姿控导弹非线性稳定性的分叉分析

应用分叉理论研究了某姿控导弹非线性动力学系统的全局稳定性,给出了导弹动力学系统的数学模型,对导弹开环和闭环纵向稳定性进行了计算分析.沿某典型弹道对该导弹的全局非线性稳定性进行了分析和评估,给出了导弹能够稳定飞行的指令范围和平衡点及其稳定性随姿控指令的变化.研究结果表明,导弹闭环系统的稳定性是令人满意的,但在低空姿态角对舵偏角过于敏感,可能导致飞行中出现小幅振荡现象.

NONLINEAR STABILITY ANALYSIS OF AN ATTITUDE-CONTROLLED MISSILE USING BIFURCATION THEORY

The global stability of the nonlinear dynamics system of a certain attitude-controlled missile was studied with the bifurcation theory. The mathematical model of the missile dynamic system was set up. The open-loop and close-loop stabilities of the missile were analyzed. The global nonlinear stability of the missile was evaluated along a typical trajectory. The command regions, in which the missile can flight stably, and the variation of the equilibrium points and their stabilities with attitude control commands were obtained. The results indicate that the stability of the close-loop missile dynamic system is satisfying. At low altitude, the attitude angles are sensitive to control surface deflections, which may result in the small amplitude oscillation in flight.