Abstract: In order to study the effects of the aeroelasticity on the performance of the hypersonic inlet，based on the mode method，aeroelasticity analysis of the two-dimensional thin panel structure inlet with different thickness is conducted. First，the two-dimensional inlet GK01 experimental model of DLR is numerically simulated，and the calculation results are in good agreement with the experimental results，which validates the reliability of the calculation method. Based on this model，in the time domain，aeroelasticity of the two-dimensional inlet thin panel structure with different thickness is analyzed. The two-dimensional mode is extracted from three-dimensional mode. The calculation results show that: (1)with increase of the panel structure’s thickness，the aeroelasticity properties of inlet change from divergence to convergence. And the natural frequency of the structure is close，the general displacement shows the "beat" phenomenon over time. (2)The performance of the inlet will be affected significantly even with a small amplitude vibration. In this study，the maximum variation amplitude of flow coefficient，total pressure recovery coefficient and pressure rise ratio reached to 14.34%，25.07% and 110.37%，respectively. Therefore，the effects of the aeroelasticity of the inlet structure should be taken into consideration while designing the structure.

Key words: Hypersonic；Inlet；Aeroelasticity；Flow coefficient；Total pressure recovery coefficient

摘要： 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。

关键词: 高超声速；进气道；气动弹性；流量系数；总压损失系数