带章动阻尼器航天器的非线性动力学分析

Nonlinear dynamics analysis of aircraft with nutational damper

研究带章动阻尼器航天器的非线性动力学特性.应用第二类拉格朗日方法建立航天器动力学方程,并对稳定性进行了分析;应用四阶Runge-Kutta法进行数值模拟,发现激励力矩增大时系统由倍周期运动变为混沌运动.

The nonlinear dynamics of the aircraft with nutational damper is investigated.The dynamics equations of the model are established by the second Lagrange＇s equations and the stability analysis is given;The numerical simulation of fourth-order Runge-Kutta method indicates that the onset of chaotic motion was characterised by period doubling when the external torque increases.