| 带有气动及结构非线性的二元机翼颤振分析 |
| |
| 引用本文： | 王益锋,邵松,朱清华,张呈林.带有气动及结构非线性的二元机翼颤振分析[J].航空动力学报,2012,27(9):2063-2074. |
| |
| 作者姓名： | 王益锋 邵松 朱清华 张呈林 |
| |
| 作者单位： | 1. 中国商用飞机有限责任公司上海飞机设计研究院强度设计研究部,上海,200232
2. 南京航空航天大学航空宇航学院直升机旋翼动力学重点实验室,南京,210016 |
| |
| 基金项目： | 航空科学基金(20115752035); 直升机旋翼动力学重点实验室基金(9140C400101120) |
| |
| 摘 要： | 研究了翼型在低马赫数条件下的非定常气动特性,从翼型表面气流运动的角度对Leishman-Beddoes（L-B）模型进行了修正,并在此基础上建立了适合低马赫数颤振研究且带有气动及结构非线性的二元机翼气弹系统分析模型.对比低马赫数翼型气动载荷试验结果表明对L-B模型的修正是有效的,且机翼颤振试验结果亦验证了二元机翼气弹分析模型.研究结果表明：二元机翼气弹系统的失速颤振与初始变距角和来流速度密切相关,且耦合的三次非线性变距和浮沉刚度是造成系统呈现准周期运动的主要原因.
|
| 关 键 词： | 颤振 动态失速 低马赫数 结构非线性 分岔 |
| 收稿时间： | 2011/12/9 0:00:00 |
Flutter analysis of a two-dimensional wing with aerodynamic and structural nonlinearity |
| |
| WANG Yi-feng,SHAO Song,ZHU Qing-hua and ZHANG Cheng-lin.Flutter analysis of a two-dimensional wing with aerodynamic and structural nonlinearity[J].Journal of Aerospace Power,2012,27(9):2063-2074. |
| |
| Authors: | WANG Yi-feng SHAO Song ZHU Qing-hua and ZHANG Cheng-lin |
| |
| Institution: | Stress Department, Shanghai Aircraft Design and Research Institute, Commercial Aircraft Corporation of China Limited, Shanghai 20023;Science and Technology on Rotorcraft Aeromechanics Laboratory, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Science and Technology on Rotorcraft Aeromechanics Laboratory, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Science and Technology on Rotorcraft Aeromechanics Laboratory, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
| |
| Abstract: | The unsteady and dynamic stall aerodynamic behavior of airfoil at low Mach number was investigated,and the modified Leishman-Beddoes (L-B) model was modeled from the viewpoint of the convection of the flow on the airfoil surface.Based on the modified L-B model,the flutter analysis model of a two-dimensional wing with aerodynamic and structural nonlinearity at low Mach number was presented.The modification to L-B is effective by comparing with experimental airfoil airload results,and the wing flutter experimental results also verify the analysis model of the two-dimensional wing aeroelastic system.Results demonstrates that the stall flutter of airfoil aeroelastic system is closely related to the initial pitch angle and the inflow velocity,and the quasi-periodical oscillation motion of the two-dimensional wing aeroelastic system mainly caused by the coupled cubic nonlinear stiffness in pitch and plunge. |
| |
| Keywords: | flutter dynamic stall low Mach number structural nonlinearity bifurcation |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
| 点击此处可从《航空动力学报》下载免费的PDF全文 |
|
