螺旋桨/大柔性机翼静气动弹性快速分析方法

谢长川; 张利娟; 刘燚; 杨超

doi:10.13700/j.bh.1001-5965.2014.0025

螺旋桨/大柔性机翼静气动弹性快速分析方法

doi: 10.13700/j.bh.1001-5965.2014.0025

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:
谢长川(1976-),男,陕西西安人,讲师,xiechangc@163.com,主要研究方向为气动弹性.

中图分类号: V224;TB553
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出版历程
- 收稿日期: 2014-01-15
- 网络出版日期: 2015-01-20

Aeroelasticity quick analysis method of very propeller/flexible wing system

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 旋转的螺旋桨滑流掠过机翼将使机翼的气动特性发生改变,在高空超长航时无人机的设计中有必要对大柔性机翼气动弹性问题的螺旋桨滑流影响进行分析.运用Prandtl修正的动量叶素理论分析螺旋桨滑流及面内载荷;采用兰金涡核模拟滑流对机翼的诱导速度;采用三维升力线方法计算机翼定常气动力,利用曲面样条插值方法解决结构/气动耦合问题,并结合非线性有限元静力学计算方法,建立了螺旋桨滑流及面内载荷作用下大柔性机翼静气动弹性问题的快速迭代求解方法.以某大展弦比螺旋桨机翼为例,采用文中所建立方法对其静气动弹性特性进行计算研究.结果表明,旋转的滑流改变了机翼绕流当地攻角,从而影响了机翼气动力和变形分布,且在小前进比时影响更大.所建立的分析方法简便高效,在初步设计阶段有较好的应用前景翼绕流当地攻角,从而影响了机翼气动力和变形分布,且在小前进比时影响更大.所建立的分析方法简便高效,在初步设计阶段有较好的应用前景.
- 螺旋桨 /
- 柔性机翼 /
- 滑流 /
- 前进比 /
- 静气动弹性
Abstract: The propeller's revolving slipstream passing wing changes the drag/lift property of the wing. For the hyper long endurance unmanned flight vehicles design, the slipstream effect should be analyzed for the aeroelasticity of the very flexible wing. The Prandtl revised blade element-momentum theory was applied to calculate the aerodynamic parameters and in-plane loads (1P loads) of the slipstream. Then a Rankine vortex core was placed along the propeller's installation axis to simulate slipstream's induced effect on the wing. Further, the 3-D lifting-line method was utilized to calculate the steady aerodynamic loads of the curved bending wing. And the generalized surface splines and large deflection interpolation method were adopted to solve the geometrical characters of structure/aerodynamic coupling problem. Coupling with the nonlinear finite element method of the structure, the iterative approach was constructed for the solving of propeller's slipstream, 1P loads and the static aeroelasticity of very flexible wing. Finally, a validation study of a very flexible rectangular wing with one propeller was carried out using the method constructed. The numerical results show that the revolving slipstream changed the local incidence angle of a wing, thus changing the aerodynamic forces and deformation distribution. And in the small advance ratios situation, it has greater influences. The results demonstrate the applicability of this method in early stages of aircraft design.
- propeller /
- flexible wing /
- slipstream /
- advance ratio /
- static elasticity

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参考文献(19)

