Monolithic Power Integrated Circuits for Merging Power Electronics, Management, and Distribution, Phase Idata.nasa.gov | Last Updated 2018-07-19T08:23:32.000Z
APIQ Semiconductor proposes development of a scalable, wide bandgap (WBG) monolithic power integrated circuit (MPIC) technology for power electronic conversion, management, and distribution. The proposed WBG microelectronics are to be based upon low defect, homogeneous gallium nitride (GaN) based materials using native GaN substrates. The technology to be developed will replace silicon power switches and drivers in power electronics systems to yield high efficiency, high density, reliable module based systems. Inclusive in the proposal are devices for 1200 V or more power switching and digital integration. Devices will be evaluated for high temperature and heavy ion radiation hardness, with performance improvements over competing technologies expected from low materials defects and carefully managed electric field profiles.
- API data.nasa.gov | Last Updated 2018-07-19T02:46:54.000Z
Galileo Orbiter Magnetometer (MAG) calibrated high-resolution data from the Earth-2 flyby in spacecraft, GSE, and GSM coordinates. These data cover the interval 1992-11-03 to 1992-12-19.
- API data.nasa.gov | Last Updated 2018-07-19T15:57:23.000Z
JEM Engineering proved the technical feasibility of the FlexScan array?a very low-cost, highly-efficient, wideband phased array antenna?in Phase I, and stands ready to develop it into a fully-functional, flight-qualifiable prototype in Phase II. JEM developed an S-Band (2.0-2.3 GHz) antenna array design appropriate for the stratospheric balloon application through requirements definition, modeling, and performance predictions. The critical technology for this array is an electrically-controlled Variable Delay Line (VDL), used to provide true time-delay for beamsteering. VDLs were designed, built and tested, and shown to have excellent performance. The VDLs were tested over 2.4 million cycles without degradation, indicating good life, especially for the balloon application. A 4-port linear beamformer was built, and used to validate the beamformer concept. The objective of the proposed 24-month Phase II effort is to develop, prototype, and demonstrate a flight-qualifiable FlexScan phased array that achieves the bandwidth, antenna gain, and scan range required for a balloon-borne TDRSS data link in S-band, while meeting environmental requirements. Upon completion of Phase II, the FlexScan array will be ready to commercialize for the balloon-borne application, with other NASA and non-NASA commercial applications soon to follow.
Generating Autoclave-Level Mechanical Properties with Out-of-Autoclave Thermoplastic Placement of Large Composite Aerospace Structures, Phase Idata.nasa.gov | Last Updated 2018-07-19T13:25:16.000Z
Out-of-autoclave thermoplastic tape/tow placement (TP-ATP) is nearing commercialization but suffers a moderate gap in mechanical properties compared with laminates fabricated via thermoset autoclave processing. Out-of-autoclave thermoplastic processing significantly lowers composite aerospace part costs, but the property gap must be closed. This STTR program, endorsed herein by Boeing and Cytec Engineered Materials, will remedy the mechanical property shortfall and enable large composite aerospace structure important to NASA to be manufactured without an autoclave. Accudyne is teaming with University of Delaware -- Center for Composite Materials to apply their state-of-the-art TP-ATP process/property models to elucidate the physical mechanisms affecting microstructural quality that cause the property gap. Models will be applied to the NASA LaRC TP-ATP deposition head to optimize the head configuration and machine operating parameters, and the control systems for full mechanical properties. Laminates will be manufactured to demonstrate the property improvements. The process, head, and equipment changes will be upgraded on the NASA-LaRC thermoplastic tape head. In Phase 2, process/head modeling will be extended through laminate fabrication and testing, and a component of interest to NASA will be fabricated demonstrating the improved "autoclave level" mechanical performance.
- API data.nasa.gov | Last Updated 2018-07-19T05:24:08.000Z
This dataset is comprised of asteroid flux data measured in 26 filters using the McCord dual beam photometer, and covering the range 0.32 - 1.08 microns for 285 numbered asteroids, as published in Chapman & Gaffey (1979b) and McFadden, et al. (1984).
