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).
Thermal Engineering of Mars Entry Non-Ablative Aeroshell Part 1
Sae Technical Papers
International Conference On Environmental Systems ; 1999
1999-07-12
Aufsatz (Konferenz)
Englisch
Thermal Engineering of Mars Entry Carbon/Carbon Non-Ablative Aeroshell - Part 3
SAE Technical Papers | 2001
|Thermal Engineering of Mars Entry Carbon/Carbon Non-Ablative Aeroshell - Part 2
SAE Technical Papers | 2000
|Design of a Mars entry 'Aeroshell'
Tema Archiv | 1974
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