[1]	谢长川,杨超.大展弦比飞机的几何非线性气弹问题[C]//第七届全国空气弹性学术交流会论文集.北京:中国空气动力学会,2001:97-102.Xie C C,Yang C.Geometric nonlinear static aeroelasticity problems of high-aspect-ratio planes[C]//7th National Conference on Aeroelastic Academic Communication.Beijing:Aerodynamic Society of China,2001:97-102(in Chinese).
[2]	Patil M J,Hodges D H.On the importance of aerodynamic and structural nonlinearities in aeroelastic behavior of high-aspect-ratio wings,AIAA-2000-1448[R].Altanta:AIAA,2000.
[3]	Patil M J,Hodges D H,Cesnik C E S,et al.Limit cycle oscillations in high-aspect-ratio wings[C]//40th Structures Structural Dynamics,and Materials Conferernce and Exhibit.St.Louis:AIAA,1999,3:2184-2194.
[4]	Patil M J,Hodges D H,Cesnik C E S.Characterizing the effects of geometrical nonlinearities on aeroelastic behavior of high-aspect-ratio wings[C]//International Forum on Aeroelasticity and Structural Dynamics.Williamsburg,VA:[s.n.],1999:501-510.
[5]	谢长川.飞行器气动弹性稳定性静/动耦合理论与试验研究[D].北京:北京航空航天大学,2009.Xie C C.Static/dynamic coupling theory and test study of aircraft aeroelastic stability[D].Beijing:Beihang University,2009(in Chinese).
[6]	Xie C C,Leng J Z,Yang C.Geometrical nonlinear aeroelastic stability analysis of a composite high-aspect-ratio wing[J].Shock and Vibration,2008,15(3-4):325-333.
[7]	刘燚,谢长川.大展弦比机翼的几何非线性静气动弹性分析方法[C]//第十二届全国空气弹性学术交流会会议论文集.北京:中国空气动力学会,2011:227-233.Liu Y,Xie C C.Anlysis method for geometric nonlinear static aeroelasticity of high-aspect-ratio wings[C]//12th National Conference on Aeroelastic Academic Communication.Beijing:Aerodynamic Society of China,2011:227-233(in Chinese).
[8]	Palacios R,Cesnik C E S.Nonlinear aeroelastic modeling and experiments of flexible wings,AIAA-2006-2186[R].Newport:AIAA,2006.
[9]	刘沛清.空气螺旋桨理论及其应用[M].北京:北京航空航天大学出版社,2006:56-63.Liu P Q.Air propeller theory and application[M].Beijing:Beihang University Press,2006:56-63(in Chinese).
[10]	Weir D S.Wing loads induced by a propeller wake,AIAA-86-1967[R].Seattle:AIAA,1986.
[11]	Agostinelli C,Liu C H,Allen C B,et al.Propeller-flexible wing interaction using rapid computational methods,AIAA-2013-2418[R].San Diego:AIAA,2013.
[12]	段中喆,刘沛清,屈秋林.某轻载螺旋桨滑流区三维流场特性数值研究[J].控制工程,2012,19(5):836-841.Duan Z Z,Liu P Q,Qu Q L.Numerical research on 3-D flow field characteristics within the slipstream of a low loaded propeller[J].Control Engineering of China,2012,19(5):836-841(in Chinese).
[13]	鄂秦,杨国伟,李凤蔚,等.螺旋桨滑流对飞机气动特性影响的数值分析[J].西北工业大学学报,1997,15(4):511-516.E Q,Yang G W.Li F W,et al.On coupling effect of two vortex systems of Chinese aircraft with turbo-propellers[J].Journal of Northwestern Polytechnical University,1997,15(4):511-516(in Chinese).
[14]	左岁寒,杨永.螺旋桨滑流对带后缘襟翼机翼气动特性影响的数值分析[J].航空计算技术,2007,17(1):54-57.Zuo S H,Yang Y.Numercal simulation of propeller/high-lift system interaction[J].Aeronautical Computing Technique,2007,17(1):54-57(in Chinese).
[15]	段义乾,史爱明.一种新型的螺旋桨滑流激励盘模型的研究方法[J].西北工业大学学报,2012,30(6):841-846.Duan Y Q,Shi A M.A new and effective actuator disk model approach for the simulation of propeller slipstream[J].Journal of Northwestern Polytechnical University,2012,30(6):841-846(in Chinese).
[16]	Kroo I.Propeller-wing integration for minimum induced loss[J].Journal of Aircraft,1986,23(7):561-565.
[17]	Ortun B,Boisard R.In-plane airloads of a propeller with inflow angle:prediction vs experiment,AIAA-2012-2778[R].New Orleans:AIAA,2012.
[18]	黄国伟.非定常漩涡空气东流额理论及应用[M].上海:上海交通大学出版社,1994:56-61.Huang G W.Unsteady vortex aerodynamics theory and application[M].Shanghai:Shanghai Jiao Tong Unversity Press,1994:56-61(in Chinese).
[19]	Xie C C.Theoretic analysis and experiment on aeroelasticity of very flexible wing[J].Science China,2012,55(9):2489-2500