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- API data.nasa.gov | Last Updated 2018-07-19T09:28:07.000Z
- API data.nasa.gov | Last Updated 2018-07-19T09:56:51.000Z
The objective of the proposed research is to identify stable configurations of a rigid deployable aerodynamic decelerator for Mars atmospheric entry which provide increased landed mass capabilities for planetary exploration. Rigid deployable aerodynamic decelerators are a proposed means of augmenting the drag performance of atmospheric entry vehicles without adding significant mass to the system. The development of such a technology would allow for bridging of the gap between the robotic missions which we have successfully landed on Mars to date and the potential human class missions. This objective will be accomplished by performing a systems level architecture assessment to identify potential candidate configurations with the desired performance, dynamic scaling and estimating the expected stability behavior with quantitative analysis of those identified configurations, developing a matrix of sub-scale models and test conditions to fully characterize the dynamic response of each configuration, and executing stability tests through the use of a ballistic range test facility. The data acquired from the tests will provide crucial insight moving forward regarding the feasibility and relative stability of each of the configurations and guide further development of rigid deployable aerodynamic decelerators. This proposed research lies directly in line with the call laid out in the technology roadmap for new technologies which aid in aerobraking, aerocapture, and entry of spacecraft. The potential of rigid deployable decelerators and other similar technologies to enable ground breaking advancements in the capability of our nation to explore hinges on the continuous efforts of researches to further understand their behavior. Stability characterization is just one piece of that effort, but is a step that is necessary to increase the technology readiness of the next generation aerodynamic decelerators which will allow for humans to step foot on Mars.
- API data.nasa.gov | Last Updated 2018-07-19T04:48:48.000Z
This data set contains Raw data taken by the New Horizons Student Dust Counter instrument during the Jupiter encounter mission phase.
- API data.usaid.gov | Last Updated 2018-11-13T03:43:15.000Z
The Latin America Public Opinion Project (LAPOP) implemented this survey in Panama as part of its 2008 round of surveys. The 2008 survey was conducted by Vanderbilt University and Alianza Ciudadana Pro Justicia with field work done by Borge y Asociados.,
- API data.nasa.gov | Last Updated 2018-07-19T08:16:58.000Z
Flight Works is proposing to expand its technology in micropump-fed propulsion, including 1U CubeSat green propulsion, to the development and demonstration of a low cost, pump-fed, cooled, non-catalytic 1-5 N-class AF-M315E thruster for secondary payload propulsion. Typically, requirements imposed by the primary mission have led secondary payloads to have very limited propulsion capability. For earth orbiting spacecraft, the requirements to reenter within 25 years can be an issue. For lunar or interplanetary missions, lack of significant ΔV capability limits the science potential. For example, the system in the Mars Cube One 6U spacecraft is only capable of a few tens of m/s. Many such nanosats, including CubeSats slated to accompany the primary spacecraft towards Europa, could greatly benefit from real delta-V capability (> 1 km/s) while reducing risks to the primary payload. Flight Works is proposing to develop such capability and focus on the development of a pump-fed AF-M315E thruster. In the novel concept, propellant atomization is improved, conventional materials can be used for the injector and the valve, resulting in a more compact, lower cost, high performance thruster. Also, since the approach to ignition and combustion sustainment does not involve catalysts, the thruster life-limiting component is removed. This thruster is integrated into a micropump-fed system: there is no need for a separate pressurization, the propellant storage and feed system operates at low pressures, and lighter, conformal tanks can be used. This combination decreases system overall size and mass by 20-40% depending on the mission while reducing risks to the primary payload. More generally, the technology is applicable to any propulsion system, whether primary or for attitude control, where hydrazine is currently used, and is competitive with bipropellant systems for microsats due to the reduced system mass.
- API data.nasa.gov | Last Updated 2018-07-19T15:25:57.000Z
Integrated Ejector Pump Flow Control for Low-Pressure Turbine, Phase I
- API data.nasa.gov | Last Updated 2019-09-20T16:00:57.000Z
ML1RADT is the EOS Aura Microwave Limb Sounder (MLS) product containing the level 1 radiances from the filter banks for the THz radiometer. The data version is 3.3/3.4. Data coverage is from August 8, 2004 to June 30, 2015. Spatial coverage is near-global (-82 degrees to +82 degrees latitude), and files contain a full days worth of data (15 orbits). Users of the ML1RADT data product should read the 'A Short Guide to the Use and Interpretation of v3.3/v3.4 Level 1 Data' document for additional information. The data are stored in the version 5 Hierarchical Data Format, or HDF-5. Each file contains radiances and ancillary information written as HDF-5 dataset objects (n-dimensional arrays), along with file attributes and metadata.
OMPS-NPP L2 NM Nitrogen Dioxide (NO2) Total and Tropospheric Column swath orbital V2 (OMPS_NPP_NMNO2_L2) at GES DISCdata.nasa.gov | Last Updated 2019-09-20T16:03:32.000Z
The OMPS-NPP L2 NM Nitrogen Dioxide (NO2) Total and Tropospheric Column swath orbital collection 2 version 2.0 product contains the retrieved nitrogen dioxide (NO2) measured by the Ozone Mapping and Profiling Suite (OMPS) Nadir-Mapper (NM) sensor on the Suomi-NPP satellite. A direct vertical column fitting (DVCF) algorithm is used to retrieve the NO2 total column amount and a new spatial technique is applied to separate the stratospheric and tropospheric amounts. Each granule contains data from the daylight portion for a single orbit or about 50 minutes. Spatial coverage is global (-90 to 90 degrees latitude), and there are about 14 orbits per day each with a swath width of 2600 km. There are 35 pixels in the cross-track direction, with a pixel resolution of about 50 km x 50 km at nadir. The files are written using the Hierarchical Data Format Version 5 or HDF5.
- API finances.worldbank.org | Last Updated 2019-09-18T05:38:10.000Z
The International Development Association (IDA) credits are public and publicly guaranteed debt extended by the World Bank Group. IDA provides development credits, grants and guarantees to its recipient member countries to help meet their development needs. Credits from IDA are at concessional rates. Data are in U.S. dollars calculated using historical rates. This dataset contains the latest available snapshot of the IDA Statement of Credits and Grants. The World Bank complies with all sanctions applicable to World Bank transactions.
- API data.oregon.gov | Last Updated 2014-09-15T21:37:52.000Z
Contacts for South Coast ESD for Fiscal Year 2013