摘要
基于描述函数法，对操纵系统的结构非线性问题，提出了用于描述函数法的耦合模态和非耦合模态的综合计算模型．使用跨音速非定常空气动力，对扑动间隙和旋转间隙进行研究．揭示了全动水平尾翼振动的根源主要是操纵间隙造成的，为其它同类问题提供了可行的工程分析方法．
An integration model of coupled and uncoupled mode, which is used for describing function technique in dealing with structural nonlinearities in control systems, has been presented in this paper. Flapping and rotary gap have been investigated with the help of transonic unsteady aerodynamic forces. The results show that oscillation of all-movable stabilizer are mainly caused by control gaps. The engineering analysis method presented in the paper canalso be used for other similar problems.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
1994年第4期357-361,共5页
Journal of Beijing University of Aeronautics and Astronautics
关键词
振动分析
非线性分析
飞机
尾翼
扑动间隙
flutter analysis
non-linear systems
aircraft systems
tail surfaces
flapping gap
rotary gap
