Publication Date:
2019-06-28
Description:
The aerothermodynamic environment during the earth return portion of a specific manned Mars mission is studied. Particular attention is given to the earlier smaller crew return capsule and its thermal protection system requirements. Data are presented on the stagnation region of a generic Mars return capsule. Insulation material thicknesses required to maintain allowable structural temperatures throughout a prolonged heat soak period are estimated.
Keywords:
SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Type:
AIAA PAPER 91-0697
Format:
text