- API data.nasa.gov | Last Updated 2018-07-19T09:51:31.000Z
In the Phase I program, Busek Co. Inc. tested an existing Hall thruster, the BHT-8000, on iodine propellant. The thruster was fed by a high flow iodine feed system, and supported by an existing Busek hollow cathode flowing xenon gas. The Phase I propellant feed system was evolved from a previously demonstrated laboratory feed system. Throttling of the thruster between 2 and 11 kW at 200-600V was demonstrated. Testing has shown that the efficiency of iodine fueled BHT-8000 is the same as with xenon, with iodine delivering slightly higher thrust to power (T/P). Plume current was also measured at a variety of operating conditions. Preliminary design work for a new thruster to be built in Phase II was also completed. In Phase II a complete iodine fueled system will be developed including the thruster, hollow cathode, and iodine propellant feed system. The nominal power of the Phase II system is 8 kW. However, it can be deeply throttled as well as clustered to much higher power levels. The technology can also be scaled to >100 kW per thruster to support MW-class missions. The target thruster efficiency for the full scale system is 65% at high Isp (~3000 s) and 60% at high thrust (Isp~2000 s). These projections are based on Phase I testing and prior testing of higher power thrusters. Iodine enables dramatic mass and cost savings for lunar and Mars cargo missions, including Earth escape and near-Earth space maneuvers. High purity iodine is available commercially in large quantities at much lower cost than xenon. Iodine stores at 2 to 3 times greater density than xenon and at approximately one thousandth of the pressure and may be stored in low mass, low cost propellant tanks instead. Passive, long term storage of a fully fueled system is feasible including storage in conformal tanks which may be used to shield internal components against some types of space radiation.
- API data.nasa.gov | Last Updated 2018-07-19T09:03:13.000Z
Under a Phase 1 effort, IES successfully developed and demonstrated a spark ignition concept where propellant flow drives a very simple fluid mechanical oscillator to excite a piezoelectric crystal. The Phase 1 effort exceeded expectations, with the device demonstrating reliable ignition of both hydrogen and propane fuels, and achieving in excess of 1 million impact cycles (40,000 start cycles) during fatigue testing without measureable degradation. Several spin-off concepts were also identified that provide additional options for improving spark ignition system design. For Phase 2, IES proposes an accelerated, 18 month effort to refine design concepts and analysis tools, and then develop specific ignition system designs for two customer applications, with the intention of having these ignition systems demonstrated in engine ground testing during Phase 2 and ready to start flight qualification immediately following the Phase 2 effort. Both customers (United Launch Alliance and Pratt Whitney Rocketdyne) have expressed interest and commitment in participating in the Phase 2 activity, making engines and facilities available for development testing, and integrating any resulting viable products into their flight engines. The ULA application is a new gaseous bipropellant H2/O2 attitude control thruster, for which the piezoelectric igniter is ideal as a simple, direct ignition source. The PWR application is for an evolved RL-10 study currently underway, for which the piezoelectric system might be scaled up or used as a pilot igniter for a torch, or make use of another spin-off concept that was identified during the Phase 1 effort. The timing of this Phase 2 effort coincides perfectly with near term needs of both these customers, as well as for other small engine applications in work to replace catalytic hydrazine engines with bi-propellant engines that will require a simple and reliable ignition source.
- API data.nasa.gov | Last Updated 2018-07-19T02:46:12.000Z
This dataset contains calibrated images of comet 103/P Hartley 2 acquired by the Medium Resolution Visible CCD (MRI) from 05 September through 26 November 2010 during the Hartley 2 encounter phase of the EPOXI mission. Clear-filter and CN images of the comet were acquired throughout this phase; OH, C2, and dust continuum images were only acquired for several days spanning closest approach.
