MUSES-Cカプセル全機周り輻射加熱環境の工学的評価

抄録

Forebody and aftbody radiative heating rates of the MUSES-C asteroid sample return capsule have been assessed along the reentry trajectory from an engineering standpoint. Nonequilibrium hypersonic flows around the capsule with ablation of the thermal protection system involved were determined by CFD calculations, while the radiative heat transfer was computed by the radiation code SPRADIAN in a non-coupled manner with the flow analysis. In order to take into account much uncertainty in the thermal relaxation, chemical reaction, and ablation models used in the flow analysis, parametric studies were performed by changing these models to obtain the conservative estimation of the radiative environments. The radiative heat flux was found to be considerably affected by the ablation model, especially in the aftbody region of the capsule.