Aerothermodynamic heating environment and thermal protection materials comparison for manned Mars-earth return vehiclesThe 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.
Document ID
19910034795
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Henline, William D. (NASA Ames Research Center Moffett Field, CA, United States)