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- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-19T09:27:05.000Z
Academy of Program/Project & Engineering Leadership's Ask the Academy magazine past issues.
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:37:23.000Z
<p>The Armstrong Flight Research Center is NASA&rsquo;s primary center for atmospheric flight research and operations,&nbsp;with a vision &ldquo;to fly what others only imagine.&rdquo; We believe that flight validation and research is one of&nbsp;the crucial phases within the advancement of any NASA technology, and it is often the barrier to technology&nbsp;utilization by the private sector. We also believe that aerospace technology can be enhanced through flight&nbsp;early in the Technology Readiness Level (TRL) lifecycle. In fact, some research can be done only in flight. The&nbsp;CIF projects are examples of aerospace technologies that are theoretically advantageous but have had&nbsp;little TRL advancement or are at too early of a technology level for support through a NASA mission.</p><p>The focus for the program is on validating, developing, and testing new and innovative technologies.</p><p>The current&nbsp;technology areas for the projects included:<br />AFRC is currently looking into following Technical Capability areas (not in any priority order and not all inclusive):<br />1.&nbsp;&nbsp; &nbsp;Small launch Space Systems<br />Develop small launch space systems such as horizontal rockets that could launch to orbit small free-flying space platforms (e.g., cuestas, nanosats, picosats).<br />2.&nbsp;&nbsp; &nbsp;Altitude Compensating Rocket Systems<br />Design, build, and test altitude compensating rocket systems or sub-systems designed to operate the rocket efficiently across a wide range of altitudes. &nbsp;Subsystems such as Altitude Compensating Nozzles are being considered.<br />3.&nbsp;&nbsp; &nbsp;Aero Gravity Assist Systems<br />Design, build, and test an Aerogravity assist system which uses a close approach to the planet, dipping into the atmosphere, so the spacecraft can also use aerodynamic lift to further curve the trajectory.<br />4.&nbsp;&nbsp; &nbsp;Launch Vehicle and Spacecraft Adaptive Controls<br />Develop and test adaptive controls architectures speci?cally tailored for application to launch vehicles. &nbsp;Adaptive Controls for launch vehicles would include unique features of the &nbsp;aerospace vehicle, such as control-structure interaction, propellant slosh, sensor performance, and actuator dynamics. &nbsp;In addition, the analysis, veri?cation, and ?ight certi?cation framework for the control system must be addressed.<br />5.&nbsp;&nbsp; &nbsp;Autonomous Systems<br />AFRC is exploring concepts for advanced autonomous systems and collaborative autonomous operations that could be applied across aerospace vehicles to enhance effectiveness, survivability, and affordability.<br />6.&nbsp;&nbsp; &nbsp;Autonomy in a Safety Critical Framework<br />Armstrong Flight Research Center is interested in the flight demonstration of high level autonomy in a safety critical framework with applicability to man-rated air and space vehicles. &nbsp;This high level of autonomy is enabled through the use of multiple sensor platforms and algorithms with high computational demands. &nbsp;Increased computational capability through embedded high performance computing and implementation of resource efficient algorithms is needed to support this integration. &nbsp;Research into embedded high performance computing using multi-core processors, FPGA, GPU, DSP and associated development of toolchains and algorithms targeted to these platforms is needed in order to reduce the Size, Weight, and Power (SWaP) of the flight vehicles..<br />7.&nbsp;&nbsp; &nbsp;Space Weather Systems<br />Design, develop, and test measurement systems to provide the capability for on-demand, validated, and archived radiation measurements related to human tissue and avionics silicon upset co
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-19T08:59:04.000Z
Satellite-derived Ocean Color Data sets from historical and currently operational NASA and International Satellite missions including the NASA Coastal Zone Color Scanner (CZCS) (1978 - 1986), NASDA's Ocean Color Temperature Scanner (OCTS) (1996 - 1997), NASA/GeoEYE Sea-viewing Wide Field-of-view Sensor (SeaWiFS) (1997 - 2010), NASA's Moderate Resolution Imaging Spectroradiometer (MODIS) on both the Terra and Aqua spacecraft (2000 - present) and ESA's medium-spectral resolution, imaging spectrometer (MERIS) (2002 - present). <strong>Level-1A Data Products</strong> Level-1A products contain the raw radiance counts from all bands as well as spacecraft and instrument telemetry. Calibration and navigation data, and instrument and selected spacecraft telemetry are also included. Level-1A data are used as input for geolocation, calibration, and processing. <strong>Ocean Level-2 Data Products</strong> Each Level-2 product is generated from a corresponding Level-1A product.The main data contents of the product are the geophysical values for each pixel,derived from the Level-1A raw radiance counts by applying the sensor calibration, atmospheric corrections, and bio-optical algorithms. Each Level-2 product corresponds exactly in geographical coverage (scan-line and pixel extent) to that of its parent Level-1A product and is stored in one