直升机非线性的稳定性分析

建立了直升机的描述函数,分析和研究了非线性条件下直升机稳定性和极限环振荡情况,导出了极限环振荡情况下纵向操纵位移计算公式和稳定裕度计算公式,并根据Z—8飞机飞行试验数据进行了验证计算和误差分折。计算结果表明,本文的方法可用于各种直升机的设计估算和飞行试验数据处理,是一种非线性闭环分析方法。

THE STUDY OF HELICOPTER STABILITY UNDER THE NONLINEAR CONDIT ION

This paper analyses and studies helicopter stability and limit loop oscillation under nonlinear condition by establishing describe function, the computation formula for longitudinal control displacement and stability store have been derived with limit loop oscillation, the computation and error analyses have been made from Z-8 flight test data. The results show that the technique in this paper suitable to any helicopter flight test data handle arid design estimate. it is a nonlinear closed loop analyses technique.