摘要
由于折叠机构间隙的存在,折叠翼的刚度特性呈非线性关系特性,工程实践中需要有效的方法,建立并求解折叠翼的非线性气动弹性方程。该文提出了弦向多个自由度具有结构非线性刚度的折叠翼颤振分析方法,并对典型折叠翼面进行了非线性颤振分析。利用动态子结构方法建立了非线性气动弹性方程,分别在频域和时域给出了颤振求解方法。对比工程软件的计算结果,验证了该方法是否满足工程计算精度的要求。通过对典型折叠翼的计算得到以下结论。在弦向多个位置具有初载间隙型非线性的典型折叠翼结构在一定速度范围内会产生稳定的极限环振荡,在一定速度范围内结构响应与初始扰动相关,后缘铰链振动相比于前缘更加剧烈,初载角较大时振荡更加剧烈。
The stiffness characteristics of the folding wing will change dramatically due to the clearance.The analysis method of a folding-wing with structural nonlinearity is needed in the folding wing design process.In this paper,a method for analyzing aeroelastic properties of the folding wing with concentrated structural nonlinearity is investigated.A component mode substitution method is used to derive the full structural equations which are solved in frequency-domain and time-domain respectively.Via comparing with results calculated by the engineering software,the method is proved whether it is precise or not.Through the analysis of a typical folding wing,the results show that the stable LCO is generated in the folding wing with pre-load free-play.Under a few velocities,the responses of the structure are related to the initial disturbance.The vibration of posterior hinge is severer than others.When the pre-load angle is increased,the amplitude of vibration is increased.
出处
《工程力学》
EI
CSCD
北大核心
2012年第2期197-204,共8页
Engineering Mechanics
基金
国家自然科学基金项目(90716006
10902006)
关键词
折叠翼
气动弹性
颤振
动态子结构
描述函数
结构非线性
间隙刚度
folding wing
aeroelasticity
flutter
component mode substitution method
describing function
structural nonlinearity
free-play spring-gap
