- API data.nasa.gov | Last Updated 2020-01-29T02:15:54.000Z
Two primary paths are available for the creation of a Rad-Hard ASIC. The first approach is to use a radiation hardened process such as existing Rad-Hard foundries. These foundries use special processing steps to decrease the total ionizing dose issues, but do not reduce the single event effects. The second approach is to use a special standard cell library containing hardening techniques that can be built on a standard state-of-the-art commercial foundry. This cell library must compensate for the unhardened foundry by using special layout techniques to retain the ability to operate through the total ionizing dose experienced in the radiation environments. These techniques are generally referred to as radiation hardened-by-design layout techniques (RHBD). For hardening of the circuit architectures against upsets from the single event effects, both the commercial and the Rad-Hard foundries must incorporate some type of mitigation scheme requiring special transistor interconnects or redundant nodes. This program will fill this void, providing the space community with the ability to easily acquire the RHBD Micro-RDC standard cell libraries for use with commercial ASIC design flows. The library will include a full suite of IO pads designed by Micro-RDC and successfully implemented in test chip designs at 90nm and 65nm. Finally, a portion of the custom via programmable structured ASIC fabric designed by Micro-RDC and Viasic will be made available to the library users. This fabric can be embedded into a design which can be modified and reprogrammed by generating just via 3 mask layer, which can lead to a substantial cost savings over a complete new ASIC design. This program will allow Micro-RDC to transform its custom libraries into synthesis libraries, and enable other companies the opportunity to use a proven and fully characterized RHBD ASIC cell library and suite of Mega Cell hard IP for rapidly developing spaceborne systems.
NASA Financial Budget Documents, Strategic Plans and Performance Reports 2009: NASA Performance Plandata.nasa.gov | Last Updated 2020-01-29T02:00:44.000Z
NASA Financial Budget Documents, Strategic Plans and Performance Reports for fiscal year 2009.
- API data.nasa.gov | Last Updated 2020-01-29T03:41:37.000Z
<p>The Advanced Manufacturing Technologies (AMT) Project supports multiple activities within the Administration's National Manufacturing Initiative. A key component of the Initiative is the Advanced Manufacturing National Program Office (AMNPO), which includes participation from all federal agencies involved in U.S. manufacturing. In support of the AMNPO the AMT Project supports building and Growing the National Network for Manufacturing Innovation through a public-private partnership designed to help the industrial community accelerate manufacturing innovation.</p> <p>The National Network for Manufacturing Innovation (NNMI) will be built through a public-private partnership designed to help the industrial community rapidly commercialize manufacturing innovation in part by sharing the financial risk of developing advanced manufacturing technologies capable of accelerating product introduction, lowering product costs and improving product performance. NASA will support the regional IMI's to provide access to an innovation ecosystem consisting of a broad array of technologies, collaborations and resources for rapidly advancing middle-stage research and development (i.e. an industrial commons). NASA will support specific activities of the regional IMIs to include: 1. Capture greater value from early-stage US research investments by enabling manufacturing scale-up and commercialization in the US. 2. Retain production in the US thereby providing insight into next generation, high-value products leading to future high-wage and highly skilled jobs in the US. 3. Lower the financial risk associated with manufacturing R&D by leveraging public and private investment and spreading costs and risks among industrial partners. 4. Generate hands-on advanced manufacturing internships and learning and training opportunities for students and those seeking to re-enter the workforce. 5. Coordinate and build strategic partnerships between federal, state, university, community college, and industrial entities to make each more productive in advancing regional and national manufacturing agendas and policies. 6. Provide small and medium-sized enterprises (including large corporate supply chain partners) virtual and physical proximity to nascent manufacturing expertise in high-performance computing, manufacturing equipment and research laboratories currently beyond their reach. The NNMI will coordinate capabilities across regional IMIs providing companies with access to a talented, diverse, and high-performance workforce and the best technology and practices to address their production challenges. Network-wide benefits of the NNMI include the ability to: 1. Maximize the innovative outcome of the NNMI investment by coordinating multi-IMI responses to industry problems. 2. Network with trusted scientists, engineers and technicians in the most relevant focus areas to drive innovation and accelerate technology breakthroughs and their assimilation to industry. 3. Identify and coordinate the sharing of IMI best practices in service to industry needs. 4. Support the rapid growth of an advanced manufacturing workforce by coordinating the development of educational resources between regions. 5. Bring about greater employment opportunities for the US workforce and help companies to find and retain the best people by disseminating internship and employment opportunities. </p>
- API data.nasa.gov | Last Updated 2020-01-29T03:24:10.000Z
Busek Co Inc proposes to develop a high power (high thrust) electric propulsion system featuring an iodine fueled Hall Effect Thruster (HET). The system to be developed will include a thruster, hollow cathode, and condensable propellant feed system. Busek Co. Inc. proposes to develop a high power (high thrust) electric propulsion system featuring an iodine fueled Hall Effect Thruster (HET). The system to be developed will include a thruster, hollow cathode, and condensable propellant feed system. The nominal power level of the thruster developed in this program will be 20 to 50 kW. The thruster can be clustered to support ~200 kW class missions to the moon, Mars, and beyond. In a future program, the technology can be scaled to ~100 kW per thruster to support MW-class missions. The available specific impulse can be throttled between 1500s to will be as high as 3000 to 4000 s. The use of iodine propellant enables significant mass and cost savings for lunar and Mars cargo missions, including Earth escape and near-Earth space maneuvers. High purity iodine is readily available commercially in large quantities at a fraction of the cost of xenon. Iodine stores at a density that is 3 times greater than xenon and at less than one thousandth of the pressure. Thus, iodine may be stored in low volume, low mass, low cost propellant tanks instead of the relatively large, high pressure, high cost COPV tanks required for xenon Hall thruster systems. Busek has already demonstrated a low power (several hundred watts) iodine thruster system based upon its flight qualified BHT-200 thruster. At most points, the efficiency are the same or nearly the same given experimental uncertainty. However, iodine may have a significant performance advantage at high power: Iodine yielded significantly higher specific impulse and thrust to power at higher input power. This effect will be investigated with the proposed high power system.
