前体边条控制技术对航向静稳定性的影响

闻静; 王延奎; 邓学蓥

doi:10.13700/j.bh.1001-5965.2015.0746

前体边条控制技术对航向静稳定性的影响

doi: 10.13700/j.bh.1001-5965.2015.0746

北京航空航天大学航空科学与工程学院, 北京 100083

基金项目: 国家自然科学基金（11272035）

详细信息

作者简介:
闻静,女,博士研究生。主要研究方向:流体力学。Tel.:010-82317524,E-mail:wenjing-1983@163.com;王延奎,男,博士,教授,博士生导师。主要研究方向:流体力学。Tel.:010-82339591,E-mail:wangyankui@buaa.edu.cn;邓学蓥,男,博士,教授,博士生导师。主要研究方向:流体力学。Tel.:010-82317524,E-mail:dengxueying@vip.sina.com

通讯作者:
王延奎,Tel.:010-82339591,E-mail:wangyankui@buaa.edu.cn

中图分类号: V221⁺.3;TB553
计量
- 文章访问数: 721
- HTML全文浏览量: 65
- PDF下载量: 629
- 被引次数: 0
出版历程
- 收稿日期: 2015-11-12
- 网络出版日期: 2016-10-20

Effect of forebody strake control technology on static directional stability

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

Funds: National Natural Science Foundation of China (11272035)

摘要

摘要: 当飞机航向失稳时，垂尾所在的机身后体处于低能的翼身涡尾流中，效率降低，而机身前体则位于尚未干扰的气流中，在机身头部加前体边条，可以起到增加航向静稳定性作用。通过对一系列前体边条的试验研究，发现长度为机身总长3%的前体边条，可将全机航向失稳迎角提高约8°左右，且侧滑角越小，航向失稳迎角提高越多。通过测压和PIV试验数据可以发现，前体边条提高航向静稳定性，主要是由于前体边条产生边条涡，该涡主要影响机身前体，使得前体背风侧负压力值减小，从而导致前体截面不稳定偏航力矩减小，增加了全机的航向静稳定性。
- 航向静稳定性 /
- 翼身涡尾流 /
- 前体边条 /
- 偏航力矩 /
- 垂尾
Abstract: When static directional stability of an aircraft is unstable, the typical effectiveness of the vertical tail and rudder to the yawing moment falls off because the vertical tail gradually becomes enveloped in the wake of wing and fuselage. Meanwhile, the forebody remains in the undisturbed flow field, and therefore the static directional stability can be enhanced though addition of forebody strake at the forebody. From the results of a series of experiments on forebody strake, it was found that the angle of attack for static directional stability from stable to unstable was increased by about 8° when chord of the forebody strake being 3% of the length of the fuselage was used. Moreover, as the sideslip angle became smaller, the more angle of attack for static directional stability from stable to unstable rose. The positive effects of forebody strake on static directional stability is due to the vortices of the forebody strake, which could affect the front part of fuselage and thus result in the reduction of negative pressure value on leeward side of forebody. Hence, the unstable yawing moment of cross sections of forebody also decreases, and the static directional stability increases.
- static directional stability /
- wake of wing and fuselage /
- forebody strake /
- yawing moment /
- vertical tail

HTML全文

参考文献(15)

[1]	钱丰学,梁贞桧.边条翼布局战斗机稳定性改进研究[J].飞行力学,2002,20(2):55-61. QIAN F X,LIANG Z H.Investigation on the improvement of stabilities of combat aircraft with strake wing configuration[J].Flight Dynamics,2002,20(2):55-61(in Chinese).
[2]	NG T T,MALCOLM G N.Aerodynamic control using forebody strakes:AIAA-1991-0618[R].Reston:AIAA,1991.
[3]	MALCOLM G N,NG T T.Aerodynamic control of aircraft by forebody vortex manipulation[C]//AIAA Aerospace Engineering Conference and Show.Reston:AIAA,1990:1-22.
[4]	WILLIAMS D R.A review of forebody vortex control scenarios[C]//28th Fluid Dynamic Conference.Reston:AIAA,1997:1-9.
[5]	HUFFMAN J K,HAHNE D E,JOHNSON T D.Experimental investigation of the aerodynamic effect of distributed spanwise blowing on a flighter configuration[C]//2nd Applied Aerodynamics Conference.Reston:AIAA,1984:1-9.
[6]	MOSKOVITZ C A,HALL R M,DEJARNETTE F R.New device for controlling asymmetric flow fields on forebodies at large alpha[J].Journal of Aircraft,1991,28(7):456-462.
[7]	ERICSSON L E,BEYERS M E.Conceptual fluid/motion coupling in the herbst supermaneuver[J].Journal of Aircraft,1997,34(3):271-277.
[8]	MALCOLM G N.Forebody vortex control-A progress review:AIAA-1993-3540[R].Reston:AIAA,1993.
[9]	SUAREZ C J,KRAMER B R,MALCOLM G N.Forebody vortex control on an F/A-18 using small,rotatable "tip-strake":AIAA-1993-3450[R].Reston:AIAA,1993.
[10]	SHAH G H,GRANDA J N.Application of forebody strakes for directional stability and control of transport aircraft:AIAA-1998-4448[J].Reston:AIAA,1998.
[11]	刘谋佶.边条翼及分离涡研究[J].北京航空学院学报,1987,4(4):1-10.LIU M J.Studies on strake-wing aerodynamics and separated vortex[J].Journal of Beijing Institute of Aeronautics and Astronauitcs,1987,4(4):1-10(in Chinese).
[12]	LAMONT P J.Pressures around an inclined ogive cylinder with laminar,transitional,or turbulent separation[J].AIAA Journal,1982,20(11):1492-1499.
[13]	夏学湔,周丹杰,麻树林.前体边条控制技术应用[J].空气动力学学报,1997,15(1):54-58.XIA X J,ZHOU D J,MA S L.Application of forebody strake control technology[J].Acta Aerodynamic Sinica,1997,15(1):54-58(in Chinese).
[14]	HUNT B L.Asymmetric vortex forces and wakes on slender bodies[C]//9th Atmospheric Flight Mechanics Conference.Reston:AIAA,1982:1-41.
[15]	LORINCZ D J,FRIEND E L.Water tunnel visualization of the vortex flows of the F-15:AIAA-1979-1649[R].Reston:AIAA,1979.