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- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:09:52.000Z
With retirement of the space shuttle program, microgravity researchers can no longer count on bringing experiment samples back to earth for post-flight analysis. Locker-sized processing facilities, which were typically transported up to and down from the International Space Station during the shuttle era, quite simply consume too much volume, mass, and power to be accommodated as part of both the upmass and downmass on current space transportation vehicles. As a result, more analysis must be accomplished on ISS, which makes on-orbit analytical tools critical to the continued success of microgravity research. The Analytical Cassette transfer Tool (ACT) is a low-cost, disposable device that efficiently transfers experiment samples in a safe and contained manner from unique experiment specific spaceflight hardware to on-orbit analytical tools that enable real-time analysis in microgravity. ACT interfaces with several flight qualified processing payloads to extract experiment samples via a needle-less septum and then allows transfer of those samples into a number of different on-orbit analytical devices, including such instrumentation as the Light Microscopy Module, the Microfluidic Flow Cytometer, a Spectrophotometer, and/or a Mass Spectrometer. Applications in life and environmental sciences include sampling liquid cultures/suspensions or sampling spacecraft water for quality evaluation. ACT functions within or outside of on-orbit gloveboxes to safely transfer any liquid material from one container fitted with the ACT mating receptacle to another container fitted with a receptacle. Its safe, simple, effective, and with its economical advantage, ACT is destined to become the new standard fluid transfer device for the ISS and future space research venues. For the Phase II project, Techshot will develop a flight version of the ACT and subject it to the major spaceflight integration tests.
- API data.nasa.gov | Last Updated 2020-01-29T01:43:17.000Z
Aerobot vehicles for missions on Titan require envelope materials that are strong, light and durable. Unlike terrestrial balloon materials, these must be able to withstand flexing at temperatures of 90K without developing pinhole leaks. To meet this requirement, it is proposed to use Lamart?s experience in lightweight laminated sailcloth and ultra light film lamination to create a material for this application. This will be a laminated combination of multiple thin films and fabric. Test capabilities will be created and correlated to those already done at NASA-JPL. Literature search and sample testing will determine the appropriate film, adhesive, fibers, and fabric weave. Further testing will determine the minimum manageable film thickness and the minimum amount of adhesive needed to meet the mission requirements. Laminations of multiple layers of thin film will be tested to determine the benefit of this schedule compared to single layer equivalent films. Small quantities of the most promising film and fabric laminate designs will be produced on a narrow width laminator that duplicates the process used to produce full sized products and tested for flex durability.
MODIS/Aqua Geolocation Fields 1km 5-Min 1A Narrow Swath Subset along CloudSat V002 (MAC03S0) at GES DISCdata.nasa.gov | Last Updated 2019-12-13T00:23:00.000Z
This is the narrow-swath MODIS/Aqua subset along CloudSat field of view track. The goal of the narrow-swath subset is to select and return MODIS data that are within +-5 km across the CloudSat track. I.e. the resultant MODIS subset swath is about 10 km cross-track. Thus, MAC03S0 cross-track width is 11 pixels. Along-track, all MODIS pixels from the original product are preserved. In the standard product, geolocation fields are calculated for each 1 km MODIS Instantaneous Field of Views (IFOV) for all orbits daily. The locations and ancillary information corresponds to the intersection of the centers of each IFOV from 10 detectors in an ideal 1 km band on the Earth's surface. A digital terrain model is used to model the Earth's surface. The main inputs are the spacecraft attitude and orbit, the instrument telemetry and the digital elevation model. The geolocation fields include geodetic Latitude, Longitude, surface height above geoid, solar zenith and azimuth angles, satellite zenith and azimuth angles, and a land/sea mask for each 1 km sample. Additional information is included in the header to enable the calculation of the approximate location of the center of the detectors of any of the 36 MODIS bands. This product is used as input by a large number of subsequent MODIS products, particularly the products produced by the Land team. (The shortname for this product is MAC03S0).
