A Thermochemical Nonequilibrium Flow around a Super Orbital Reentry Capsule with Ablation

The Institute of Space and Astronautical Science report. S.P Pub Date : 2001-08-30 DOI:10.1063/1.1407630

Ryoji Doihara, M. Nishida, 良次土井原, 迪雄西田

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引用次数: 4

Abstract

The aerodynamic heating to the super orbital reentry capsule of MUSES-C is numerically studied by using thermochemical nonequilibrium full Viscous-Shock-Layer (VSL) equations. An 11 airspecies model is used for non-ablating boundary conditions. Six carbonous species are added for ablating boundary conditions. With a three-temperature model, thermal nonequilibrium effect is taken into account. The convective and radiative heat fluxes to the wall are examined for both fully catalytic wall (FCW) condition and non-catalytic wall (NCW) condition at various altitudes for the capsule reentry trajectory path. The maximum heat fluxes estimated for FCW and NCW are 8.7 MW/m2 at the altitude of 56 km and 6.1 MW/m2 at the altitude of 56 km, respectively. The radiative heat flux at the stagnation point of the capsule has also been calculated and the maximum radiative heat flux of 0.9 MW/m2 has been found at the altitude of 62 km. The intensity of UV and VUV spectra are extremely intense, so that such UV and VUV spectra mainly contribute to the radiative heat flux.

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热化学非平衡流绕超轨道返回舱消融

采用热化学非平衡全粘冲击层(VSL)方程，对缪斯- c超轨道返回舱的气动加热进行了数值研究。非烧蚀边界条件采用11气相模型。在烧蚀边界条件下加入了六种碳化物。采用三温度模型，考虑了热非平衡效应。在不同高度的返回舱轨道路径上，对全催化壁(FCW)和非催化壁(NCW)条件下的壁面对流热通量和辐射热通量进行了研究。在56 km高度，FCW和NCW的最大热通量分别为8.7 MW/m2和6.1 MW/m2。计算了太空舱驻点处的辐射热通量，在海拔62 km处最大辐射热通量为0.9 MW/m2。紫外和甚紫外光谱的强度非常强，因此这类紫外和甚紫外光谱对辐射热通量的贡献是主要的。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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The Institute of Space and Astronautical Science report. S.P

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