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- W2355921912 abstract "The ablation of a heat shield subjected to dynamic changes of the surface material depth and temperature can be reasonably predicted in the whole re-entry process.The approach of constructing a dynamic ablation process is presented by combining the reentry trajectory and aerodynamic heat with Newton-Raphson and tridiagonal matrices(TDMA)algorithms.A three degrees of freedom direct and skip re-entry trajectory model is established.The modified Newtonian flow theory,FayRiddell and Sutton-Grave theory are adopted to calculate respectively the aerodynamic parameters and stagnation heat flux. A one dimensional nonlinear heat conduction model is employed to simulate the process of thermal protective material ablation.The results of ablation prediction demonstrate that continuous dynamic change of the surface material depth and the temperature can be realized.The proposed method can be applied to more complicated structures of the flight vehicles and the results of it are shown to be reliable and reasonable by comparing them with those of the heat balance integral(HBI) method.This study provides a reference for further optimization of the design of thermal protection systems(TPS)." @default.
- W2355921912 created "2016-06-24" @default.
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- W2355921912 date "2014-01-01" @default.
- W2355921912 modified "2023-09-26" @default.
- W2355921912 title "Research on Ablation for Crew Return Vehicle Based on Re-entry Trajectory and Aerodynamic Heating Environment" @default.
- W2355921912 hasPublicationYear "2014" @default.
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