基于自由尾迹/面元法的旋翼下洗干扰计算和直升机配平

吕少杰; 魏靖彪; 曹义华

doi:10.13700/j.bh.1001-5965.2014.0680

基于自由尾迹/面元法的旋翼下洗干扰计算和直升机配平

doi: 10.13700/j.bh.1001-5965.2014.0680

1.
总参谋部陆航研究所, 北京 101121
2. 北京航空航天大学航空科学与工程学院, 北京 100191

详细信息

通讯作者:
吕少杰(1983—),男,山西朔州人,工程师,aili-008@163.com,主要研究方向为直升机飞行力学.

中图分类号: V212.4
计量
- 文章访问数: 1290
- HTML全文浏览量: 124
- PDF下载量: 12693
- 被引次数: 0
出版历程
- 收稿日期: 2014-11-02
- 网络出版日期: 2015-09-20

Rotor downwash interference calculation and helicopter trims with free-wake/panel method

1.
Army Aviation Research Institute for the Headquarters of General Staff, Beijing 101121, China
2. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 基于自由尾迹/面元法的耦合方法,建立了一种旋翼气动干扰模型和直升机配平计算模型.采用自由尾迹方法和升力面理论计算旋翼尾流带来的气动干扰,使用三维面元模型代替机身,采用涡镜像法模拟机身对尾迹的诱导和堵塞.以UH-60A直升机为算例,基于耦合方法,分别计算了旋翼尾迹形状以及尾迹对机身、平尾和尾桨的下洗速度,并与风洞试验结果对比.最后将自由尾迹/面元耦合法与直升机飞行力学模型嵌套,完成了配平计算,并与试飞结果和涡粒子模型计算结果进行了对比,结果的一致性证明了本方法的有效性.
- 自由尾迹 /
- 面元法 /
- 气动干扰 /
- 飞行力学 /
- 配平
Abstract: A coupled free-wake/panel method to predict the rotor downwash aerodynamic interaction and helicopter trims is presented. Based on lifting-surface theory, free-wake method was developed to analyze aerodynamics interference of rotor wake. A three dimensional panel model was applied to represent the fuselage, the vortex line mirror method was adopted to account for the induced and obstructed effects of the fuselage on the rotor wake. Based the coupled method, the rotor wake geometry and rotor downwash velocity on fuselage, horizontal stabilator and tail rotor of UH-60A helicopter were investigated including comparisons with the wind tunnel measured data. Combined with the helicopter flight dynamic model, the coupled method was embedded in the trim procedure and applied to trim. Comparisons among predictions, vortex particle model results and flight test results were for the control stick positions and attitude angles, coincidence of the results validated accuracy of the present methodology.
- free-wake /
- panel method /
- aerodynamic interference /
- flight dynamic /
- trim

HTML全文

参考文献(20)

[1]	Johnson W.Wake model for helicopters in high speed light,NASA Report 177507[R].California:NASA,1988.
[2]	Komerath N M,Smith M J,Tung C.A review of rotor wake physics and modeling[J].Journal of the American Helicopter Society,2010,56(2):1-19.
[3]	Bhagwat M J,Leishman J G.Stability consistency and convergence of time-marching free-vortex rotor wake algorithms[J].Journal of the American Helicopter Society,2001,46(1):59-71.
[4]	Strawn R C,Caradonnna F X,Duque E P N.30 years rotorcraft computational fluid dynamics research and development[J].Journal of the American Helicopter Society,2006,51(1):5-21.
[5]	冯德利,招启军,徐国华.基于CFD方法的直升机前飞状态配平分析[J].航空学报,2013,34(10):2256-2264.Feng D L,Zhao Q J,Xu G H.Trim analysis of helicopter in forward flight based on CFD method[J].Acta Aeronautica et Astronautica Sinica,2013,34(10):2256-2264(in Chinese).
[6]	Zhao J,He G.Modeling rotor wake dynamic with viscous vortex particle method[J].AIAA Journal,2009,47(4):902-915.
[7]	Cheng H,Greengard L,Rokhlin L.A fast adaptive multipole algorithm in three dimensions[J].Journal of Computational Physics,1999,155(2):468-498.
[8]	Bi N,Leishman J G.Experimental study of rotor/body aerodynamic interactions[J].Journal of Aircraft,1990,27(9):779-788.
[9]	Tan J F,Wang H W.Panel/full-span free-wake coupled method for unsteady aerodynamics of helicopter rotor blade[J].Chinese Journal of Aeronautics,2013,26(3):535-543.
[10]	Richason T F,Katz J.Unsteady panel method for flows with multiple bodies moving along various paths[J].AIAA Journal,1994,32(1):62-68.
[11]	吕少杰,曹义华,肖阳.直升机机身、平尾、垂尾的气动干扰[J].航空动力学报,29(5):1122-1127. Lyu S J,Cao Y H,Xiao Y.Aerodynamic interaction of fuselage,horizontal stabilator and vertical stabilator of helicopter[J].Journal of Aerospace Power,2014,29(5):1122-1127(in Chinese).
[12]	徐华舫,朱自强.亚、超音速定常位流的面元法[M].北京:国防工业出版社,198l:20,180.Xu H F,Zhu Z Q.Subsonic unsteady potential flow panel method[M].Beijing:National Defense Industry Press,1981:20,180(in Chinese).
[13]	Leishman J G.Rotor blade system with reduced blade-vortex interaction noise:USA,6948906[P].2005-09-27.
[14]	Leishman J G,Principles of helicopter aerodynamics[M].2nd ed.Cambridge:Cambridge University Press,2006:598-601.
[15]	Bagai A.Contributions to the mathematical modeling of rotor flow fields using a pseudo implicit free wake analysis[D].Maryland:University of Maryland,1995.
[16]	Crouse G L,Leishman J G,Bi N.Theoretical and experimental study of unsteady rotor/body aerodynamic interactions[J].Journal of the American Helicopter Society,1992,37(1):55-65.
[17]	谭剑锋,王浩文.直升机旋翼/机身非定常气动干扰数值分析[J].空气动力学学报,2014,32(3):320-327.Tan J F,Wang H W.Numerical analysis of helicopter rotor/fuselage unsteady aerodynamic interaction[J].ACTA Aerodynamica Sinica,2014,32(3):320-327(in Chinese).
[18]	Hilbert K B.A mathematical model of UH-60 helicopter,NASA Report TM85890[R].California:NASA,1984.
[19]	Cao Y H,Li G Z,Hess R A.Helicopter flight characteristics in icing conditions[J].The Aeronautical Journal,2012,116:963-979.
[20]	Zhao J,He G.A viscous vortex particle model for rotor wake and interference analysis[J].Journal of the American Helicopter Society,2010,55(1):1-14.