高速飞行器空腔脉动压力主动控制与非线性数值模拟

doi:10.7527/S1000-6893.2014.0277

实验与数值模拟

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

高速飞行器空腔脉动压力主动控制与非线性数值模拟

王一丁^1,2, 郭亮^1,2, 童明波¹, 张杰³

1. 南京航空航天大学航空宇航学院, 南京 210016;
2. 成都飞机设计研究所, 成都 610091;
3. 北京银景科技有限公司, 北京 100107

收稿日期:2014-07-02 修回日期:2014-10-08 出版日期:2015-01-15 发布日期:2014-10-23
通讯作者: 童明波,Tel.: 025-84896031 E-mail: tongw@nuaa.edu.cn E-mail:tongw@nuaa.edu.cn
作者简介:王一丁男,博士研究生。主要研究方向: 计算气动声学,噪声控制。 E-mail: wyding127@163.com;郭亮男,博士研究生,工程师。主要研究方向: 飞机气动综合设计。 E-mail: brightgl@hotmail.com;童明波男,博士,教授,博士生导师。主要研究方向: 飞行器总体设计。 Tel: 025-84896031 E-mail: tongw@nuaa.edu.cn;张杰男,博士,工程师。主要研究方向: 计算气动声学。 E-mail: jerry.zhang@visionstrategy.com.cn
基金资助:
航空科学基金(2012ZC52035)

Active control and nonlinear numerical simulation for oscillating pressure of high-speed aircraft cavity

WANG Yiding^1,2, Guo Liang^1,2, TONG Mingbo¹, Zhang Jie³

1. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Chengdu Aircraft Design and Research Institute, Chengdu 610091, China;
3. Beijing Yinjing Technology Co., Ltd., Beijing 100107, China

Received:2014-07-02 Revised:2014-10-08 Online:2015-01-15 Published:2014-10-23
Supported by:
Aeronautical Science Foundation of China (2012ZC52035)

摘要/Abstract

摘要：

空腔脉动压力(空腔噪声)预测是高速飞行器内埋弹舱的关键技术之一。非线性噪声求解方法是近年来新提出的一种噪声求解方法,为研究该方法对空腔噪声的预测性能,将雷诺平均Navier-Stokes(RANS)方程与之相结合。首先,通过RANS求解空腔周围流场,得到初始湍流统计平均解,其中包含平均流场基本特征及强制设定的湍流脉动的统计描述。然后,采用非线性噪声求解方法重构噪声源并高精度模拟压力脉动的传播,计算了马赫数Ma=1.5和Ma=5条件下的空腔噪声。结果表明,噪声特性计算值与试验结果基本吻合,说明非线性噪声求解方法对于高速空腔流动噪声具有较好的预测能力。在此基础上,研究了马赫数Ma=1.5和Ma=5条件下在空腔前缘加入气帘喷流主动控制措施对噪声的抑制作用,并得出在超声速和高超声速条件下,气帘喷流对于空腔脉动压力都有较好的抑制作用。

关键词: 脉动, 非线性, 空腔, 湍流, 主动控制

Abstract:

Prediction of oscillating pressure is a key technology for the weapon bay of high-speed aircraft cavity. Nonlinear numerical simulation is proposed as a new method to analyze noise recently. In order to evaluate the prediction performance of cavity noise, nonlinear numerical simulation solver is combined with Reynolds-averaged Navier-Stokes(RANS) equation. Firstly, the flow field around cavity is solved by RANS, and the average solution of initial turbulent statistics is obtained which contains the basic characteristics of average flow field and statistics description of turbulence fluctuation. After that, noise source is refactored and the spreading of pressure fluctuation is simulated precisely by the nonlinear acoustics solution. According to the comparison of the cavity noise calculation and experimental results under Ma = 1.5 and Ma = 5, it indicates that nonlinear numerical solution is able to well predict cavity flow noise at high speed. Based on that, the contribution to noise suppression made by active control such as adding jet screen at the leading edge of cavity under Ma = 1.5 and Ma = 5 is investigated. It is found that jet screen is suitable for suppression of oscillating pressure under supersonic condition as well as in hypersonic state.

