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• W2603407735 abstract "ABSTRACTCarbon-carbon composite materials offer greater thermal efficiency, stiffness to weight ratio, tailorability, and dimensionalstability than aluminum. These lightweight thermal materials could/significantly reduce the overall costs associated withsatellite thermal control and weight. However, the high cost and long lead-time for carbon-carbon manufacture have limitedtheir widespread usage. Consequently, an informal partnership between government and industrial personnel called theCarbon-Carbon Spacecraft Radiator Partnership (CSRP) was created to foster carbon-carbon composite use for thermally andstructurally demanding space radiator applications. The first CSRP flight opportunity is on the New Millennium Program(NMP) Earth Orbiter-1 (EO-I) spacecraft, scheduled for launch in late 1999. For EO-I, the CSRP designed and fabricated aCarbon-Carbon Radiator (CCR) with carbon-carbon facesheets and aluminum honeycomb core, which will also serve as astructural shear panel.While carbon-carbon is an ideal thermal candidate for spacecraft radiators, in practice there are technical challenges that maycompromise performance. In this work, the thermal and mechanical performance of the EO-1 CCR is assessed by analysisand testing. Both thermal and mechanical analyses were conducted to predict the radiator response to anticipated launch andon-orbit loads. The thermal model developed was based on thermal balance test conditions. The thermal analysis wasperformed using SINDA version 4.0. Structural finite element modeling and analysis were performed using SDRC/I-DEASand UAI/NASTRAN, respectively. In addition, the CCR was subjected to flight qualification thermal/vacuum and vibrationtests. The panel meets or exceeds the requirements for space flight and demonstrates promise for future satellite missions.Keywords: Spacecraft Radiator, Carbon-Carbon Composite, Thermal/Vacuum Testing, Vibration Testing, ThermalModeling, Structural Modeling, EO-1, and Performance1. INTRODUCTIONThe New Millennium Program (NMP) Earth Orbiter-1 (EO-1) is the spacecraft platform for the Advanced Land Imager(ALI) instrument and will fly in a sun-synchronous orbit 705 kilometers above the Earth. The launch date is scheduled forlate 1999 aboard a Delta 7320 Expendable Launch Vehicle (ELV). Though the ALI is the primary instrument aboard the EO-l, the spacecraft will also be used to test a number of new technologies, one of which is the Carbon-Carbon Radiator (CCR)shown in Figure 1. The CCR is a sandwich composite panel with facesheets made of carbon fibers in a carbon matrix. Inflight, the panel will be attached to the spacecraft bus, and will support two electronics boxes with a total weight of 58 lb andtotal heat output of 60W. The panel was built by the Carbon-Carbon Spacecraft Radiator Partnership (CSRP) and delivered toNASA/Goddard Space Flight Center (GSFC) for environmental testing. The spacecraft integrator, Swales Aerospace Inc.(SAI) l, specified the thermal and mechanical flight requirements for the CCR. During the testing at GSFC, the integratedhoneycomb panel was subjected to thermal/vacuum and vibration tests. In support of these tests computer models weredeveloped and correlated as needed to understand the response of the CCR to the respective environments. In this paper, theresults of GSFC environmental testing and modeling are presented and used to assess the performance of the CCR design.The CSRP is an informal partnership established to promote the use of carbon-carbon on spacecraft. CSRP membershipincludes research engineers and scientists at government and private facilities. The government agencies include the AirForce Research Laboratory's Materials and Manufacturing Directorate and Space Vehicles Directorate, the Naval SurfaceWarfare Center's Carderock division, NASA Langley Research Center (LaRC), NASA Goddard Space Flight Center(GSFC). Private industry members include TRW, Lockheed Martin Astronautics (LMA), Lockheed Martin Missiles & Space(LMMS), Lockheed Martin Vought Systems (LMVS), Amoco Polymers, Materials Research & Design (MR&D), and BFGoodrich. The CSRP designed and fabricated a radiator panel that could significantly reduce spacecraft weight and thermalcontrol costs and possibly extend their operational lives. The panel was built to demonstrate that carbon-carbon can be a costefficient choice for radiators that also function as part of the primary spacecraft structure. In this case the radiator is also ashear panel. The panel will be instrumented for on-orbit data. [f successful, the new design may dramatically change howradiators are constructed for future spacecraft and could lead to other important cost-reduction applications in space andprivate industry. Flight and spare panels were built and both were subjected to flight qualification testing. This paper focuseson the results of the actual flight panel." @default.
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• W2603407735 date "1999-01-01" @default.
• W2603407735 modified "2023-09-24" @default.
• W2603407735 title "Thermal and Mechanical Spacecraft Radiator" @default.
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