- API data.nasa.gov | Last Updated 2020-01-29T02:09:37.000Z
<p>This research is an innovative approach to fuse the rapid advancements in miniaturized high-speed electronics with the ultra-compact freeform optical design from our FY16 efforts to create the next generation of stellar scanner instruments.</p><p>The objective of this project is to develop a novel star scanner sensor prototype for integrated Cubesat structures that desire streamlined Guidance, Navigation and Control (GN&C) components. This prototype will be the first star scanner developed to slide into a frame and can be easily swapped with other components. This modularity would <em>significantly</em> reduce CubeSat development time, cost, and integration.</p><p>The four primary objectives are to develop new freeform optical alignment methods for the mechanical structure. Next, utilize/manufacture a sensor electronics board with a slim volume and develop mature signal processing algorithms specifically for attitude determination software. Last, perform a trade study on emerging detector technology, that promises ~20% (or greater) noise reduction for Goddard Cubesat sensor and instruments.</p><p> </p><p> </p>
Low Cost Resin for Self-Healing High Temperature Fiber Reinforced Polymer Matrix Composites, Phase Idata.nasa.gov | Last Updated 2020-01-29T05:01:22.000Z
Over the past few decades, the manufacturing processes and our knowledge base for predicting the bulk mechanical response of fiber reinforced composite materials has matured and opened the capability to design lightweight materials. The rapid development and progress of composites technology has been spawned by the high specific strength, stiffness, and toughness offered with respect to other engineering materials. However, the performance of a composite material is heavily influenced by the strength and toughness of the polymer matrix, which binds the high stiffness fibers into a cohesive element. Unfortunately, the highly cross-linked polymers necessary to achieve the high Tg required by propulsion systems are costly and prone to brittle fracture under even small elastic deformations. While the rigidity of the polymer is required for practical applications, the lack of resistance to crack propagation leads to damage prone materials. This proposed SBIR will develop a new low cost self-healing thermosetting polymer which exhibit high Tg (>550 F), high strength, stiffness and toughness from a room temperature low viscosity resin that allows processing without heating the polymer. The self-healing properties of polymer will yield increased reliability of the composite and reduced maintenance costs. HARP Engineering will formulate a polymer that meets or exceeds both the performance and cost metrics required by NASA through the use of multifunctional self-healing resins. This Phase I will perform mechanical testing of the resin at elevated temperatures and layup composites for ASTM testing to demonstrate the high specific strength, stiffness, and toughness compared to existing high temperature resins.
- API data.nasa.gov | Last Updated 2020-01-29T04:00:13.000Z
Rocket plume impingement may cause significant damage and contaminate co-landed spacecraft and surrounding habitat structures during Lunar landing operations. Under this proposed SBIR program, CFDRC and the University of Florida will develop an innovative high-fidelity simulation system for predicting surface erosion and debris transport caused by rocket plume impingement on lunar surface. This simulation system will combine 1) a unified continuum-rarefied flow solver capable of simulating plume impingement flow in lunar vacuum, 2) granular flow solid-fluid interaction technology for developing lunar soil grain erosion and debris particle release mechanism models, and 3) particle tracking tools to simulate debris kinetics, dispersion and contamination after liberation. In Phase I, the plume stagnation layer flow conditions at the soil surface will be modeled and computed. The solid-fluid interaction physics in the soil layer in response to this surface flow environment will be simulated and a generalized soil erosion model will be derived. The erosion model will then serve to prescribe debris mass and initial conditions for the debris-tracking module embedded in the flow solver. In Phase II, the individual modules will be combined into a single simulation system. The simulation system will be essential for predicting the severity and range of dust and debris transport and for designing lunar settlement layout, dust and debris impact mitigation measures. He will spend at least 35 % of his time on this project and his commitment to other projects is less than 50 %.
