Material Response Analysis of a Titan Entry Heatshield

Palmer, Grant ; Schulz, Joseph ; Stern, Eric

关键词: ABLATIVE MATERIALS;    THERMAL PROTECTION;    ATMOSPHERIC ENTRY;    HEAT SHIELDING;    TITAN;    COMPUTERIZED SIMULATION;    TIME RESPONSE;   

RP-ID  :  ARC-E-DAA-TN61238

学科分类：力学，机械学

美国|英语

来源: NASA Technical Reports Server

【 摘 要 】

Accurate calculation of thermal protection material response is critical to the vehicle design for missions to the Saturn moon Titan. In this study, Icarus, a three-dimensional, unstructured, finite-volume material response solver under active development at NASA Ames Research Center, is used to compute the in-depth material response of the Huygens spacecraft along its November 11 entry trajectory. The heatshield analyzed in this study consists of a five-layer stack-up of Phenolic Impregnated Carbon Ablator (PICA), aluminum honeycomb, adhesive, and face sheetmaterials. During planetary entry, the PICA outer layer is expected to undergo pyrolysis. A surface energy balance boundary condition that captures both time- and spatial-variance of surface properties during entry is used in the simulation.