Lightweight and Compace Multifunction Computer-Controlled Strength and Aerobic Training Device, Phase Idata.nasa.gov | Last Updated 2018-07-19T09:03:34.000Z
TDA Research proposes to develop a computer-controlled lightweight and compact device for aerobic and resistive training (DART) to counteract muscular atrophy and bone loss and to improve the overall wellness of astronauts operating in microgravity. The DART will be able to provide resistive loads up to 350 lbf and will accurately simulate the load profile of a mass in a 1-g environment. It will also be capable of applying custom load profiles such as eccentric overloading. In aerobic training mode, the DART will simulate the loads of a rowing machine with loads up to 175. The system will computer-controlled and can automatically calibrate to a user's range of motion. The total weight of the device will be less than 20 lbs and have a compact form factor to enable integration into a small crew module. By using a regenerative energy recovery system, the average power consumption of the DART will be less than 100 W during an exercise session. TDA is able to build on previous experience building exercise equipment for NASA and develop the DART in a short timeframe. TDA will prove the feasibility of providing effective aerobic and resistive training with a single device that is lightweight and compact in Phase I. At the end of Phase I a prototype will be delivered to NASA for evaluation. In Phase II we will advance the technology and provide the second generation prototype to NASA for testing on the International Space Station.
- API data.nasa.gov | Last Updated 2018-07-19T10:53:04.000Z
<p>The project will develop a system of 3D-printed connectors that can be used as a kit of parts to connect inflatable air beams to form a variety of spacecraft interior outfitting components. Examples of inflatable IVA structures that can be assembled include crew quarters, waste & hygiene compartment, crew medical restraint system, splints, science payload racks, stowage and other equipment racks, science glove box, recreational devices, other portable devices, work surfaces and other workstations, support braces, other secondary structures, etc. This inflatable technology can enable such hardware to be packaged in much smaller volumes for delivery in logistics flights or potentially to be integrated within inflatable spacecraft, increasing trade space options. Crew can also reconfigure spacecraft in-flight, using the ability to 3D-print custom connectors to redesign living spaces or create entirely new interior architectures to respond to mission developments or psychosocial needs.</p> <p>The Habitabiltiy Design Center has already prototyped scale models of inflatable crew stations and initial prototypes of a standard interface connector. These connectors have demonstrated basic capability, but are too large relative to the airbeams for pracitcal use. We have a notional reduced size connector and will use this concept as a starting point, to fabricate and test under operational inflation pressures. Pending initial success, we will fabricate various connectors to provide several linear and angled connections. This will form the basic building block for assembly of a variety of crew stations and support hardware.</p><p> </p><p>This research addresses HAT Needs Numbers 12.1.a and 12.1.b and provides steps towards several HAT-specified performance targets: Bladder Material Selection: The potentially frequent cycles of inflation and deflation experienced by IVA inflatable structures will require bladder material and seal interfaces capable of resisting puncture, tear, flex cracking, or other damage due to folding, handling, or stowage temperatures. Predictive Modeling of Deployment Dynamics: Inflation or deflation may involve imparted torques and loads that require IVA inflatable structures to be anchored to the spacecraft secondary structure prior to the initiation of inflation or deflation. Lightweight Structures and Materials Optimization to Realize Structural System Dry Mass Savings (Minimum of 20-25%) and Operational Cost Savings: The inflatable air beam and connector technology offers significant dry mass savings over traditional IVA structural materials. Structural mass savings for an individual crew quarters is expected to be in excess of 75% over ISS crew quarters.</p><p> </p><p>The intended product deliverable of this activity includes three airbeams of at least 12-inch length and no less than one each of the following: 90-degree connector, 45-degree connector, 180-degree connector, 90-degree five-airbeam connector, 60-degree three-airbeam connector. Additionally, a test report and CAD models for each connector will constitute deliverables of this activity.</p><p> </p><p>Upon completion of this initial ICA effort, we will be able to demonstrate use of the airbeams in conjunction with existing Logistics to Living Modified Cargo Transfer Bags (MCTBs) to demonstrate deployable partitions as an initial example case. This demonistration will be helpful in explaining the potential for continued investment to reduce both mass and habitability risks. We will continue to pursue research funding for further development and will also pursue options to directly engage exploration programs to generate solutions for their specific mission architectures.</p>