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针对预测飞行器再入过程中气动热流引发的烧蚀热响应导致热防护罩表层材料质量损耗的问题,研究了热防护罩的几何模型和烧蚀质量估算的方法,通过建立三自由度再入轨迹动力学方程,应用修正的牛顿流体理论计算气动系数,以及Detra-Kemp-Riddell和Tauber-Sutton理论计算驻点热流密度和热辐射,利用一维非线性热传导方程模拟了碳化材料的烧蚀过程,提出了基于Newton-Raphson和TDMA的烧蚀热响应算法估计飞行器热防护罩质量损耗的方法。通过分析,实现了再入全过程热防护材料烧蚀深度连续动态变化的预测,能够有效替代热平衡积分法,估算的烧蚀质量为优化热防护罩的几何模型和再入轨迹提供了参考依据。
In order to predict the mass loss of the surface material of the thermal shield due to the thermal ablation response caused by the aerodynamic heat flow during the reentry of the aircraft, the geometric model of the thermal shield and the method of estimating the ablation mass are studied. By establishing a three-freedom reentry trajectory Kinetic equation, the modified Newtonian fluid theory is used to calculate the aerodynamic coefficient, and Detra-Kemp-Riddell and Tauber-Sutton theories are used to calculate the stagnation heat flux and thermal radiation. The ablation process of carbonized material is simulated by using one-dimensional nonlinear heat conduction equation. A method based on Newton-Raphson and TDMA ablation thermal response algorithm is proposed to estimate the mass loss of thermal shield of aircraft. Through the analysis, the prediction of the continuous dynamic change of the ablation depth of the thermal protective material during the reentry can be realized, which can effectively replace the thermal balance integral method. The estimated ablation quality provides a reference for optimizing the geometric model and reentry trajectory of the thermal protective cover.