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Date of Publication:2022-10-09

Journal:兵工学报

Issue:10

Page Number:1949-1954

ISSN No.:1000-1093

Abstract:It is inevitable to evaluate the aerodynamic heat and the ablation of thermal protection material for designing a hypersonic aircraft. A coupling method is presented for the calculation of aerodynamic heat, material ablation and transient temperature distribution. The method and program are validated by experimental data. The results indicate that the method has higher precision and efficiency. For a given trajectory, the aerodynamic heat, ablation performance of thermal protection layer and temperature filed are predicted by the coupling method. The proposed method can be used to calculate the ablation and temperature distribution in given operation conditions in design phase which is referable for the design of multi-layer thermal protection material for hypersonic aircrafts. © 2015, China Ordnance Society. All right reserved.

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