边界层转捩飞行测量方法及实现

Boundary Layer Transition Flight Measurement and Implementation

针对高超声速边界层转捩飞行试验研究的需要,通过一体化的变厚度薄壁测温和热流辨识方法,利用测量薄壁内壁温度辨识表面热流可实现飞行器表面转捩位置的测量。考虑到飞行器高速飞行过程中表面气动加热和振动环境要求,对测量结构和机体结构开展了一体化模块设计,提高了测量结构的整体承载抗热振能力;利用热振联合地面试验系统,在飞行状态地面模拟条件下,对测热部件进行了热振联合试验考核,验证了测量结构的安全性和可靠性。地面热振联合试验和飞行试验结果表明,该型转捩测量结构可承受飞行条件气动加热和振动环境,能迅速地响应和准确地反映气动加热环境热流的变化,可准确捕捉飞行条件下高超声速边界层转捩现象。获取的热流转捩测量数据,可为高超声速转捩预测计算模型提供校准数据。

For the needs of hypersonic boundary layer transition flight test and research,through integrating the variable thickness thin wall temperature test and heat flow identification method,where thin wall temperature measurement is used to identify the surface heat flux,then aircraft surface transition position can be measured.Considering the requirements of surface aerodynamic heating and the vibration environment during the high speed flight of the aircraft,the integrated module of the measuring structure and the aircraft structure is designed to improve the overall load resistance of the measuring structure.The thermal-vibration test system is to test the thermal measuring components under the ground simulation condition of flight state,and the safety and reliability of the measuring structure are verified.The results of ground thermal-vibration and flight tests show that the transition measuring structure can withstand the aerodynamic heating and vibration environment under flight conditions,respond quickly to and accurately reflect the changes of heat flow in the aerodynamic heating environment,and accurately capture the hypersonic boundary layer transition phenomenon under flight conditions.The measured data can provide calibration data for the prediction and calculation model of hypersonic transition.