Key words: oscillating, nonlinear, cavity, turbulence, active control

中图分类号:

V211.3

王一丁, 郭亮, 童明波, 张杰. 高速飞行器空腔脉动压力主动控制与非线性数值模拟[J]. 航空学报, 2015, 36(1): 213-222.

WANG Yiding, Guo Liang, TONG Mingbo, Zhang Jie. Active control and nonlinear numerical simulation for oscillating pressure of high-speed aircraft cavity[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(1): 213-222.

参考文献

[1] Wu J F, Luo X F, Fan Z L. Flow control method to improve cavity flow and store separation characteristic[J]. Acta Aeronautica et Astronautica Sinica, 2009, 30(10): 1840-1845 (in Chinese). 吴继飞, 罗新福, 范召林.内埋式弹舱流场特性及武器分离特性改进措施[J]. 航空学报, 2009, 30(10): 1840-1845.

[2] Feng Q, Cui X C. Study on integrated flow control for weapons bay of flying wing configuration aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(5): 781-787 (in Chinese). 冯强, 崔晓春. 飞翼布局飞机武器舱综合流动控制技术研究[J]. 航空学报, 2012, 33(5): 781-787.

[3] Perng S W. Passive control of pressure oscillations in hypersonic cavity flow[D]. Austin: University of Texas at Austin, 1996.

[4] Barter J W. Prediction and passive control of fluct-uating pressure loads produced by shock-induced turbulent boundary layer separation[D]. Austin: University of Texas at Austin, 1995.

[5] Shaw L. Active control for cavity acoustics, A1AA-1998-2347[R].Reston: AIAA, 1998.

[6] Miehael J A.Control of cavity resonance through very high frequency forcing, AIAA-2000-1905[R]. Reston: AIAA, 2000.

[7] Smith B R, Welterlen T J, Maines B H, et al.Weapons bay acoustic suppression from rod spoilers,AIAA-2002-0662[R].Reston: AIAA, 2002.

[8] Alvi F S, Elavarasan R, Garg G, et al. Control of supersonic impinging jet using microjets, AIAA-2000-2236 [R]. Reston: AIAA, 2000.

[9] Bower W W, Kibens V, Cary A W, et al. High-frequency excitation active flow control for high-speed weapon release(HIFEX), AIAA-2004-2513[R]. Reston: AIAA, 2004.

[10] Tam C K W. Computational aeroacoustics:an overview of computational challenges and applications[J]. International Journal of Computational Fluid Dynamics, 2004, 18(6): 547-567.

[11] Long S L, Nie H, Xue C J, et al. Simulation and experiment on aeroacoustic noise characteristics of aircraft landing gear[J]. Acta Aeronautica et Astronautica Sinica,2012, 33(6): 1002-1013 (in Chinese). 龙双丽, 聂宏, 薛彩军, 等. 飞机起落架气动噪声特性仿真与试验[J]. 航空学报, 2012, 33(6): 1002-1013.

[12] Hou Z X, Yi S H, Wang C Y. Numerical analysis of supersonic open cavity[J]. Journal of Propulsion Technology, 2001, 22(5): 400-403 (in Chinese). 侯中喜, 易仕和, 王承尧. 超声速开式空腔流动的数值模拟[J]. 推进技术, 2001, 22(5): 400-403.

[13] Li X D, Liu J D, Gao J H. Numerical simulation of flow-induced oscillation and sound generation in a cavity[J]. Chinese Journal of Theoretical and Applied Mechanics, 2006, 38(5): 599-604 (in Chinese). 李晓东, 刘靖东, 高军辉. 空腔流激振荡发声的数值模拟研究[J]. 力学学报, 2006, 38(5): 599-604.

[14] Batten P, Ribaldone E, Casella M, et al. Towards a generalized non-linear acoustics solver, AIAA-2004-3001[R]. Reston: AIAA, 2004

[15] Batten P,Goldberg U,Chakravarthy S. Reconstructed sub-grid methods for acoustics predictions at all Reynolds Numbers, AIAA-2002-2511[R]. Reston: AIAA, 2002.

