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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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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.
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ESPA Based Secondary Payload Orbit Maneuvering System Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:15:37.000ZBusek Co. Inc. proposes to develop/design an integrated propulsion, power, ACS, and separation module for secondary ESPA payloads. The standardized secondary payload orbit maneuvering system (OMS) will have; 1) 200 W or 600 W Hall effect thruster system for primary propulsion, 2) Xe cold gas thrusters for propulsive ACS, 3) solar array, batteries and power conditioning with steady state power of !V230/680W and 4) an integral structure that supports the payload and a LightBand separation mechanism for the ESPA ring. The proposed system architecture is based upon an EELV Secondary Payload Adapter (ESPA). Because the ESPA OMS has power, avionics, and propulsion, it is a free flying spacecraft capable of delivering payloads to disparate altitudes and inclinations. In Phase I, Busek will design an OMS to meet NASA mission needs including deploying large numbers of micro satellites and CubeSats. Preliminary analysis suggests the each secondary OMS can provide 780 m/sec delta velocity to a 125 kg payload. A key Phase I activity will be a prototypical orbital deployers adapter for clusters of CubeSat. With this adapter, the system could deliver large numbers of CubeSats to discrete, pre-defined orbits. Phase II products will include a clustering adapter ready to fly in 2010, along with the OMS propulsion system.
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Hall-Effect Thruster Modifications for Dual-Mode Electric Propulsion Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:08:18.000ZThe integrated NASA/DoD electric propulsion objectives are for a specific mass less than 3 kg/kW while demonstrating a throttlable thrust-to-power ratio of 100:1 at a specific impulse of 1,000 sec down to 40:1 at 4,000 sec with an operational lifetime exceeding 20,000 hours. Modern Hall-effect thrusters (HETs) are a proven technology with flight heritage, established manufacturing readiness and testing channels that nearly meet the desired specifications (as shown in Figure 1). However, the major limitation is that HETs fail to achieve all four of objectives simultaneously. This Phase I feasibility study is focused on a proof-of-concept experiment to alleviate the HET dual-mode operational envelope limitation for both high thrust-to-power and high specific impulse. Starfire Industries believes that a &quot;low hanging fruit&quot; modification to HETs exists, and such an improvement would be evolutionary to enable multi-mission EP systems for NASA's Science Mission Directorate and DoD platforms. Towards this end, Starfire has partnered with Aerojet Corporation to rapidly demonstrate feasibility in Phase I through experimental modification to an existing HET system. If results are confirmed, a Phase II design can be driven to yield immediate upgrades for flight-qualified HET systems for near-term payback.
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6 CFM Electrochemical Hydrogen Pump and Compressor Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:11:32.000ZHydrogen is an essential resource for space missions. NASA has a need for equipment to generate, handle and store hydrogen. In terms of handling hydrogen, conventional rotating mechanical pumps and compressors require extensive modification and have limited reliability. Electrochemical pumping and compression of hydrogen occurs without any moving parts and is highly reliable and efficient. Sustainable Innovations has demonstrated up to 6,000 psi of compression using electrochemical cell hardware. However, for high flow applications, such as a 6 CFM hydrogen pump for NASA, a departure from traditional electrochemical cell hardware designs is needed. The proposed Expandable Modular Architecture cell design, allows a large variable footprint for the electrochemical stack. This is achieved using modular cell parts to create large active area cells. The modular parts are inexpensive to manufacture and can achieve the high tolerances need for large active area cells. The proposed Phase I activity will demonstrate a single cell Electrochemical Hydrogen Pump &amp; Compressor (EHPC) using the EMA design to validate the modularity of the cell components. The ability to stack large active area cells will also be demonstrated with a four cell EHPC. For both pieces of cell hardware, cycling a pneumatic device will be demonstrated. A manufacturing study will also be undertaken to validate the compatibility of the EMA design with cost reduction pathways. This will facilitate establishing the design criteria for a 3-4 CFM 1,000 psi EHPC to be constructed on Phase II
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Ullage Compatible Optical Sensor for Monitoring Safety Significant Malfunctions Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:33:20.000ZSignificant emphasis has been placed on aircraft fuel tank safety following the TWA Flight 800 accident in July 1996. Upon investigation, the National Transportation Safety Board (NTSB) determined that the explosion of the center wing tank (CWT) resulted most likely from ignition of the flammable fuel/air mixture. The growing concern of aircraft fuel tank safety has taken an added dimension in the post 9/11 world where both commercial and military aircrafts are vulnerable to terrorist attacks utilizing MANPADS (MAN-Portable Air Defense Systems), explosives in shoe/socks, and small arms fire. Fuel tanks also need protection from explosions caused by ballistic impact, lightning, and other sources of ignition. In Phase I, InnoSense LLC has demonstrated the feasibility of an all-optical oxygen sensor capable of detecting oxygen at 40,000 feet elevation down to the ambient level. This Phase II proposal discusses how InnoSense LLC would develop a prototype and perform field testing. The project team possesses seventy person-years of optical sensor related hardware and software expertise. InnoSense has attracted $300,000 in Phase III follow-on funding for further engineering. Innosense will deliver the prototype to NASA, complete with software, manuals, and schematics.