concept options will be matured with analysis and design details in the first quarter of FY15.&nbsp; A final trade evaluation with updated requirements and FOMS will be conducted to select a primary hatch design for maturation, fabrication and demonstration.&nbsp;&nbsp; In addition, a materials survey will be conducted to inform the current state of the art (SOA) and advance material options for the hatch system design.&nbsp;</p><p>In FY15, the MASH project will work with a HAT vehicle analysis team to define a reference airlock.&nbsp; The reference airlock will be used to inform and evaluate the performance of the hatch system against the key performance parameters, mass and volume.</p><p>In FY15 MASH will also futher the technology development of a soft goods hatch system design.&nbsp; Material candidate(s) from the materials survey and performance evaluations will be selected for implementation into the hatch design.&nbsp; Design analysis cycles will be conducted to inform fabrication of hatch components.&nbsp; Hatch components will be experimentally tested to validate performance.&nbsp; Specifically, sealing tests for required pressure loads and packaging evaluations will be peformed.&nbsp; The design, analysis, and component test validation along with customer needs will inform a final hatch design for a hatch system demonstration in FY16.&nbsp; The potential customers will be invited to participate in the design selection and evaluation to ensure the soft hatch design continues to be relevant to their needs.&nbsp; The technical review of the final hatch system design will be conducted prior to a continuation review of the project, and fabrication of a hatch system.&nbsp;</p><p>In FY16 MASH project activities will focus on the fabrication and experimental testing of the integrated hatch system. &nbsp;Design details for fabrication and the procurment statement of work (SOW) will be completed and ready for award the first quarter of FY16.&nbsp; An award kick-off and an intermin review for fabrication will be held during the fabrication process to ensure the fabrication of the hatch will meet requirements.&am
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Integrated Sublimator Driven Coldplate for use in Active Thermal Control System Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:13:00.000ZThe original Sublimator Driven Coldplate (SDC) design sought to provide significant mass savings over a traditional pumped fluid loop by combining the functions of a cold plate and a sublimator and eliminating the fluid loop (Leimkuehler, et. al., "Design of a Sublimator Driven Coldplate Development Unit," 2008-01-2169). The target application was to provide heat rejection for the ascent module of the Altair lunar lander vehicle during the lunar ascent mission phase. However, in order to provide heat rejection for the ascent module during the rest of the mission, it is desirable to keep the ascent module integrated with the fluid loop in the rest of the Altair vehicle. Therefore, we propose an Integrated Sublimator Driven Coldplate (ISDC) that can function as both a standard flow-through cold plate and a Sublimator Driven Coldplate. The ISDC builds on the original SDC concept by adding coolant layers so that it can be integrated with the pumped fluid loop on the rest of the vehicle. This approach provides mass savings by (1) combining multiple pieces of hardware into a single piece of hardware and (2) providing additional fault tolerance without the need for redundant hardware.
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ESPA Based Secondary Payload Orbit Maneuvering System Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:16:25.000ZBusek proposes to develop an integrated propulsion, power, ACS, (ProPACS) system for micro-spacecraft deployed from the ESPA ring secondary payload ports. The standardized ProPACS system integrates the essential elements needed for highly capable micro-spacecraft bus including; 1) 600 W Hall effect thruster system for primary propulsion, 2) Xe cold gas thrusters for propulsive ACS, 3) articulated solar array, batteries and power management and distribution (PMAD) system with steady state power of 700W available to the payload when propulsion is off and 4) an integral structure that supports the payload and a LightBand separation mechanism for the ESPA ring. The ProPACS can provide over 1,800 m/sec deltaV to a 181 kg spacecraft with a 80kg payload. In Phase 1 ProPACS system architecture design was completed and all major components were identified. Mass, power, data budgets were developed and major interfaces were specified. Phase 2 focus will be on the ProPACS elements with lower TRL to achieve system wide TRL6 at the end of the program. The thruster will be advanced to near flight level, two PMAD systems will be evaluated and one selected and the ProPACS integral structure supporting the payload and separation ring will be designed and built.