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Thermal Engineering of Mars Entry Carbon/Carbon Non-Ablative Aeroshell - Part 2
ISSN: 0148-7191, e-ISSN: 2688-3627
Published July 10, 2000 by SAE International in United States
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Candidate Aeroshell Test models composed of a quasi-isotropic Carbon/Carbon(C/C) front face sheet (F/S), eggcrate core, C/C back F/S, Carbon Aerogel insulation, C/C radiation shield and the C/C close-out were constructed based on the analytical temperature predictions presented in Part One of this work. The analytical results obtained for a simulated Mars entry of a 2.9 meter diameter cone shaped Carbon-Carbon Aeroshell demonstrated the feasibility of the design. These results showed that the maximum temperature the front F/S reached during the decent was 1752 °C with the resulting rear temperature reaching 326 °C in the thermal model.
Part Two of this work documents the thermal modeling and correlation for the Mars Aeroshell test sample and fixture. A finite difference, SINDA/G, thermal math model of the test fixture and sample was generated and correlated to data from an arc jet test conducted at the NASA Ames Research Center's interactive heating facility. A transient thermal analysis was executed for 175 seconds to simulate the heating and part of the cooldown of the sample. Heat transfer coefficients and convective couplings were varied to achieve a good correlation. Results showed that after 45 seconds of heating, the predicted arc jet temperatures versus test data for the front face-sheet were 1396°C versus 1412°C, the predicted temperatures versus test data for the copper coated face-sheet were 1275°C versus 1302°C and the predicted temperatures versus test data for Aerogel core rear surface were 41°C versus 75°C.
CitationHickey, G., Lih, S., Wise, R., McElroy, P. et al., "Thermal Engineering of Mars Entry Carbon/Carbon Non-Ablative Aeroshell - Part 2," SAE Technical Paper 2000-01-2404, 2000, https://doi.org/10.4271/2000-01-2404.
- Wise, B. McElroy, P. Hickey, G. and Lih, S. “Thermal Engineering of Mars Entry Non-Ablative Aeroshell, Part 1,” 29th International Conf. On Enviroment Systems, July 12-15, 1999.
- Huy Tran et al, “Mars/Pathfinder Back Interface Plate Heat Shield and Designs Verification Tests in the ARC 20 MW Panel Test Facility.,” Report for the Mars/Pathfinder Project office of the Jet Propulsion Laboratory, 1995.
- Pekala, R.W. et al, “Carbon Aerogels and Xerogels”, in Novel Forms of Carbon, Cox, D. Pouch, J. Renschler, C.I. ed: Materials esearch Society Symposium Proceedings (1992).
- Bock V., et al, “Thermal Properties of Carbon Aerogels”, J. Non-Cryst. Solids, 185, (1995) p. 233-239.