Cost-Effective ISS Space-Environment Technology Validation of Advanced Roll-Out Solar Array (ROSA), Phase IIdata.nasa.gov | Last Updated 2020-01-29T04:58:30.000Z
DSS proposes to systematically mature, mitigate risk for; and perform hardware-based ground validations / demonstrations of a low-cost, high technology payoff, ISS-based flight experiment that will allow key relevant space-flight environmental validation of our innovative Roll-Out Solar Array (ROSA) technology. The ROSA flex-blanket solar array technology provides game-changing affordability and performance, and delivers a performance paradigm shift in terms of: significantly lower cost, greater specific power, more compact stowage volume, higher structural performance, less complexity, and more modularity / scalability than state-of-the-art solar arrays. A critical aspect of readying the enabling ROSA technology for infusion into potential end-user applications is to increase the TRL to 7+ via test / analytical validation of hardware in a relevant spaceflight environment for: Deployment, Deployed Dynamics and Photovoltaic Power Production. The ISS provides a ready and cost-effective relevant space environment (zero-G, vacuum and solar illumination/thermal) test-bed for the validation of these key technology areas via the straightforward flight experiment proposed. The Phase 2 effort is intended to lead to the definition of a comprehensive and test-validated ISS-based ROSA experiment design and operations plan that will facilitate / accelerate an ISS experiment manifest / review / approval process to significantly shorten the time to flight. The program includes: comprehensive risk mitigation for the flight experiment that includes hardware-based testing / ground simulation of experiment operations (including ISS structure and robotic arm interfaces) with functional and flight-like experiment hardware and generation of documentation to facilitate ISS flight experiment board requirements, integration, operations and safety reviews.
- API data.nasa.gov | Last Updated 2020-01-29T04:17:08.000Z
We propose to develop a Multi-Element Lean Direct Injection, ME-LDI, Combustion concept with the following innovative features: 1. Independent, mini burning zones created by containing the flame in a cylinder downstream of each fuel injector/swirler element in a multiple fuel injector array, see figure 1. The independent burning zones will enable fuel staging the fuel injectors (turning off fuel to selected fuel injectors) to cover the operating cycle, such that at each point of the operating cycle the combustor will have high combustion efficiency (>99%) and low NOx emissions. At high power conditions the combustion efficiency should be greater than 99.9%. 2. A low flow number, "Butterfly" fuel injector will be incorporated into ME-LDI that is low cost and simple to manufacture but a highly effective atomizer. The term "Butterfly" derives from the butterfly shape of the spray. The shape of the spray is formed by two diametrically opposed slots cut through a closed end fuel tube, see figure 2. The fuel flow through each slot forms a fan spray. The slot width can be varied to control drop-sizes within the spray.
- API data.nasa.gov | Last Updated 2020-01-29T01:42:45.000Z
We propose to develop an innovative Autonomous Flight Safety Inference Engine (AFSIE) system to autonomously and reliably terminate the flight of an errant launch vehicle. This proposed phase 1 research is innovative in that it combines proven NASA-developed AFS algorithms, real-time hazard assessment algorithms and hazard envelopes generated from Joint Advanced Range Safety System Real Time (JARSS RT) and an on-board vehicle simulator into a refined onboard software inference engine that monitors navigation states, mission flight rules and onboard anomaly instrumentation. An autonomous flight safety system must be able to reliably perform accurate and autonomous navigation so as to determine the vehicle position, velocity and attitude states in real time. Reliability requirements for AFS are high due to stringent loss-of-life constraints, often leading to redundant navigation sensors with attendant cost impacts. Our innovative solution proposes to satisfy RCC accuracy and reliability requirements by exploiting the low-cost COTS sensor and processor architectures that are currently being baselined for the Common NanoSat/Launcher Avionics Technology (CNAT) study and a Nano launch vehicle avionics design. This dual use hardware implementation will greatly reduce the recurring costs for the production of an autonomous flight safety system. This has significant implications for reducing the costs for launch vehicles, particularly Nano and Micro Satellite Launch Vehicles (NMSLV), where range safety costs currently consume a burdensome percentage of the launch cost. Under this proposed phase 1 effort, we will 1) identify the range requirements and develop a plan for range safety for approval of the system, 2) identify reliable low-cost COTS hardware that satisfies the range accuracy and reliability requirements and, 3) develop an end to end simulation to demonstrate the AFSIE Concept of Operations.