Qualitative evaluation indicates that low-density charring ablators are most likely to meet all requirements; low density-foamed-silicone (LDFS) and epoxy-modified-silicone (ESM) were subjected to various tests, designed to simulate ground, flight, and entry environmental conditions expected to be encountered; LDFS survived thermal cycling to temperatures as low as -300 F; ESM survived to -275 F; change of base elastomer to phenyl-methyl silicone should give even better low-temperature capability; both heat-protection materials are capable of meeting all mission requirements. (15093)
Thermal protection systems for mars-entry vehicle
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 5 , n 11
1968
7 pages
Aufsatz (Zeitschrift)
Englisch
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Thermal protection systems for a Mars-entry vehicle.
AIAA | 1968
|Thermal protection systems for a Mars-entry vehicle
AIAA | 1968
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