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为了研究气动弹性对高超声速进气道性能的影响,基于模态方法对不同厚度的二维进气道薄壁结构进行气动弹性分析。首先,对DLR中GK01二维进气道实验模型进行数值模拟,计算结果与实验结果吻合较好,验证了计算方法的可靠性。以此模型为研究对象,在时域内,对不同厚度的二维进气道薄壁结构进行气动弹性分析,其中二维进气道的模态数据从三维模态数据中提取。计算结果表明:(1)随薄壁结构厚度的增加,进气道的气动弹性特性由发散变为收敛,由于结构的固有频率比较接近,广义位移随时间的变化历程表现出“拍”效应;(2)即使是较小幅度的振动,也会对进气道性能产生较明显的影响,对于本文模型,其流量系数、总压恢复系数和压升比的最大变化幅度分别达到14.34%,25.07%和110.37%。因此,设计进气道结构时,应考虑气动弹性的影响。
In order to study the effect of aeroelasticity on the performance of hypersonic air intake, aeroelastic analysis of two-dimensional air intake thin-walled structures of different thicknesses is carried out based on the modal method. First of all, numerical simulation of GK01 two-dimensional inlet experimental model in DLR is carried out. The calculated results are in good agreement with the experimental results, which verifies the reliability of the calculation method. Taking the model as the research object, the aerodynamic elasticity of the two-dimensional air intake thin-walled structures with different thicknesses is analyzed in the time domain. The modal data of the two-dimensional air intake are extracted from the three-dimensional modal data. The results show that: (1) With the increase of the thickness of the thin-walled structure, the aeroelastic characteristics of the air intake change from divergence to convergent, and the natural frequency of the structure is relatively close. The generalized displacement changes with the course of time, (2) even a small amplitude of vibration will have a significant impact on the inlet performance. For the model, the maximum variation of the flow coefficient, the total pressure recovery coefficient and the pressure-rising ratio are 14.34% , 25.07% and 110.37% respectively. Therefore, the design of the inlet structure should take into account the impact of aeroelasticity.