高超声速飞行器表面测热技术综述

高超声速飞行中飞行器表面气动加热量是飞行器热防护系统最为关键的设计输入，在理论计算与地面模拟的有限近似条件下，通过飞行试验实时获取真实环境下飞行器表面的气动加热量，并在此基础上完成对计算模型与地面试验的验证与改进具有重要意义。详细列举了20世纪50年代以来，国外具有代表性的飞行试验与测热方案。以“内置式”与“嵌入式”作为测热技术的分类特征，介绍了各类测试设备及相应的飞行试验结果。着重分析了“热匹配性”与“结构匹配性”作为关键因素对飞行测热技术的影响，通过飞行试验实例介绍了该问题的解决方法及工程经验。归纳了飞行测热技术发展的共性、特点与未来趋势，并结合当前我国发展现状，对该领域未来研究提出建议。

Overview of Heat Measurement Technology for Hypersonic Vehicle Surfaces

The aero thermal heating rate of hypersonic vehicle surfaces is a key input parameter for thermal protection system design, It is of great significance, in view of the limitation of computation and ground test, to obtain the aerothermal heating rate in the real environment of flight, and then validate and upgrade the computation code and ground test based on this information. Typical flight missions in the world and their in-flight heat transfer measurement plans since the 1950s are enumerated in this study. With the "Design in" and "Add on" as the classification features for heat measuring technology, various instruments and corresponding flight results are described. The impact of "thermal matching" and "structural matching" is analysed as a key factor for the flight heat transfer measurement technology, solution of the problem and engineering experience introduced by flight test examples. A conclusion is made for the general and specific characteristics, and the development trend for heat measurement technology. Finally, suggestions are made based on the above study for future research in this field.