直升机机身、平尾、垂尾的气动干扰

吕少杰; 曹义华; 肖阳

直升机机身、平尾、垂尾的气动干扰

1. 北京航空航天大学航空科学与工程学院, 北京 100191;
2. 总参陆航研究所机体发动机室, 北京 101114

详细信息

作者简介:
吕少杰（1983- ），男，山西朔州人，博士生，主要从事直升机飞行力学研究.

中图分类号: V212.4
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- 被引次数: 0
出版历程
- 收稿日期: 2013-03-09
- 刊出日期: 2014-05-28

Aerodynamic interaction of fuselage,horizontal stabilator and vertical stabilator of helicopter

1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. Department of Helicopter Airframe and Engine, Aviation Research Institute for the Headquarters of General Staff, Beijing 101114, China

摘要

摘要: 运用面元法模拟直升机机身流场，计算前飞状态的ROBIN（rotor body interaction）模型孤立机身顶部中线的压力系数分布，并与参考数据、CFD计算结果对比，验证了本方法的准确性.采用离散涡系模拟平尾、垂尾和短翼等升力面，以带短翼的UH-60直升机为例，研究了升力面参数变化对机身、平尾、垂尾气动干扰的影响.结果表明：改变升力面的安装角显著改变了气流对其周围的绕流情况，在参数中影响最大；平尾参数尤其是安装角会对垂尾和短翼的压力系数产生较大影响；减小垂尾展长和增大短翼安装角会提升各自的压力系数.
- 气动干扰 /
- 直升机 /
- 平尾 /
- 垂尾 /
- 涡格法 /
- 面元法
Abstract: The panel method was used to simulate the helicopter fuselage flowfield.For the isolated fuselage of rotor body interaction (ROBIN) model,the pressure coefficient distribution along the top centerline was calculated in forward flight.The computational results were compared with the referenced data and computational fluid dynamics(CFD) results,validating accuracy of the methodology.Discrete vortices system was used to simulate the lifting surfaces,including horizontal stabilator,vertical stabilator and short wing.Aerodynamic interaction of fuselage,horizontal stabilator and vertical stabilator of UH-60 helicopter with short wing was computed and analyzed when the lifting surface parameters were adjusted.The results indicate that,change of the installation angle will have significant influence on the airflow around the lifting surface as the greatest influential parameter.Horizontal stabilator parameters,in particular the installation angle,can yield evident impact on the pressure coefficient of vertical stabilator and short wing,while decrease of the vertical stabilator span and increase of short wing installation angle can respectively increase their own pressure coefficient.
- aerodynamic interaction /
- helicopter /
- horizontal stabilator /
- vertical stabilator /
- vortex lattice method /
- panel method

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参考文献(16)

[1]	CAO Yihua, YUAN Kungang, LI Xiaoyong.Computational methods for simulation of flow around helicopter engine inlet[J].Journal of Aircraft, 2006, 43(1):141-146.
[2]	CAO Yihua, SU Yuan.Insight into the effects of rotor downwash on engine jet[J].Aircraft Engineering and Aerospace Technology, 2003, 75(4):345-349.
[3]	胡利, 曹义华, 赵明.直升机旋翼机身发动机耦合流场数值模拟[J].航空动力学报, 2008, 23(10):1882-1887. HU Li, CAO Yihua, ZHAO Ming.Numerical simulation of helicopter rotor-fuselage-engine aerodynamic interactions[J].Journal of Aerospace Power, 2008, 23(10):1882-1887.(in Chinese)
[4]	Markus D, Manuel K, Ewald K, et al.Tip vortex conservation on a helicopter main rotor using vortex-adapted chimera grids[J].AIAA Journal, 2007, 45(8):2062-2074.
[5]	ZHAO Ming, CAO Yihua.Numerical simulation of rotor flow field on several spatial discretisation schemes[J].Chinese Journal of Aeronautics, 2012, 25(2):155-163.
[6]	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, 1981.
[7]	沈银初.直升机机身流场计算[D].北京:北京航空航天大学, 1994. SHEN Yingchu.Calculation of helicopter fuselage flowfield[D].Beijing:Beijing University of Aeronautics and Astronautics, 1994.(in Chinese)
[8]	赵景根.直升机旋翼/机身气动干扰的研究[D].南京:南京航空航天大学, 2000. ZHAO Jinggen.Study of helicopter rotor/body aerodynamic interaction[D].Nanjing:Nanjing University of Aeronautics and Astronautics, 2000.(in Chinese)
[9]	Hess J L, Smith A M O.Calculation of non-lifting potential flow about arbitrary three-dimensional bodies[J].Journal of Ship Research, 1963, 8(2):22-44.
[10]	Freeman C E, Mineck R E.Fuselage surface pressure measurements of a helicopter wind-tunnel model with a 3.15-meter diameter single rotor[R].NASA-TM-80051, 1979.
[11]	Bettschart N.Rotor fuselage interaction:Euler and Navier-Stokes computations with an actuator disk[R].Montreal, Canada:American Helicopter Society 55th Annual Forum, 1999.
[12]	CAO Yihua, ZHAO Ming, HU Li.Numerical simulation of rotor-fuselage-cylinder interaction in forward flight[J].Journal of Aircraft, 2010, 47(4):1426-1430.
[13]	Leishman J G.Principles of helicopter aerodynamics[M].2nd ed.New York:Cambridge University Press, 2006.
[14]	Bagai A, Leishman J G.Rotor free wake modeling using a pseudo implicit technique:including comparisons with experimental data[J].Journal of the American Helicopter Society, 1995, 40(3):29-41.
[15]	钱翼稷.空气动力学[M].北京:北京航空航天大学出版社, 2005.
[16]	Hilbert K B.A mathematical model of UH-60 helicopter[R].NASA-TM-85890, 1984.