高超声速进气道气动弹性的影响研究

推进技术 ›› 2016, Vol. 37 ›› Issue (12): 2270-2277.

高超声速进气道气动弹性的影响研究

叶坤,叶正寅,屈展

西北工业大学航空学院，陕西西安 710072,西北工业大学航空学院，陕西西安 710072,西北工业大学航空学院，陕西西安 710072

发布日期:2021-08-15
作者简介:叶坤，男，博士生，研究领域为高超声速热气动弹性和超声速燃烧。
基金资助:
国家自然科学基金(11272262)。

Effects of Aeroelasticity on Performance of Hypersonic Inlet

College of Aeronautics，Northwestern Polytechnical University，Xi’an 710072，China,College of Aeronautics，Northwestern Polytechnical University，Xi’an 710072，China and College of Aeronautics，Northwestern Polytechnical University，Xi’an 710072，China

Published:2021-08-15

摘要/Abstract

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

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

叶坤,叶正寅,屈展. 高超声速进气道气动弹性的影响研究[J]. 推进技术, 2016, 37(12): 2270-2277.

YE Kun,YE Zheng-yin,QU Zhan. Effects of Aeroelasticity on Performance of Hypersonic Inlet[J]. Journal of Propulsion Technology, 2016, 37(12): 2270-2277.

参考文献

[1] H?berle J, Gülhan A. Investigation Two-Dimensional Scramjet Inlet Flowfield at Mach 7[J]. Journal of Propulsion and Power, 2008, 24, (3): 446-459.
[2] Mahapatra D, Jagadeesh G. Studies on Unsteady Shock Interactions Near a Generic Scramjet Inlet[J]. AIAA Journal, 2009, 47(9): 2223-2231.
[3] Krishnan L, Sandham N D, Steelant J. Shock- Wave/Boundary-Layer Interactions in a Model Scramjet Intake[J]. AIAA Journal, 2009, 47(7): 1680-1691.
[4] Kline H, Palacios F, Alonsoz J J. Sensitivity of the Performance of a 3-Dimensional Hypersonic Inlet to Shape Deformations[R]. AIAA 2014-3228.
[5] Lamorte N, Friedmann P P. Uncertainty Propagation in Integrated Airframe-Propulsion System Analysis for Hypersonic Vehicles[R]. AIAA 2011-2394.
[6] Culler A J, Mcnamara J J. Impact of Fluid-Thermal- Structural Coupling on Response Prediction of Hypersonic Skin Panels[J]. AIAA Journal, 2011, 49(11): 2393-2406.
[7] Duzel U, Eyi S. The Effect of Static Aeroelasticity on the Performance of Supersonic/Hypersonic Nozzles[R]. AIAA 2014-2770.
[8] Yao C, Liu Z S. Effect of Wall Deformation on Aerodynamic Performance for Mixed Compression Intake[R]. AIAA 2014-2445.
[9] Yao C, Liu Z S. Numerical Vibration Analysis of Supersonic Mixed-Compression Intake[R]. ASME 2013-GT-95444.
[10] 靖建朋, 郭荣伟. 气动变形对独立模块薄壳进气道性能影响研究[J]. 宇航学报, 2011, 32(1): 210-218.
[11] 张云峰. 高速气流作用下冲压发动机进气道壁板结构振动特性研究[D]. 哈尔滨:哈尔滨工业大学, 2007.
[12] Culler A J, McNamara J J. Studies on Fluid-Thermal- Structural Coupling for Aerothermoelasticity in Hyper- sonic Flow[J]. AIAA Journal, 2010, 48(8): 1721-1738.
[13] 蒋跃文, 张伟伟, 叶正寅. 基于CFD技术的流场/结构时域耦合求解方法研究[J]. 振动工程学报, 2007, 20(4): 396-400.
[14] 谢亮, 徐敏, 安效民, 等. 基于径向基函数的网格变形及非线性气动弹性时域仿真研究[J]. 航空学报, 2013, 34(7): 1501-1511.
[15] H?berle J, Gülhan A. Experimental Investigation of a Two-Dimensional and a Three-Dimensional Scramjet Inlet at Mach 7[J]. Journal of Propulsion and Power, 2008, 24, (5): 1024-1034.
[16] 徐旭, 蔡国飙. 超燃冲压发动机二维进气道优化设计方法研究[J]. 推进技术, 2001, 22(6): 468-472. (XU Xu, CAI Guo-biao. Design and Optimization Method for Two Dimensional Scramjet Inlet[J]. Journal of Propulsion Technology, 2001, 22(6): 468-472.)
[17] 范晓樯, 李桦, 李晓宇, 等. 高超声速二维进气道参数化设计方法初探[J]. 航空动力学报, 2007, 22(1): 66-72.
[18] 钟启涛, 张堃元, 庞丽娜. 出口马赫数分布可控的二元高超进气道双重反设计[J]. 推进技术, 2015, 36(7): 982-988. (ZHONG Qi-tao, ZHANG Kun-yuan, PANG Li-na. Double Inverse Design of 2-D Hyper- sonic Inlet with Controllable Exit Mach Number Distribution[J]. Journal of Propulsion Technology, 2015, 36(7): 982-988.)　　　　　　　　　　　　　*　收稿日期:2015-07-30；修订日期:2015-09-23。基金项目:国家自然科学基金(11272262)。作者简介:叶坤,男,博士生,研究领域为高超声速热气动弹性和超声速燃烧。E-mail: yekun@mail.nwpu.edu.cn(编辑:张荣莉)