高超声速飞行器受热壁板的气动弹性声振分析

doi:10.7527/S1000-6893.2016.0115

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

高超声速飞行器受热壁板的气动弹性声振分析

杨智春¹, 刘丽媛², 王晓晨¹

1. 西北工业大学航空学院, 西安 710072;
2. 北京航空航天大学航空科学与工程学院, 北京 100083

收稿日期:2016-01-07 修回日期:2016-04-03 出版日期:2016-12-15 发布日期:2016-04-20
通讯作者: 杨智春,Tel.:029-88460461,E-mail:yangzc@nwpu.edu.cn E-mail:yangzc@nwpu.edu.cn
作者简介:杨智春,男,博士,教授,博士生导师。主要研究方向:飞行器气动弹性力学、飞行器结构动力学与飞行器结构健康监测。Tel:029-88460461,E-mail:yangzc@nwpu.edu.cn;刘丽媛,女,硕士研究生。主要研究方向:流固耦合与湍流模拟。E-mail:nwpu_candice@126.com;王晓晨,男,博士研究生。主要研究方向:噪声振动与流固耦合。Tel:029-88460461,E-mail:wxc_npu@163.com
基金资助:
国家自然科学基金（11472216）

Analysis of aeroelastic vibro-acoustic response for heated panel of hypersonic vehicle

YANG Zhichun¹, LIU Liyuan², WANG Xiaochen¹

1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China

Received:2016-01-07 Revised:2016-04-03 Online:2016-12-15 Published:2016-04-20
Supported by:
National Natural Science Foundation of China (11472216)

摘要/Abstract

摘要：

高超声速飞行器壁板在非定常气动力、热载荷和噪声载荷构成的多物理场联合作用下，将表现出复杂的非线性气动弹性声振响应，特别是在颤振临界动压附近，受热载荷以及声载荷作用，壁板表现出复杂的跳变运动。基于von Karman大变形板理论，建立了热-声载荷和气动力共同作用下的壁板运动方程，分析了超声速气流中受热壁板的屈曲变形及热屈曲稳定性，借助势阱概念初步分析了壁板跳变运动产生的机理。通过定义“穿零频次”给出了跳变运动定量的分类方法，并计算得到不同温升和动压情况下，壁板发生跳变运动所对应的临界声压级。结果表明：在颤振临界动压之前，随着动压的增加，受热壁板势阱的深度先增大后减小，且受热壁板的势阱深度随着温升的增加而增大。

关键词: 壁板, 气动弹性, 气动加热, 声振响应, 跳变, 热屈曲, 势阱

Abstract:

Hypersonic vehicle panel in combination with unsteady aerodynamic pressure, thermal loading and acoustic loading exhibits a complex nonlinear aeroelastic vibration response. The panel shows a complex snap-through response, especially in the vicinity of the critical flutter dynamic pressure. Based on von Karman large deformation plate theory, the equations of motion under the interaction of aerodynamic pressure and thermal-acoustic loading are established. In addition, the buckling deformation and thermal buckling instability of a heated panel in supersonic flow is analyzed. According to the potential well theory, the mechanism of snap-through phenomenon is explored. By defining zero-cross frequency, a quantitative classification method for snap-through motion is proposed. Furthermore, the critical sound pressure level under different dynamic pressure and temperature conditions is calculated. The results show that when the dynamic pressure is smaller than the critical flutter dynamic pressure, the depth of the potential well first increases and then decreases with dynamic pressure increasing. And the depth of potential well increases with the increase of temperature rise.

Key words: panel, aeroelasticity, aerodynamic heating, vibro-acoustic response, snap-through, thermal buckling, potential well

中图分类号:

杨智春, 刘丽媛, 王晓晨. 高超声速飞行器受热壁板的气动弹性声振分析[J]. 航空学报, 2016, 37(12): 3578-3587.

YANG Zhichun, LIU Liyuan, WANG Xiaochen. Analysis of aeroelastic vibro-acoustic response for heated panel of hypersonic vehicle[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(12): 3578-3587.

