Thermal Engineering of Mars Entry Non-Ablative Aeroshell Part 1

Paper #:
  • 1999-01-2198

Published:
  • 1999-07-12
Citation:
Wise, R., McElroy, P., Hickey, G., and Lih, S., "Thermal Engineering of Mars Entry Non-Ablative Aeroshell Part 1," SAE Technical Paper 1999-01-2198, 1999, https://doi.org/10.4271/1999-01-2198.
Pages:
8
Abstract:
A transient thermal analysis of a Carbon/Carbon (C/C) Mars Entry Non-Ablative Aeroshell Assembly was performed to determine the maximum temperatures it would reach during a Mars entry. The purpose of this thermal analyses was to (1) determine the maximum temperatures of the 5 layers and the close-out which make up the aerothermal shield and (2) to transmit these temperatures from SINDA/G finite difference format to finite element format in COSMOS/M structures/dynamic models using Technical Alliance Group (TAG) developed SINDA/ G temperature translator software (STT).
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