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-19T08:34:46.000Z
The reprocessed Aura OMI Version 003 Level 2 Cloud Data Product OMCLDRR is made available (in April 2012) to the public from the NASA Goddard Earth Sciences Data and Information Services Center (GES DISC). http://disc.gsfc.nasa.gov/Aura/OMI/omcldrr_v003.shtml ) Aura OMI provides two Level-2 Cloud products (OMCLDRR and OMCLDO2) at pixel resolution (13 x 24 km at nadir) that are based on two different algorithms, the Rotational Raman Scattering method and the O2-O2 absorption method. This level-2 global cloud product (OMCLDRR) provides effective cloud pressure and effective cloud fraction that is based on the least square fitting of the Ring spectrum (filling-in of Fraunhofer lines in the range 392 to 398 nm due to rotational Raman scattering). This product also contains many ancillary and derived parameters, terrain and geolocation information, solar and satellite viewing angles, and quality flags. The shortname for this Level-2 OMI Cloud Pressure and Fraction product is OMCLDRR and the algorithm lead for this product is NASA OMI scientist Dr. Joanna Joinner. OMCLDRR files are stored in EOS Hierarchical Data Format (HDF-EOS5). Each file contains data from the day lit portion of an orbit (53 minutes). There are approximately 14 orbits per day. The maximum file size for the OMCLDRR data product is about 9 Mbytes. A list of tools for browsing and extracting data from these files can be found at: http://disc.gsfc.nasa.gov/Aura/tools.shtml . A short OMCLDRR Readme Document that includes brief algorithm description and data quality is also provided by the OMCLDRR Algorithm lead. The Ozone Monitoring Instrument (OMI) was launched aboard the EOS-Aura satellite on July 15, 2004(1:38 pm equator crossing time, ascending mode). OMI with its 2600 km viewing swath width provides almost daily global coverage. OMI is a contribution of the Netherlands Agency for Aerospace Programs (NIVR)in collaboration with Finish Meterological Institute (FMI), to the US EOS-Aura Mission. OMI is designed to monitor stratospheric and tropospheric ozone, clouds, aerosols and smoke from biomass burning, SO2 from volcanic eruptions, and key tropospheric pollutants (HCHO, NO2) and ozone depleting gases (OClO and BrO). OMI sensor counts, calibrated and geolocated radiances, and all derived geophysical atmospheric products are archived at the NASA GES DISC. For more information on Ozone Monitoring Instrument and atmospheric data products, please visit the OMI-Aura sites: http://aura.gsfc.nasa.gov/instruments/omi/ http://www.knmi.nl/omi/research/documents/ . Data Category Parameters: The OMCLDRR data file contains one swath which consists of two groups: Data fields: Two Effective Cloud Fraction and two Cloud Top Pressures that are based on two different clear and cloudy scene reflectivity criteria, Chlorophyll Amount, Effective Reflectivity (394.1 micron), UV Aerosol Index (based on 360 and 388 nm), and many Auxiliary Algorithm Parameter and Quality Flags. Geolocation Fields: Latitude, Longitude, Time, Solar Zenith Angle, Viewing Zenith Angle, Relative Azimuth Angle, Terrain Height, and Ground Pixel Quality Flags. OMI Atmospheric data and documents are available from the following sites: http://disc.gsfc.nasa.gov/Aura/OMI/ http://mirador.gsfc.nasa.gov/
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:24:15.000Z
The proposed innovation is: A data and information integration (DI2) system built from the methods and tools used to create Wiki websites. Wiki (Hawaiian for "quick") is software that allows users to create and edit Web page content using any Web browser. The significance of the innovation is that a Wiki-based DI2 system will: (1) Produce a collaborative, interactive website designed for the unique needs of government and commercial spacecraft projects for capturing, disseminating, managing and linking data resources across multiple projects and among distributed teams, (2) Provide "out of the box" advanced DI2 capabilities needed by project management and technical personnel from day one, (3) Provide a low cost DI2 solution for small companies and teams needing alternatives to expensive, complicated and inflexible project management tools, (4) Be easy to install, use and maintain without requiring programming or webmaster skills. The proposed innovation merges the Wiki philosophy of fast, easy and rewarding online content creation with standard project management functions and capabilities for data and information integration within secure, user-authenticated environments. This facilitates critical elements of communication, interaction and data capture/synthesis that are often missing or underdeveloped in many traditional project management efforts. Phase 1 TRL will be 6.
