发汗冷却控制系统的参数辨识

本文针对飞行器再入全程热环境的地面模拟试验和飞行实测研究，应用发汗冷却控制技术，通过热层内点温度测量，引入敏感系数，给出热层加热面表面热流的参数辨识方法，解决了这一参数辨识定解问题的不适定性。由于应用了发汗冷却控制技术，避免了热层表面出现烧蚀，内点测温可以获得全程信息，因此为再入热环境的全程实验研究提供了实现的途径。本文参数辨识的计算结果与正问题的数值模拟结果吻合得很好。

Parameter Identification of Transpiration Cooling Control System

In this paper, by using the transpiration cooling control technique and the temperature measurement of inside points of the thermal shield, and by introducing the sensitive coefficient,the parameter identification of the surface heat transfer for the thermal shield is obtained. The no-well posed question of this parameter identification is solved. Due to the application of this technique the surface ablation of the thermal shield is avoided and the information of all process for the temperature measurement of inside points can be got. So it provides a means of the experimental study of all process of the reentry heat enviroment. The present results of calculations agree very well with those of the numerical simulation of the ordinary problem.