Forebody TPS sizing with radiation and ablation for the Stardust Sample Return Capsule

Abstract

The development of a new high-fidelity methodology for predicting entry flows with coupled radiation and ablation is described. The prediction methodology consists of an axisymmetric, nonequilibrium, Navier-Stokes flow solver loosely coupled to a radiation prediction code and a material thermal response code. The methodology is used to simulate the 12.6 km/s Earth atmospheric entry of the Stardust sample return capsule at seven trajectory points using ablating and nonablating boundary conditions. These flow simulations are used to size and design the Stardust forebody heatshield and develop arc-jet test conditions and models. The paper describes details of the methodology, results from the flow simulations, and, various heatshield design issues.