气动热环境试验及测量技术研究进展

地面风洞试验和飞行试验是研究高超声速飞行器气动加热的主要手段。针对临近空间复杂气动外形高超声速飞行器气动热环境研究的需要，分析探讨了国内气动热试验及测量技术的发展情况。分析了临近空间高超声速飞行器外形特征以及飞行剖面、边界层转捩和气动热环境特性等，进而分析了气动热环境风洞试验模拟理论，介绍了适用于气动热研究的风洞试验设备及其模拟能力，重点讨论了适用于不同类型风洞的热流测量技术发展近况、存在的问题和发展趋势；在以长时间、高热流、高壁温为主要特征的高超声速飞行试验中，无法应用风洞环境下的热流测量技术，因而介绍了目前飞行试验中采用的气动热测量技术，讨论了根据结构温度反辨识表面热流存在的问题，以及热流传感器表面的"冷点效应"、表面催化特性等因素对飞行试验气动热测量的影响，提出了后续工作中应重点研究和解决的临近空间飞行器气动热环境测量技术问题。

Research progress of aerodynamic thermal environment test and measurement technology

Ground wind tunnel tests and flight tests are the primary means of obtaining pneumatic heating data. In this paper, the development of the domestic hypersonic aerodynamic test and the heat flux measurement technology is analyzed and discussed. Firstly, the shape characteristics, the flight profile, the boundary layer transition and the aerodynamic thermal environment characteristics of the adjacent space hypersonic vehicles are analyzed. On this basis, the wind tunnel test simulation theory of the aerodynamic thermal environment is analyzed, and the domestic application for aerodynamic thermal measurement, wind tunnel test equipment and its simulation capability are introduced, focusing on the analysis of the development and trend of wind tunnel aerodynamic thermal environment measurement technology, including point measurement technology based on sensor measurement and non-contact measurement technology such as phosphorescence heat map technology and infrared heat map technology. Finally, the measurement principle and engineering application of the "built-in" and "embedded" measure-ment technologies are introduced for the flight test thermal environment measurement. The problems faced by the flight test aerodynamic thermal environment measurement are discussed. Both further research and present problems for thermal environment measurement technologies are proposed.