Validation Testing of a New Dual Heat Pulse, Dual Layer Thermal Protection System Applicable to Human Mars Entry, Descent and Landing

In NASA’s quest to find a system capable of delivering 40 metric ton payloads to the surface of Mars, one proposed mission scenario employs a 10 x 29 meter mid lift-over-drag (L/D) vehicle with a dual heat pulse capable thermal protection system (TPS) that achieves orbit via aerocapture, cools down there, and then enters, descends and lands. This paper discusses the simulated dual heat pulse thermal testing conducted in the Ames arcjet complex of a dual layer, phenolic impregnated carbon ablator (PICA) atop a LI-900 (Shuttle insulating tile) TPS attached with large honeycomb (~ 5 cm), proposed for this mission scenario. Test results and recommendations for future work on the maturation of the dual heat pulse TPS technology are provided.