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Thermal Engineering of Mars Entry Carbon/Carbon Non-Ablative Aeroshell - Part 3
ISSN: 0148-7191, e-ISSN: 2688-3627
Published July 09, 2001 by SAE International in United States
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This is Part 3 of a development program to evaluate candidate nonablative aeroshell designs. The primary goal of this C/C aeroshell development task was to demonstrate the feasibility and performance of a lightweight C/C non-ablative aeroshell design that integrates advanced C/C materials and structural configurations. The thermal performance was evaluated by Arc Jet testing at NASA Ames of representative structural models. In this phase of the program, new carbon-carbon materials and structural core designs were evaluated, as well as an alternative aerogel material. The test models were composed of a quasi-isotropic Carbon/Carbon(C/C) front face sheet (F/S), eggcrate or honeycomb core, C/C back F/S, Carbon and resorcinol-formaldehyde aerogel insulation. Part One of this work  demonstrated the feasibility through arc-jet testing and Part Two  included analytical modeling of the test geometry to validate the design. In this work alternative carbon-carbon material, core construction and oxidation resistant coatings were used as the design variables. Testing was conducted on six test models with the arc jet temperature at nominally 1500 °C. Three design configurations successfully maintained the rear surface below 150°C during 45 seconds of exposure.
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CitationHickey, G., Lih, S., and Shih, W., "Thermal Engineering of Mars Entry Carbon/Carbon Non-Ablative Aeroshell - Part 3," SAE Technical Paper 2001-01-2279, 2001, https://doi.org/10.4271/2001-01-2279.
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