Aeroheating and Structural Coupled Analysis in Thermal Protection System for Reusable Launch Vehicle

摘要

The thermal protection system design for reusable launch vehicle (RLV) associated is significant and complex with vehicle trajectory, aeroheating, structural temperature and response. To improve the calculation accuracy of TPS performance, this paper introduced an aeroheating and structural coupled method to analyze the non-ablative composite rigid external TPS for RLV at the project earlier stage, and the finite element method decoupling was employed. The research indicated that, during the RLV descent process, the hot-wall heat flux actual action on the TPS is less than the initial calculation value obtained. And the aeroheating and structural coupling problem must be considered for TPS design. And the shingle structure response of RLV TPS is discussed.