Abstract
Gas particles produced by dissociation and ionization in the high temperature shock, have strong radiative heating on surface when spacecraft re-enter at high Mach number. Aiming at the radiation heating problem of the hypersonic reentry spacecraft, the finite volume method was used to calculate the radiation transfer equation, in which a ghost cell method is employed to processed the boundary condition. Using this method to calculate the typical cylindrical furnace. The results showed that the accuracy of the current methods was high, the grid convergence was good, and it satisfied the physical fact. The method was then used to calculate the radiative heating on the Fire II surface based on the calculation data of the chemical non-equilibrium flow field. The radiation heat flux on the surface of the spacecraft is calculated. The results were in good agreement with other researcher’s calculation value.
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Hao, J., Zhang, L., Lyu, J., Ai, B. (2019). Radiation Heating Analysis of Hypersonic Re-entry Spacecraft. In: Zhang, X. (eds) The Proceedings of the 2018 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2018). APISAT 2018. Lecture Notes in Electrical Engineering, vol 459. Springer, Singapore. https://doi.org/10.1007/978-981-13-3305-7_20
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DOI: https://doi.org/10.1007/978-981-13-3305-7_20
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