- API data.nasa.gov | Last Updated 2018-07-19T08:48:16.000Z
<p>In spite of our best efforts to minimize the amount of disposable supplies (and the associated packaging) used during space missions, the accumulation of solid wastes is an inevitable consequence of mission activity. That waste will occupy precious cargo or living space within the habitat unless it is properly managed. Converting solid wastes to an energy source presents a potential solution to this problem. Waste-to-energy (WTE) presents a viable solution to this problem in that the solid wastes can be converted into an energy source for use during a mission. Because this fuel is generated using available resources, it significantly offsets the initial mission logistics requirements, and provides several operational benefits and opportunities. WTE also addresses several terrestrial challenges related to our energy needs, environmental conservation, and our need to more efficiently use land resources. This study will produce a detailed chemical and thermodynamic model of a deep-space exploration waste stream. The model will be used in designing technologies for WTE systems within the Advanced Exploration Systems (AES) program and can also provide a starting point for commercial WTE systems.</p>
- API data.nasa.gov | Last Updated 2018-07-18T20:18:14.000Z
This grouping contains the compressible-flow cases from the 1980-81 Data Library.
- API data.nasa.gov | Last Updated 2018-07-19T22:59:10.000Z
The operating conditions of conventional multijunction solar cells are severely limited by the current matching requirements of serially connected devices. The goal of this SBIR program is to enhance the operating tolerance of high efficiency III-V solar cells by employing nanostructured materials in an advanced device design. By using quantum wells and quantum dots embedded in a higher band gap barrier material, solar cell devices that avoid the limitations of current matching can be constructed. This Phase I effort will focus on quantifying the trade-offs between short circuit current and open circuit voltage in InGaP / InGaAs nanostructures. Ultimately, the technical approach employed in this program has the potential of achieving conversion efficiencies exceeding 50% with a single p-n junction device, enabling improved overall performance and lower manufacturing costs than existing technologies.
- API data.nasa.gov | Last Updated 2018-07-19T08:30:15.000Z
<p>The proposed work seeks to design, develop and test a hard impact penetrator/sampler that can withstand the hard impact and enable the sample to be returned to orbit. Tether technology for release of the penetrator and capture of the sample eliminate many of the restrictions that presently inhibit the development of sample return missions.<p/><p>Since the Apollo era, sample return missions have been primarily limited to asteroid sampling. More comprehensive sampling could yield critical information on the formation of the solar system and the potential of life beyond Earth. Hard landings at hypervelocity (1-2 km/s) would enable sampling to several feet below the surface penetration while minimizing the Delta V and mass requirements. Combined with tether technology a host of potential targets becomes viable. The proposed work seeks to design, develop and test a hard impact penetrator/sampler that can withstand the hard impact and enable the sample to be returned to orbit. Tether technology for release of the penetrator and capture of the sample eliminate many of the restrictions that presently inhibit the development of sample return missions. The work builds upon in hypervelocity laboratory testing that use 1" Al projectiles that investigate crater formation and penetration through hard surfaces. The proposed work will enable realistic size (6" diameter) projectiles to be studied by taking advantage of the development of cheap high power commercial rocket motors that will enable impacts up to Mach 2 for Phase I. With this data, methodologies for studying higher velocity impacts can be developed along with mission scenarios to test the viability of mission return samples in the near future. Successful development of sample return capabilities will provide a major impetus for solar system exploration.</p>
- API data.nasa.gov | Last Updated 2018-08-02T15:25:24.000Z
This grouping contains the incompressible-flow cases from the 1980-81 Data Library.
- API data.nasa.gov | Last Updated 2018-07-19T22:50:56.000Z
Embedded Dual-Function Arc Fault Circuit Breaker/ Locator based on OSA, Phase I
- API data.nasa.gov | Last Updated 2018-09-05T23:02:22.000Z
This data set contains Calibrated data taken by the New Horizons Solar Wind Around Pluto instrument during the Pluto encounter mission phase. This is VERSION 3.0 of this data set. This data set contains SWAP observations taken during the the Approach (Jan-Jul, 2015), Encounter, Departure, and Transition mission sub-phases, including flyby observations taken on 14 July, 2015, and departure and calibration data through late October, 2016. This data set completes the Pluto mission phase deliveries for SWAP. This is version 3.0 of this dataset. Changes since version 2.0 include the addition of data downlinked between the end of January, 2016 and the end of October, 2016, completing the delivery of all data covering the Pluto Encounter and subsequent Calibration Campaign. Also, updates were made to the calibration files, documentation, and catalog files. Finally, downlink data several days beyond the end of the nominal end of mission phase were included in this data set in an attempt to fill out the products at the nominal end of mission phase; refer to the CONFIDENCE_LEVEL_NOTE in this data set catalog for more details.