[16] Silva C R I, Almeida O, Batten P. Investigation of an axi-symmetric subsonic turbulent jet using computational aeroacoustics tools,AIAA-2007-3656[R]. Reston: AIAA, 2007.

[17] Aflalo B S, Simoes L G C, Silva R G, et al. Comparative analysis of turbulence models for slat noise source calculations employing unstructured meshes, AIAA-2010-3838 [R]. Reston: AIAA, 2010.

[18] Rossiter J E.Wind tunnel experiments on the flow over rectangular cavities at subsonic and transonic speeds, RAE Technical Report No. 64037[R]. Hampshire: Royal Aircraft Establishment, 1964.

[19] Unalmis O H, Clemens N T, Dolling D S. Experimental study of shear-layer/acoustics coupling in Mach 5 cavity flow[J]. AIAA Journal, 2001, 39(2): 242-252.

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

高速飞行器空腔脉动压力主动控制与非线性数值模拟

Active control and nonlinear numerical simulation for oscillating pressure of high-speed aircraft cavity

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]	王迪, 冷岩, 杨龙, 韩忠华, 钱战森. 基于广义Burgers方程的声爆传播特性大气湍流影响[J]. 航空学报, 2023, 44(2): 626318-626318.
[2]	施方成, 高振勋, 田雨岩, 蒋崇文, 王田天, 李椿萱. 超声速理想膨胀喷流噪声的大涡模拟[J]. 航空学报, 2023, 44(2): 626266-626266.
[3]	乔建领, 韩忠华, 丁玉临, 宋文萍, 宋笔锋. 分层大气湍流场对远场声爆传播的影响[J]. 航空学报, 2023, 44(2): 626350-626350.
[4]	田得阳, 平熠, 陈烨斯, 陈伟芳. 物理化学模型对流场电磁波传播特性影响[J]. 航空学报, 2022, 43(S2): 214-224.
[5]	王新光, 毛枚良, 何琨, 陈琦, 万钊. 壁面函数在超声速湍流模拟中的应用[J]. 航空学报, 2022, 43(9): 126153-126153.
[6]	许文纲, 王志颖, 孙闯, 严如强, 陈雪峰. 转频调制下齿轮泵压力脉动机理[J]. 航空学报, 2022, 43(9): 625508-625508.
[7]	程剑锐, 施崇广, 瞿丽霞, 徐悦, 尤延铖, 朱呈祥. 二维弯曲激波/湍流边界层干扰流动理论建模[J]. 航空学报, 2022, 43(9): 125993-125993.
[8]	童福林, 董思卫, 段俊亦, 李新亮. 激波/湍流边界层干扰分离泡直接数值模拟[J]. 航空学报, 2022, 43(7): 125437-125437.
[9]	刘俊, 罗新福, 王显圣. 前缘形状对空腔模型气动特性影响试验[J]. 航空学报, 2022, 43(7): 125235-125235.
[10]	吴航空, 王丁喜, 黄秀全, 徐慎忍. 定黏假设"对伴随系统求解和梯度精度影响[J]. 航空学报, 2022, 43(7): 125512-125512.
[11]	张昊元, 孙东, 邱波, 朱言旦, 王安龄. 湍动能在激波/边界层干扰流动中的影响[J]. 航空学报, 2022, 43(7): 125504-125504.
[12]	周宜涛, 杨阳, 吴志刚, 杨超. 大展弦比无人机平台的阵风减缓飞行试验[J]. 航空学报, 2022, 43(6): 526126-526126.
[13]	朱荻, 刘嘉, 王登勇, 房晓龙, 刘言. 脉动态电解加工[J]. 航空学报, 2022, 43(4): 525959-525959.
[14]	荆涛, 田锡天. 基于蒙特卡洛-自适应差分进化算法的飞机容差分配多目标优化方法[J]. 航空学报, 2022, 43(3): 425278-425278.
[15]	李强, 万兵兵, 杨凯, 朱涛. 高超声速尖锥边界层压力脉动和热流脉动特性试验[J]. 航空学报, 2022, 43(2): 124956-124956.