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    1970 NASA/GSFC Battery Workshop

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    NASA/GSFC workshop on materials processing, chemical analysis, cell processing, and testing of batteries for aerospace application

    NASA GSFC Perspective on Heterogeneous Processing

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    This presentation provides an overview of NASA GSFC, our onboard processing applications, the applicability heterogeneous processing to these applications, and necessary developments to enable heterogeneous processing to be infused into our missions

    NASA/GSFC 1970 Battery Workshop, sessions 3 and 4 Transcript of proceedings

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    NASA/GSFC workshop on battery separators, seals, test techniques, and research and development of nickel cadmium and silver zinc batterie

    Spartan 201, NASA GSFC, High Altitude Observatory, Smithsonian Astrophysical Observatory pin

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    Spartan 201 logo, NASA GSFC, High Altitude Observatory, Smithsonian Astrophysical Observatory. (satellite released, then retrieved during the Space Shuttle Discovery mission STS-95 in 1998)Credit: John Glenn Archives, The Ohio State University

    Shoulder patch for the NASA GSFC Spartan 201 High Altitude Observatory satellite

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    Shoulder patch for the NASA GSFC Spartan 201 High Altitude Observatory satellite released then retrieved during the Space Shuttle Discovery mission STS-95 in 1998.Artifact Size: 4.5 inch diameter.Credit: John Glenn Archives, The Ohio State University

    The NASA GSFC MEMS Colloidal Thruster

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    A number of upcoming missions require different thrust levels on the same spacecraft. A highly scaleable and efficient propulsion system would allow substantial mass savings. One type of thruster that can throttle from high to low thrust while maintaining a high specific impulse is a Micro-Electro-Mechanical System (MEMS) colloidal thruster. The NASA GSFC MEMS colloidal thruster has solved the problem of electrical breakdown to permit the integration of the electrode on top of the emitter by a novel MEMS fabrication technique. Devices have been successfully fabricated and the insulation properties have been tested to show they can support the required electric field. A computational finite element model was created and used to verify the voltage required to successfully operate the thruster. An experimental setup has been prepared to test the devices with both optical and Time-Of-Flight diagnostics

    NASA GSFC CCMC Recent Model Validation Activities

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    The Community Coordinated Modeling Center (CCMC) holds the largest assembly of state-of-the-art physics-based space weather models developed by the international space physics community. In addition to providing the community easy access to these modern space research models to support science research, its another primary goal is to test and validate models for transition from research to operations. In this presentation, we provide an overview of the space science models available at CCMC. Then we will focus on the community-wide model validation efforts led by CCMC in all domains of the Sun-Earth system and the internal validation efforts at CCMC to support space weather servicesjoperations provided its sibling organization - NASA GSFC Space Weather Center (http://swc.gsfc.nasa.gov). We will also discuss our efforts in operational model validation in collaboration with NOAA/SWPC

    Data for: An experimental sky-image-derived cloud validation dataset for Sentinel-2 and Landsat 8 satellites over NASA GSFC

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    Reference cloud data over NASA GSFC for validating cloud masking algorithm for moderate spatial resolution satellite data, namely Sentinel-2 and Landsat 8

    Novel applications of the NASA/GSFC Viterbi decoder hardware simulator

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    The NASA/GSFC developed an all digital, real time, programmable Viterbi decoder simulator operating at rates up to 6 Msps. With this simulator, the bit error rate (BER) performance of convolutionally encoded/Viterbi decoded Shuttle-TDRSS return link channels under pulsed radio frequency interference (RFI) conditions has been predicted. The principles of the simulator are described with special emphasis on the channel simulator and the essential interaction between CLASS software and the simulator. The sensitivity of coded BER as function of several illustrative RFI parameters is discussed for two typical Shuttle-TDRSS return link configurations
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