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.
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Reviznikov, D.L., Nenarokomov, A.V., Konstantinov, M.S. et al. Calculation of Heat Loads in Analysis of Superorbital Entry of Spacecraft into Atmosphere of the Earth. J. Engin. Thermophys. 32, 467–481 (2023). https://doi.org/10.1134/S1810232823030050
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DOI: https://doi.org/10.1134/S1810232823030050