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:43:05.000Z
<p> The TOAST instrument is an open-loop processor of GPS navigation signals. The electronics fits on a single 10 cm square card with RF components and digital components on opposite sides. A dime-sized programmable chip (FPGA) acts as a signal processor for the GPS signals of up to 10 satellites. This FPGA is under the control of a very low-power Linux CPU which handles all of the tracking models for very weak GPS signals transecting the atmosphere. Unlike typical GPS receivers, TOAST tracks without tight phase-locked loop tracking of the received carrier phase. For any given GPS satellite to be observed, TOAST generates a precise 3rd order range and phase model and only updates the FPGA every 1 - 10 seconds. This allows the processor to be loosely coupled with the signal processing to the point where, given sufficient ground to space bandwidth, TOAST can be controlled by a ground-based CPU. However, in this implementation, a Linux CPU will accompany the RF and FPGA logic to provide real-time data.</p>
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:42:40.000Z
<p>Key NCPS project objectives are to conduct preliminary design, fabrication, and test of representative fuel samples and partial length fuel elements for the two primary NTP fuel forms identified by NASA and DOE &ndash; NERVA carbide &ldquo;graphite composite&rdquo; and ceramic-metallic (Cermet) fuels; further define NTP system concept designs that can meet the mission requirements of Mars DRA 5.0 and serve as a basis for the above two primary fuel elements/types for both a smaller demonstration sized engine and the larger Mars Crewed Vehicle sized engine (25 klbf); and using the results of the above fuel development and testing as well as other heritage NTP data, develop fuel downselection criteria and recommendations to support a fuel&nbsp;type downselection in early FY 2015.</p>
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:24:24.000Z
We propose to develop and commercialize a new class of extreme ultraviolet (EUV) multilayer coatings containing the rare-earth element gadolinium (Gd), designed as efficient narrow-band reflective mirror coatings operating near normal incidence in the 60-65 nm wavelength range. This long-wavelength region of the EUV includes the important solar emission lines O V near l=63.0 nm and Mg X near l=61.0 nm, formed at intermediate temperatures in the solar atmosphere. While narrow-band EUV multilayer coatings are by now widely used in NASA missions for high-resolution solar imaging at wavelengths shorter than 35 nm, the observations made at those wavelengths probe coronal and transition region lines formed at either low (e.g., He II at l=30.4 nm) or high (e.g., numerous Fe lines) temperatures. In contrast, the 60?65 nm wavelength region provides a unique spectral window in which to observe intermediate-temperature solar emission lines. However, efficient narrow-band multilayer coatings operating in this range have been unavailable until now. The successful development of efficient, stable Gd-based multilayers as we propose, based on preliminary experimental results, especially those obtained during our Phase I effort, will therefore enable the construction of new high-resolution solar telescopes tuned to O V or Mg X that will complement existing multilayer telescopes tuned to shorter EUV wavelengths, thereby providing more complete temperature coverage, and leading to better understanding of the solar atmosphere, its variability, and its crucial role in driving space weather. EUV imaging instruments incorporating the multilayer technology we propose to develop may be included in future missions such as RAM, Solar Probe, and Solar Orbiter, as well as future GOES satellites and new Explorer-class missions.
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:18:09.000Z
Robotic planetary exploration missions will need to perform in-situ analysis of rock and/or regolith samples or returning samples back to earth. Obtaining and delivering a sample can be a complex engineering problem, especially if it's done autonomously thousands of miles away. To accommodate future missions, these subsurface access and sample handling technologies must be developed to meet a broad range of potential requirements, including a variety of rock or subsurface materials, rigorous sample preservation requirements, and the general problem of autonomous operation in the presence of dust and with limited resources. The one-to-three meter range has been identified as a critical regime for planetary exploration and while there has been some technology development in this regime, there is currently no proven flight-like approach to robotically achieving this depth through layers of challenging material from realistic roving or landed platforms. The Phase 1 research has resulted in proving the benefits of rotary-percussive drilling system as it pertains to breaking of formation and cuttings transport. The primary objective of the proposed effort is to develop, via testing in a simulated Mars environment, a breadboard one-meter sampling drilling system for acquiring a small volume of drilled cuttings and a core (if necessary) from a target depth on Mars. This project would build on the existing knowledge base of Mars drilling, and its particular strength lies with its capability of performing drilling tests under simulated Martian conditions of temperature and pressure and CO2 atmosphere. This is a component technology effort that includes the development of a rotary percussive drill head and a sampling lead drill string. Honeybee Robotics will leverage drill head development by utilizing voice coil percussive actuator technology developed by the Jet Propulsion Laboratory (JPL) for the Mars Science Laboratory Powder Drill.
- API nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:14:47.000Z
This Phase I Small Business Innovative Research project proposes to develop a multiscale computational methodology capable of accurate prediction of the properties and performance of insulating ablative materials that are used to protect the re-entry of vehicles from excessive thermal loads. In particular, this effort will focus on multi-million atom, reactive molecular dynamics (MD) simulations of pyrolysis of phenolic resins enhanced with carbon nanotubes (CNT). The results will reveal the role of CNT interface on the reaction and the thermo-mechanical properties. The derived interfacial strength characteristics will then be incorporated into continuum-level simulations. The outcome of Phase I will provide a benchmark to perform MD simulations on pyrolysis of resin composites and methodology development to link atomistic-level with continuum-level simulations. Phase II will involve MD simulations on multi-walled, functionalized CNTs in cross-linked resin, optimization of the multi-scale modeling methodology and experimental validation. The outcome of the multiscale computational program will involve a detailed parametric study to find optimal parameters at multiple scales including: nanofiller diameter size, volume fraction and functionalization of nanotubes and ?]m-sized carbon fibers. These parameters will be optimized to best meet Orion vehicle!&s TPS challenges. The team involves engineers from ACT and researchers from Rensselaer Polytechnic Institute.