参考文献

[1] 杨智春, 夏巍. 壁板颤振的分析模型、数值求解方法和研究进展[J]. 力学进展, 2010, 40(1):81-98. YANG Z C, XIA W. Analytical models, numerical solutions and advances in the study of panel flutter[J]. Advances in Mechanics, 2010, 40(1):81-98(in Chinese).
[2] THIODOR H B, PAUL H. High speed research program sonic fatigue summary report:NASA/CR-2005-213742[R]. Washington, D.C.:NASA, 2005.
[3] MEI C. Large deflection multimode response of clamped rectangular panels to acoustic excitation:AFWAL-TR-83-3121[R].[s.l.]:AF Wright Aeronautical Laboratories, 1983.
[4] ABDEL-MOTAGALY K, DUAN B, MEI C. Nonlinear response of composite panels under combined acoustic excitation and aerodynamic pressure[J]. AIAA Journal, 2000, 38(9):1534-1542.
[5] DHAINAUT J M, GOU X, MEI C, et al. Nonlinear random response of panels in an elevated thermal-acoustic environment[J]. Journal of Aircraft, 2004, 40(4):683-691.
[6] DHAINAUT J M, CHENG G F, MEI C. Response of plats under uniform random loads unsynchronized in time:AIAA-2006-1927[R]. Reston:AIAA, 2006.
[7] DHAINAUT J M. Nonlinear finite element modal formulation for panel flutter with thermal effects and acoustic excitation:AIAA-2012-1789[R]. Reston:AIAA, 2012.
[8] MILLER B A, MCNAMARA J J, SPOTTSWOOD S M, et al. The impact of flow induced loads on snap-through behavior of acoustically excited thermally buckled panels[J]. Journal of Sound and Vibration, 2011, 330(23):5736-5752.
[9] SUCHEENDRAN M M, BODONY D J, GEUBELLE P H. Coupled structural-acoustic response of a duct-mounted elastic plate with grazing flow[J]. AIAA Journal, 2014, 52(1):178-194.
[10] OSTOICH C M, BODONY D J, GEUBEUE P H. Interaction of a Mach 2.25 turbulent boundary layer with a fluttering panel using direct numerical simulation[J]. Physics of Fluid, 2013, 25(11):110806.
[11] PRZEKOP A, RIZZI S A, SWEITZER K A. An investigation of high-cycle fatigue models for metallic structures exhibiting snap-through response[J]. International Journal of Fatigue, 2008, 30(9):1579-1598.
[12] MIGNOLET M P, SOIZE C. Stochastic reduced order models for uncertain geometrically nonlinear dynamical systems[J]. Computer Method in Applied Mechanics and Engineering, 2008, 197(45-48):3951-3963.
[13] 夏巍. 超音速气流中受热复合材料壁板的非线性颤振特性研究[D]. 西安:西北工业大学, 2008. XIA W. Nonlinear flutter of heated composite panels in supersonic airflow[D]. Xi'an:Northwestern Polytechnical University, 2008(in Chinese).
[14] YANG C, LI G S, WAN Z Q. Aerothermal aeroelastic two-way coupling method for hypersonic curved panel flutter[J]. Science China Technological Sciences, 2012, 55(3):831-840.
[15] 李鹏, 杨翊仁, 鲁丽. 外激励作用下亚音速二维壁板的复杂响应研究[J]. 计算力学学报, 2011, 28(6):864-871. LI P, YANG Y R, LU L. Complicated response analysis of two-dimensional thin panel in subsonic flow with external excitation[J]. Chinese Journal of Computational Mechanics, 2011, 28(6):864-871(in Chinese).
[16] 沙云东, 魏静, 高志军, 等. 热声载荷作用下薄壁结构的非线性响应特性[J]. 航空学报, 2013, 34(6):1336-1346. SHA Y D, WEI J, GAO Z J, et al. Nonlinear response characteristics of thin-walled structures under thermos-acoustic loadings[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(6):1336-1346(in Chinese).
[17] 沙云东, 郭小鹏, 廖连芳, 等. 随机声载荷作用下的复合薄壁结构Von Mises应力概率分布研究[J]. 振动与冲击, 2011, 30(1):137-141. SHA Y D, GUO X P, LIAO L F, et al. Probability distribution of Von Mises stress for complex thin-walled structures undergoing random acoustic loadings[J]. Journal of Vibration and Shock, 2011, 30(1):137-141(in Chinese).
[18] DOWELL E H. Nonlinear oscillations of a fluttering plate II[J]. AIAA Journal, 1967, 5(10):1856-1862.
[19] BLEVINS R D, BOFILIOS D, HOLEHOUSE I, et al. Thermo-vibro-acoustic loads and fatigue of hypersonic flight vehicle structure:AFRL-RB-WP-TR-2009-3139[R]. Chula Vista, CA:Goodrich Aerostructures Group, 2009.
[20] 贺尔铭, 刘峰, 胡亚琪, 等. 热声载荷下薄壁结构非线性振动响应分析及疲劳寿命预测[J]. 振动与冲击, 2013, 32(24):135-139. HE E M, LIU F, HU Y Q, et al. Nonlinear vibration response analysis and fatigue life prediction of a thin-walled structure under thermal-acoustic loading[J]. Journal of Vibration and Shock, 2013, 32(24):135-139(in Chinese).

