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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 aerodynamic heat flux in hypersonic flight, the heat flow identification technique was used to study the aerodynamic heat flow on the plate surface. First, the simulation data is used to verify the identification method. The results show that the error of the identification results of heat flow is small when the measurement noise is low. After that, the experiment of hypersonic aerodynamic hot-wind tunnel was carried out. The internal temperature of the slab was measured by embedded thermocouple, and the aerodynamic heat flow of slab surface was obtained by the identification of heat flow. Reliability. Finally, the identification results are compared with the theoretical results of heat flow in the boundary layer of the slab, and the reasons for the errors between the two are analyzed. The research in this paper lays the foundation for the practical application of heat flow identification technology.