- API data.nasa.gov | Last Updated 2018-07-19T23:28:49.000Z
Cloud-Aerosol Lidar and Infrared Pathfinder Satellite Observations (CALIPSO) was launched on April 28, 2006 to study the impact of clouds and aerosols on the Earth’s radiation budget and climate. It flies in formation with five other satellites in the international “A-Train” (PDF) constellation for coincident Earth observations. The CALIPSO satellite comprises three instruments, the Cloud-Aerosol LIdar with Orthogonal Polarization (CALIOP), the Imaging Infrared Radiometer (IIR), and the Wide Field Camera (WFC). CALIPSO is a joint satellite mission between NASA and the French Agency, CNES. These data consist 5 km aerosol layer data.
- API data.nasa.gov | Last Updated 2018-09-07T17:47:13.000Z
Future robotic missions to Venus require actuators for powering robotic arms, sampling systems, and gimbals for the positioning of cameras and antennas. There are many types of actuators (e.g. pneumatic, hydraulic); however electric actuators offer the greatest versatility for space missions. An electric actuator consists of an electric motor and a position sensor. The electric motor converts electrical energy (electricity) into mechanical output (shaft rotation). The position sensor, on the other hand, determines the angular position of the motor shaft, which then is processed by drive electronics to commutate and control the motor. Because of the extreme conditions on the Venus surface (92 bar pressure, 462 °C temperature, and supercritical CO2 atmosphere), conventional actuators will not be able to function properly, or at all. The main challenges pertain to changes in electrical properties like an increase in wire resistance (leading to greater losses), changes in magnetic properties like permeability and retentivity (leading to demagnetization of magnets), and changes in physical properties such as linear expansion, decrease in strength, increase in friction, and accelerated oxidation. Since 2007, Honeybee and NASA Jet Propulsion Laboratory (JPL) have been developing Venus actuator technologies. We developed a 48V Brushless DC motor (BLDC) and custom position sensor called the Pulsed Injection Position Sensor (PIPS) for motor commutation and feedback control. The motor and PIPS are at Technology Readiness Level (TRL) 5. The main objective of the proposed work is to mature the Venus actuator technology through an iterative process of Venus chamber testing of a TRL5 actuator, followed by re-design and fabrication of a TRL6 actuator and subsequent Venus chamber qualification testing of that actuator. The critical objectives to be met are as follows: 1. Design of a motor with 28V windings (28 V is a conventional spacecraft power bus), 2. Increase PIPS resolution from 12 to 48 counts/rev (this will make motor more efficient and allow actuator to be used for precision positioning systems – robotic arms and gimbals), 3. Establish reproducible procedures, standards, and guidelines for fabricating, assembly, test, and inspection of Venus actuators (currently actuators are hand crafted by selected engineers – this knowledge needs to be captured so that any skilled person will be able to fabricate Venus actuator whenever needed). Technical approach: This effort will be achieved in one year period to enable technology infusion into the New Frontiers (NF) Venus In Situ Explorer (VISE) mission. Specific tasks are: Step 1 (Months 1-3): we will characterize performance of the TRL5 actuator under Venus conditions in JPL’s Venus Materials Test Facility (VMTF) chamber. We will connect two existing TRL5 BLDC actuators: one will act as a brake to enable characterization of the second actuator. The actuator will be run until failure in order to assess failure condition. Step 2 (Months 4-9): we will incorporate lessons from Step 1 to design and fabricate three 28V actuators. We will develop procedures and standards for fabrication, inspection and testing. Step 3 (Months 10-12): we will perform the same tests as in Step 1 to characterize performance of the 28V actuators. At this point, it is assumed that we will be able to fabricate identical TRL 6 actuators by following manufacturing process developed in Step 2. Significance of the work to the solicitation: HOTTech supports development of electrical technologies (such as our proposed electric actuator) for the robotic exploration of Venus surfaces. Our electrical actuator will enable Venus missions in the Discovery, New Frontiers (Venus In Situ Explorer), and Flagship (Venus Mobile Explorer) class. Per HOTTech, our actuator also has terrestrial applications in the Geothermal, Oil and Gas, and Aeronautical industries.
- API data.nasa.gov | Last Updated 2018-07-20T06:54:04.000Z
To address NASA's need for applying advanced dynamical theories to space mission design and analysis, especially in the context of unstable orbital trajectories in the vicinity of small bodies and libration points, Physical Optics Corporation (POC) proposes to develop a novel advanced Orbit Dynamic Computation Approach for Space Mission Analysis in the Vicinity of Small Bodies and Libration Points (ODYBOLP), with corresponding computational algorithms and software based on advanced models of complicated celestial dynamical systems with libration points (LPs) and a pseudo-arclength continuation method for computation of periodic orbits in such systems. The ODYBOLP approach will enable users to analyze space missions using: (a) all possible stable and unstable periodic orbits near LPs of Sun-Earth and Earth-Moon systems, etc.; (b) all possible periodic orbits near asteroids and comets; (c) possible dynamic transitions between different orbits connecting them to each other to organize space for near-zero fuel cost passageways through such orbits. The ODYBOLP software will be integrated into standard NASA software (GMAT, JAT, etc.) for mission analysis and design. In Phase I, POC will demonstrate the feasibility of the ODYBOLP approach. In Phase II, POC will develop a fully functional software system and demonstrate its complete feasibility.