Abstract

Correlations for calculation of heat loads during a return of spacecraft at the second cosmic velocity are given. Analysis of the heat transfer for a model descent trajectory has been carried out. The convective and radiative heat fluxes, the relative heat transfer coefficient, and the radiative-equilibrium surface temperature have been calculated. The results obtained are a basis for design and optimization of the heat shield of spacecraft.

中文翻译：

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航天器超轨道进入地球大气层分析中的热负荷计算

摘要

给出了航天器以第二宇宙速度返回期间热负荷计算的相关性。对模型下降轨迹的传热进行了分析。计算了对流和辐射热通量、相对传热系数和辐射平衡表面温度。所得结果为航天器隔热罩的设计和优化提供依据。