HIGH-FIDELITY THERMAL PROTECTION SYSTEM SIZING OF REUSABLE LAUNCH VEHICLE

A coupled computational fluid dynamics/in-depth conduction analysis pr ocedure to perform high-fidelity thermal protection system sizing is p resented. The thermal environment on the vehicle surface, including ra diative equilibrium wall temperature and surface catalycity, is comput ed using a real-gas, Navier-Stokes flow solver, Based on the computed surface temperatures, a thermal protection system material mapping is performed, Material thickness and overall thermal protection system ma ss are obtained using an in-depth conduction code, This procedure is u sed to size the thermal protection system on a lifting-body, single-st age-to-orbit vehicle.