鸭式旋翼/机翼飞行器转换末段气动特性

李毅波; 马东立; 牛凌宇

鸭式旋翼/机翼飞行器转换末段气动特性

1.
北京航空航天大学[KG*2]航空科学与工程学院, 北京 100191
2. 北京系统工程研究所, 北京 100101

基金项目: 武器装备预研重点基金资助项目(9140A25010208HK0101)

详细信息

作者简介:
李毅波(1983-),男,湖南娄底人,博士生,liyibo1983@tom.com.

中图分类号: V 275⁺.3
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- 被引次数: 0
出版历程
- 收稿日期: 2010-07-14
- 网络出版日期: 2011-03-31

Aerodynamic characteristic of canard rotor/wing aircraft in conversion

1.
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2. Beijing System Engineering Institute, Beijing 100101, China

摘要

摘要: 采用数值模拟方法研究鸭式旋翼/机翼(CRW,Canard Rotor/Wing)飞行器在转换过程末段,旋翼转速极低时全机气动特性变化规律及其产生原因.给出了旋翼旋转一周时,全机气动力、气动力矩、焦点位置变化规律,对此布局形式,转换过程末段全机升力、阻力变化幅度可达10.7%,3.7%,焦点可移动0.6 m.研究显示:旋翼处于前后不对称流场及旋翼处于不同方位角时对机体的不对称干扰是气动力与气动力矩变化原因,旋翼与平尾升力线斜率变化、旋翼自身焦点位置变化导致了全机焦点移动.
- 鸭式旋翼/机翼飞行器 /
- 气动特性 /
- 流场干扰 /
- 飞行模式转换
Abstract: The aerodynamic characteristics and mechanism of canard rotor/wing(CRW) aircraft during conversion from rotary to fixed-wing flight was numerically investigated. The variation of forces, moments and aerodynamic center with respect to rotor position are presented, the amplitude of lift, drag and aerodynamic center for this configuration in conversion can reach 10.7%, 3.7% and 0.6 m separately. The investigation shows that the cause of forces and moments variation is the asymmetry flow field in rotary plane and asymmetry interference between rotor and fuselage, the motion of aerodynamic center can be explained by the motion of rotor aerodynamic center and the variation of lift curve slope of rotor and horizontal tail.
- canard rotor/wing(CRW) aircraft /
- aerodynamic characteristic /
- flow interference /
- flight mode conversion

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参考文献(1)

[1] Mitchell C A,Vogel B J.The canard rotor wing(CRW)aircraft:a new way to fly .AIAA 2003-2517,2003 [2] Kim C,Lee J.Hub drag-reduction strategies of canard rotor/wing unmanned aerial vehicles[J].Journal of Aircraft,2007,44(4):1388-1391 [3] Lee J W,Jeon K S,Kim M,et al.Rotor design for the performance optimization of canard rotor/wing aircraft[J].Lecture Notes in Computer Science,2006,3984:932-941 [4] 曹旭,詹浩,邓阳平.尖部喷气驱动旋转机翼地面试验装置的研制[J].实验流体力学,2007,21(2):89-92 Cao Xu,Zhan Hao,Deng Yangping.Development of experimental equipment for reaction driving rotor wing[J].Journal of Experiments in Fluid Mechanics,2007,21(2):89-92(in Chinese) [5] 詹浩,邓阳平,高正红.椭圆翼型低速气动特性研究[J].航空计算技术,2008,38(3):25-27 Zhan Hao,Deng Yangping,Gao Zhenghong.Investigation on aerodynamics performance of elliptic airfoil at low speed[J].Aeronautical Computing Technique,2008,38(3):25-27(in Chinese) [6] Pandya S A,Aftosmis M J.Computation of external aerodynamics for a canard rotor/wing aircraft .AIAA 2001-0997,2001 [7] 陆志良.空气动力学[M].北京:北京航空航天大学出版社,2009:256-260 Lu Zhiliang.Aerodynamics[M].Beijing:Beijing University of Aeronautics and Astronautics Press,2009:256-260(in Chinese) [8] 朱自强,吴子牛,李津,等.应用计算流体力学[M].北京:北京航空航天出版社,1998:136-137 Zhu Ziqiang,Wu Ziniu,Li Jin,et al.Application of computational fluid dynamics[M].Beijing:Beijing University of Aeronautics and Astronautics Press,1998:136-137(in Chinese)

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