physical HDFfile. <strong>Ocean Level-3 Binned Data Products</strong> Level-3 binned data products consist of the accumulated data for all Level-2 data corresponding to a period of one day, 8 days, a calendar month, or a calendar year. Each Level-3 binned data product is stored in one or more HDF files. Each multi-file product includes a main file containing all product-level metadata and data for each bin that are common to all the binned geophysical parameters, and multiple subordinate files, each of which contains data of one binned geophysical parameter for all bins. Subordinate files must be read in conjunction with the associated main file. <strong>Ocean Level-3 Standard Mapped Image Products</strong> The Level-3 standard mapped image (SMI) products are image representations of binned data products generated from SeaWiFS, MODIS, OCTS or CZCS data. The data in each SMI product represents an image of the parameter specified by the global attribute Parameter. This object is a two-dimensional array of an Equidistant Cylindrical (also known as Platte Carre) projection of the globe. The values can be stored as bytes, 2-byte integers, or 4- byte floats. The first two are scaled real values and may be converted projected to geophysical values using the global attributes Scaling, Scaling Equation, Base, Slope, and Intercept. The standard SMI products are generated from binned data products, one for each of the following geophysical parameters: chlorophyll a concentration, angstrom coefficient, normalized water-leaving radiance at each visible wavelength, aerosol optical thickness, epsilon, and diffuse attenuation coefficient at 490 nm. For MODIS, products are generated for sea surface temperature (SST), 4 micron SST (SST4) and nighttime SST (NSST). Thus, each SMI product represents data binned over the period covered by the parent product. The arithmetic mean is used in each case to obtain the values for the SMI grid points from the binned data products. Each SMI product contains one image of a geophysical parameter and is stored in one physical HDF file.
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:26:19.000Z
A recently developed mathematical folding theory has great value for deployable space structures and in situ manufacture of large beams, panels and cylinders. The new technology offers diverse capacity to design, manufacture, and self-assemble periodically folded sheet material. The range of materials includes many customized core materials for laminated panels, cellular habitat walls, structural beams, parabolic reflectors, and efficient truss systems that can be packaged ideally as a roll of sheet material and deployed in space by inflation or passive radiation. The algebraic linkage conditions on the deployment of a folded structure forms an over-constrained system of equations. The deployment kinetics are only possible due to engineered relationships between the neighboring facet geometry, and globally requires a uniform angular change in fold extension across the pattern. This implies that fixing an individual fold angle fixes all of the fold angles in its neighboring region. If the fold angles are all made rigid, then the entire structure is highly over-constrained and forms a very robust truss system. The goal is to introduce the technology by demonstrating the diversity of folding architectures that can be directly applied to deployable space structures, and by developing the associated design and simulation software to transfer this know-how to the engineering community.
- API 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>
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:13:00.000Z
Colorado Power Electronics (CPE) has built an innovative modular power processing unit (PPU) for Hall Thrusters, including discharge, magnet, heater and keeper supplies, and an interface module. The innovations of this high-performance PPU are its resonant circuit topologies, magnetics design, modularity, and its stable and sustained operation during severe Hall effect thruster current oscillations. Laboratory testing at NASA Glenn Research Center (GRC) has demonstrated discharge module efficiency of 96% with is considerably higher than current state of the art. The purpose of the Phase II project is to develop an Engineering Model HiVHAc PPU that includes a digital control interface unit (DCIU) to TRL 6. This will position CPE to manufacture a qualification model PPU as a Phase III project. The prototype digitally-controlled flow controller with a PC interface developed in Phase I will serve as the foundation for a combination DCIU-Flow module to be added to the PPU in Phase II. Thermal and vibration Finite element analysis (FEA) will be performed on the reduced-mass chassis designed in Phase I, and then a test brassboard PPU will be built and tested. Additionally, the control loops of the PPU will be analyzed and a stress analysis will be performed. The test PPU will be a deliverable to NASA GRC. The results of the analysis and testing will be used to design and build an engineering model flight-like PPU that includes flight-like wire harnessing schemes, EMI filtering, enhanced modularity and the new DCIU-Flow module. At the beginning of the project, the TRL of the PPU is between 4 and 5, the TRL of the DCIU is 2, and the TRL of the valve driver is 3. At the conclusion of the Phase II effort the PPU/DCIU will be at TRL 6.
