摘要
为了有效地抑制和消除某飞机纵向DBW中非线性引起的自持振荡,在控制律设计中采取了降低系统开环增益、引入相位超前滤波、设置条件反馈校正和限制振荡幅值等措施。本文利用描述函数法,重点分析了条件反馈校正对自持振荡的抑制作用。
In order to restrain effectively and to eliminate the self-sustaining oscillation caused by nonlinearity in longitudinal DFBW of an aircraft, adopted several methods in design of control law:reduced open loop gain, adding phase lead filter, conditional feedback correction and limited amplitude of oscillation. Using the describing function method, this paper gives emphasis to analyse the conditional feedback correction effect on restrain self-sustaining oscillation.
出处
《飞行力学》
CSCD
北大核心
1989年第4期53-63,共11页
Flight Dynamics
