全部 标题 作者
关键词 摘要

OALib Journal期刊
ISSN: 2333-9721
费用:99美元

查看量下载量

相关文章

更多...
航空学报  2013 

低声爆静音锥设计方法研究

DOI: 10.7527/S1000-6893.2013.0190, PP. 1009-1017

Keywords: 超声速飞机,激波,计算流体力学,声波传播,气动噪声

Full-Text   Cite this paper   Add to My Lib

Abstract:

声爆精确预测及低声爆设计方法已成为新一代军民用超声速飞机研制过程中必须解决的关键难题之一。基于计算流体力学(CFD)、波形参数法以及MARK-VII方法构建了高精度声爆预测方法,利用该方法对低声爆静音锥的设计展开研究。研究结果表明,静音锥的设计存在临界长度,静音锥长度小于临界长度时,静音锥产生的激波在传播过程中与机头弓形激波合并,静音锥无法起到降低声爆的作用;静音锥长度大于临界长度时,声爆水平也会略有上升。静音锥临界长度随飞行高度和飞行马赫数的变化而变化,可以根据实际飞行状态采用可伸缩设计,达到最佳的低声爆效果。多级静音锥利用多道弱激波取代机头强弓形激波,其声爆水平较单级静音锥也更低,同样,多级静音锥每一级的长度也要达到临界长度。不同静音锥头部形状产生的脱体激波形状不同,脱体距离也不同,导致阻力系数以及静音锥壁面温度有所不同,但静音锥头部形状对远场声爆信号的影响并不明显。采用静音锥的低声爆方案与原始方案比较,声爆水平得到大幅降低,阻力系数略有上升。

References

[1]  National Research Council. High speed research aeronautics and space engineering board U.S. supersonic commercial aircraft: assessing NASA’s high speed research program[M]. Washington, D.C.: National Academy Press, 1997.
[2]  Seebass A R. Sonic boom theory[J]. Journal of Aircraft, 1969, 6(13): 177-184.
[3]  Haas A, Kroo I. A multi-shock inverse design method for low-boom supersonic aircraft[R]. AIAA - 2010-843, 2010.
[4]  Li W, Shields E, Le D. Interactive Inverse Design Optimization of Fuselage Shape for Low-Boom Supersonic Concepts[J]. Journal of Aircraft, 2008,45(4):1381–1398.
[5]  Howe D C. Improved sonic boom minimization with extendable nose spike[R]. AIAA-2005-1014, 2005.
[6]  Donald Freund, Frank Simmons. Quiet spike? prototype flight test results[R].AIAA-2007-1778,2007.
[7]  陈鹏,李晓东.基于Khokhlov-Zabolotskaya-Kuznetsov方程的声爆频域预测法[J].航空动力学报,2010,25(2):359-365. (Chen Peng. Frequency domain method for predicting sonic boom propagation based on Khokhlov-Zabolotskaya-Kuznetsov equation. Journal of Aerospace Power, 2010;25(2):359-365.(in chinese))
[8]  但聃.基于声爆和起降噪声要求的超音速公务机设计[D].硕士学位论文,中国航空研究院611所,2010:31-35.(Dan Dan. Supersonic business design based on request of sonic boom and takeoff/approaching acoustics[D].Chengdu Aircraft Research and Design Institute,2010.(in chinese) )
[9]  冯晓强,李占科,宋笔锋. 超音速客机音爆问题初步研究[J]. 飞行力学, 2010, 28(6): 21-27. (Feng Xiaoqiang, Li Zhanke, Song Bifeng. Preliminary analysis on the sonic boom of supersonic aircraft[J]. Flight Dynamics,2010,28(6):21-27(in Chinese))
[10]  冯晓强,李占科,宋笔锋.超声速客机低音爆布局反设计技术研究[J].航空学报,2011,32(11):1980-1986. (Feng Xiaoqiang, Li Zhanke, Song Bifeng. A research on inverse design method of a lower sonic boom supersonic aircraft configuration[J]. Acta Aeronautica et Astronautica sinica,2011,32(11):1980-1986(in chinese))
[11]  冯晓强. 声爆计算方法研究及在超声速客机设计的应用[D].硕士学位论文,西北工业大学,2012:43-53.(Feng Xiaoqiang. The research of sonic boom prediction method and application in supersonic aircraft design[D]. Northwestern Polytechnical university,2012.(in chinese))
[12]  Isik Ali Ozcer. Sonic boom prediction using euler / full potential methodology[R].AIAA-2007-0369,2007.
[13]  Carlson H W. A wind tunnel investigation of the effect of body shape on sonic boom pressure distributions[R]. NASA TND-3106, 1965.
[14]  Thomas C L. Extrapolation of sonic boom pressure signatures by the waveform parameter method[R]. NASA TND-6832, 1972.
[15]  Stevens.S.S. Perceived level of noise by Mark VII and decibels. The Journal of the Acoustical Society of America,1972;51(2):575-601.
[16]  J D Anderson. Fundamentals of aerodynamics[M].New York,McGraw-Hill companies,2005.

Full-Text

Contact Us

service@oalib.com

QQ:3279437679

WhatsApp +8615387084133