高超声速气动热辨识技术实验研究

Experimental study of heat flux identification technology for hypersonic aero-thermodynamics

为估计高超声速飞行中的气动热流,采用热流辨识技术研究了平板表面的气动热流。首先采用仿真数据对辨识方法进行验证,结果表明,在测量噪声较低时热流辨识结果误差较小。此后,开展了平板的高超声速气动热风洞实验,通过内埋热电偶测量平板内部温度,采用热流辨识法获得平板表面的气动热流,采用辅助测点对比验证了内埋测点辨识结果的可信度。最后将辨识结果与平板边界层热流理论估算结果进行对比,分析了两者产生误差的原因。本文的研究为热流辨识技术的实际应用奠定了基础。

In order to estimate the heat flux of aero-thermo in hypersonic flight,the heat flux identification method has been introduced in this paper.Heat flux simulation is introduced to validate this method.The results show that small difference between simulated heat flux and the identified results is achieved with low variance noises inserted in.Series of wind tunnel experiments have been carried out to identify the heat flux with buried thermocouples measuring inner temperatures.An assistant measure point result is compared with the identifactation result by the buried thermocouples.At last,the boundary layer flux theory is used to analyze the aero-thermo results quantitatively.This research is expected to improve the practical application of the heat flux identification method.