高超声速进气道气动弹性的影响研究

发布时间：2018-12-18 00:49

【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。
[Abstract]:In order to study the effect of Aeroelasticity on hypersonic inlet performance, Aeroelastic analysis of thin-walled two-dimensional inlet structures with different thickness was carried out based on modal method. First, the numerical simulation of the GK01 two-dimensional inlet model in DLR is carried out, and the calculated results are in good agreement with the experimental results, which verifies the reliability of the calculation method. Based on the model, Aeroelastic analysis of thin-walled structure with different thickness is carried out in time domain, in which the modal data of two-dimensional inlet are extracted from three-dimensional modal data. The results show that: (1) with the increase of thin-walled structure thickness, the Aeroelastic characteristics of the inlet change from divergence to convergence. Because the natural frequency of the structure is relatively close, the variation of generalized displacement with time shows the "beat" effect; (2) even small amplitude vibration will have obvious influence on the performance of the inlet. For this model, the maximum variation range of flow coefficient, total pressure recovery coefficient and pressure rise ratio is 14.34, respectively. 25.07 percent and 110.37 percent. Therefore, the effect of Aeroelasticity should be taken into account in the design of inlet structure.
【作者单位】：西北工业大学航空学院;
【基金】：国家自然科学基金(11272262)
【分类号】：V211.47

【相似文献】