摘要
操纵面间隙会引起结构非线性,容易诱发极限环颤振。根据设计需要,考虑操纵面中心间隙的影响,采用最小状态拟合技术对频域非定常气动力进行有理函数拟合,采用分段函数描述间隙引起的非线性刚度,研究操纵面在间隙作用下的极限环颤振响应的行为特点。结果表明,由于中心间隙的影响,系统会在低于线性颤振速度时就产生极限环振荡,同时,振荡幅值随飞行速度或中心间隙的增大而增大。
The freeplay of the control surfaces is a cause of the structural nonlinearity,which will easily lead to the limit cycle flutter.According to the design requirements,considering the center freeplay of the control surface,rational function approximations of the unsteady aerodynamics in the frequency-domain are constructed based on the Minimum-State Approximation Formula,with the nonlinear stiffness caused by the center freeplay being described by the subsection function.Then the nonlinear response characteristics and the behaviors of the limit cycle flutter due to the freeplay on the control surface are studied.Results show that due to the influence of the central freeplay in the nonlinear system,the limit cycle oscillation is produced below the linearflutter speed,and the limit cycle amplitude increases with the increase of the flight speed or the center gap.
作者
吕继航
罗琳胤
Lü Jihang;LUO Linyin(Research and Development Centre,China Aviation General Aircraft Institute,Zhuhai 519040,Guangdong,China;Science and Technology Committee,China Aviation General Aircraft Institute,Zhuhai 519040,Guangdong,China)
出处
《力学与实践》
北大核心
2020年第4期418-423,共6页
Mechanics in Engineering
基金
工信部民机研制项目(MJ-2017-F-**)资助。
关键词
操纵面
中心间隙
非线性刚度
极限环颤振
control surface
central freeplay
nonlinear stiffness
limit cycle flutter