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

高超声速飞行器受热壁板的气动弹性声振分析

Analysis of aeroelastic vibro-acoustic response for heated panel of hypersonic vehicle

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	田阔, 孙志勇, 李增聪. 面向结构静力试验监测的高精度数字孪生方法[J]. 航空学报, 2024, 45(7): 429134-429134.
[2]	孟亮, 杨金沅, 杨智威, 高彤, 刘洪权, 张卫红. 典型飞机壁板结构的抗屈曲优化设计与试验验证[J]. 航空学报, 2024, 45(5): 529679-529679.
[3]	张程, 任浩源, 史泰龙, 戴雯迪. 含非线性连接的折叠舵全时域多学科耦合分析方法及应用[J]. 航空学报, 2023, 44(S2): 729461-729461.
[4]	陈浩宇, 王彬文, 宋巧治, 李晓东. 热颤振地面模拟试验技术[J]. 航空学报, 2023, 44(8): 227295-227295.
[5]	喻世杰, 周兴华, 黄锐. 变弯度机翼参数化气动弹性建模与颤振特性分析[J]. 航空学报, 2023, 44(8): 227346-227346.
[6]	王培涵, 吴志刚, 杨超, 孙晓旭. 一种适用于弹性飞机飞行仿真的补丁方法[J]. 航空学报, 2023, 44(6): 127038-127038.
[7]	刘为佳, 李映坤, 陈雄, 李春雷. 基于流固耦合的激波/边界层干扰作用下壁板颤振特性[J]. 航空学报, 2023, 44(6): 127085-127085.
[8]	王梓伊, 张伟伟, 刘磊, 杨肖峰. 适用于复杂流动的热气动弹性降阶建模方法[J]. 航空学报, 2023, 44(4): 126807-126807.
[9]	汪松柏, 陈勇, 吴亚东, 张少平, 曹志鹏. 轴流压气机转子叶片非同步振动研究进展[J]. 航空学报, 2023, 44(17): 28044-028044.
[10]	郭瑜超, 王立凯, 孙喜桂, 聂小华. 民用飞机机身壁板复杂试验载荷优化技术[J]. 航空学报, 2023, 44(17): 227989-227989.
[11]	王立波, 荆志伟, 唐矗. 波阵风中的弹性飞机动力学建模与仿真[J]. 航空学报, 2023, 44(17): 228214-228214.
[12]	杨应科, 李东升, 沈立恒, 李汝鹏, 翟雨农. 大型复合材料机身壁板多机器人协同装配调姿控形方法[J]. 航空学报, 2023, 44(14): 428006-428006.
[13]	张志楠, 宁宇, 庄茁, 王恒, 秦剑波, 严红. 大型飞机整体壁板损伤断裂分析方法[J]. 航空学报, 2022, 43(6): 526134-526134.
[14]	汪厚冰, 王夏涵, 林国伟, 李新祥, 杨胜春. 含离散源损伤的复合材料壁板的剩余强度评估[J]. 航空学报, 2022, 43(6): 525899-525899.
[15]	李崇, 柴亚南, 王彬文, 陈向明, 于振波, 周红. 大型机身壁板复杂应力场试验技术[J]. 航空学报, 2022, 43(6): 526409-526409.