Material Response Analysis of a Titan Entry Heatshield

[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.

[发布日期] 2018-09-17

[学科分类] 力学，机械学

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