Abstract
Arc plasma tests of a range of ablative materials considered candidates for the thermal protection system for the Mars Science Laboratory are described. The objective of these tests was to identify ablative thermal protection materials that offer weight, performance, cost, or other advantages relative to SLA-561V. Several low-density silicones with a mixture of low-density fillers and polymer-impregnated ceramics were tested in the Ames Interaction Heating Facility at conditions representative of nominal stagnation point and worst-case conical heating on the Mars Smart Lander forebody. A wide variety of low-density ablatives and impregnated flexible materials were tested in the Ames Panel Test Facility at nominal and worst-case heating for the Mars Smart Lander backshell. The results of these tests have identified several attractive materials worthy of further investigation.
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