大展弦比柔性机翼非线性颤振研究
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摘要
使用非线性ONERA气动模型对大展弦比柔性机翼进行颤振分析,将变形后的柔性机翼视为曲梁。基于曲梁的运动微分方程,结合非线性ONERA模型,建立了大展弦比柔性机翼的颤振分析模型。运用传递函数方法,将颤振微分方程转换为状态空间方程形式,通过求解复特征值问题,获得了大展弦比柔性机翼在非线性气动力作用下的颤振速度和颤振频率,得出了机翼线密度、展弦比、抗弯刚度和抗扭刚等因素影响下不同气动模型的颤振结果的差异。
The nonlinear flutter problem of a high-aspect-ratio very flexible aircraft wing was researched by nonlinear ONERA aerodynamic model. The deformed flexible wing was regarded as a curved beam. Based on differential equations of motion curved beams,the nonlinear flutter analysis model of large flexible wing with high-aspect-ratio was established by combining nonlinear unsteady ONERA aerodynamic model. The flutter differential equations were transformed into the state space equations by the transfer function method. Both the flutter velocity and flutter frequency of large flexible wing with high-aspect-ratio under the action of nonlinear aerodynamic force were obtained by solving a complex eigenvalue problem. The effects of wing linear density,aspect-ratio,bending stiffness and torsional stiffness on flutter characteristics were discussed.
The nonlinear flutter problem of a high-aspect-ratio very flexible aircraft wing was researched by nonlinear ONERA aerodynamic model. The deformed flexible wing was regarded as a curved beam. Based on differential equations of motion curved beams,the nonlinear flutter analysis model of large flexible wing with high-aspect-ratio was established by combining nonlinear unsteady ONERA aerodynamic model. The flutter differential equations were transformed into the state space equations by the transfer function method. Both the flutter velocity and flutter frequency of large flexible wing with high-aspect-ratio under the action of nonlinear aerodynamic force were obtained by solving a complex eigenvalue problem. The effects of wing linear density,aspect-ratio,bending stiffness and torsional stiffness on flutter characteristics were discussed.
引文
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[2]伍星,卢永刚,宋琼,等.基于Fluent的弹体气动特性计算与分析[J].兵器装备工程学报,2016,37(2):22-25.
[3]雷勇军.结构分析的分布参数传递函数方法[D].长沙:国防科学技术大学,1998.
[4] XIEC C,LENG J Z,YANG C. Geometrical Nonlinear Aeroelastic Stability Analysis of a Composite High-Aspect-Ratio Wing[J]. Shock&Vibration,2013,15(3/4):325-333.
[5] CESNIK C,SENATORE P,SU W,et al. X-HALE:A very flexible UAV for nonlinear aeroelastic tests[J]. Aiaa/asme/asce/Ahs/asc Structures,Structural Dynamics,&Materials Conference,2006.
[6] TANG D,GRASCH A,DOWELL E H. Gust Response for Flexibly Suspended High-Aspect Ratio Wings[J]. Aiaa Journal,2010,48(10):2430-2444.
[7] PATIL M J,HODGES D HCESNIK C. Nonlinear Aeroelasticity and Flight Dynamics of High-Altitude Long-Endurance Aircraft[J]. Journal of Aircraft,2012,38(1):88-94.
[8] SMITH M,PATIL M,HODGES D. CFD-based analysis of nonlinear aeroelastic behavior of high-aspect ratio wings.Structures[J]. Structural Dynamics&Materials Conference,2013.
[9]赵雪健.平面曲梁自由振动的动力刚度法研究[D].北京:清华大学,2010.
[10]赵永辉.气动弹性力学与控制[M].北京:科学出版社,2006.