Aeroservoelastic suppression of LCO due to free-play using a combined analytical and experimental approach Projectnasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:34:45.000Z
Aerodynamic control surfaces with excessive free-play can cause limit cycle oscillations (LCO), a sustained vibration of constant amplitude that is caused by a combination of aeroservoelastic effects and free-play. The LCO can impact handling qualities, ride quality and can cause structural fatigue, ultimately leading to structural failure. Due to the negative impacts of free-play induced LCO, very stringent absolute free-play limits have been established for control surfaces on both military and commercial aircraft. Systems Technology, Inc. (STI) and Boeing propose to develop an innovative, robust, and reliable active control concept that alleviates the adverse effects of control surface free-play, relieving costly requirements associated with manufacturing, inspection, and part replacement. The solution involves a novel linear fractional transformation framework for relevance to models of varying complexity and a robust control approach that exploits the piecewise-linear nature of the free-play nonlinearity. To aid in control design and to provide practical real-world relevance, a combined analytical and experimental approach is proposed by the STI-Boeing team. The proposed solution is minimally intrusive, providing for application to a wide array of existing and future aircraft (including both high speed fighters and transport aircraft), ultimately resulting in significant cost savings and increased pilot safety.
- API data.nasa.gov | Last Updated 2020-01-29T03:41:20.000Z
Venus, despite being our closest neighboring planet, is under-explored due to its hostile environment. The atmosphere is composed primarily of CO2, with a 92 bar pressure and 467°C temperature at the surface. The temperature decreases at higher altitudes, approaching conditions similar to that of Earth’s surface at 65km. Due to more moderate conditions above 50 km, balloon missions have survived as long as 46 h at an altitude of 54 km. However, due to the opacity of the Venus atmosphere, orbital/balloon observations at such altitudes are not capable of characterizing the surface. The recent decadal survey for Planetary Science (2013-2022) and VEXAG study (2014) emphasized the need to gather basic information on the crust, mantle, core, atmosphere/exosphere and bulk composition of Venus through in situ investigations, using low-altitude aerial platforms or land probes. The hostile conditions prevalent at low altitudes and on the surface of Venus have limited the low-altitude aerial or surface missions to a few hours (Russian Venera landers <2 h), due mainly to the lack of adequate thermal resilience of electronics and power sources. Since photovoltaic and nuclear power sources are currently inapplicable at low altitudes, there is a crucial need for new long-lasting power technology concepts to enable extended low-altitude aerial missions. We propose to develop a novel Venus Interior Probe Using In-situ Power and Propulsion (VIP-INSPR) architecture for sustained Venus atmospheric exploration. The probe utilizes H2 and O2, harvested through electrolysis of sulfuric acid/water to supplement fuel carried from Earth, in order to supply a solid oxide fuel cell (SOFC) for power generation at low altitudes, and to supplement H2 as a buoyancy gas for the ascent/descent of a balloon. The major components include: i) A high temperature reversible SOFC, ii) Chemical hydride for H2 storage, iii) A H2 buoyancy-based altitude control system, and iv) A solar array, to generate power in the upper atmosphere. A solar array will power the probe at high altitude and the SOFC will provide power at low altitudes using H2 and O2 carried from Earth. Both H2 and O2 will be regenerated through electrolysis of the water produced in the fuel cell (a closed–system) at high altitudes. Additionally, these reactants will be replenished by electrolyzing either H2SO4 or H2O harvested from the Venus atmosphere at high altitudes to compensate for the loss of H2 from the balloon and/or water from the fuel cell. This novel architecture enables generation of fuel from in-situ resources at high altitudes, power at low altitudes, and transport gas for the balloon. In contrast to earlier Venus probes, our Venus probe is designed to survive the range of hostile environments on Venus without the need for thermal management. Cycling between high and low altitudes (e.g., 65k to 15km), the probe can be utilized as a long duration low-altitude aerial platform for Venus exploration. This would enable new scientific studies on the Venus inner atmosphere and surface geology using advanced analytical and imaging techniques. The component technologies used here, i.e., metal hydrides, SOFC and a high-temperature solar array, have terrestrial relevance and will enable a new mission paradigm for Venus exploration. In Phase-1, we formulated the requirements of the component technologies and identified the materials based on thermal stability and performance. We have established an appropriate protocol for the lowaltitude and high-altitude transitions of the probe and developed a preliminary design for a 150kg balloon. In Phase-II, we will continue this development, focusing on key aspects relevant to a broader range of missions, identifying and advancing enabling technologies and developing a technology road map for incorporation in future Venus missions. We expect maturation of this concept at the end of the project to TRL 3.
- API stat.cityofgainesville.org | Last Updated 2016-08-29T03:33:44.000Z
- API opendata.utah.gov | Last Updated 2020-03-20T15:43:53.000Z
This dataset depicts oil and gas well points in Utah from the Utah Department of Natural Resources, Oil Gas and Mining Division. The dataset contains the API code, well and company name, account number, filed number, field name, elevation, locations coordinates, lease numbers, well type and status, total cumulative oil, gas and water, and more. More information at: http://gis.utah.gov/data/energy/oil-gas/