基于回馈递推方法的导弹鲁棒飞行控制系统设计

首先将一种侧滑转弯导弹的非线性运动方程变换为适用于回馈递推方法的形式,其次利用回馈递推方法设计了导弹飞行控制器,系统的收敛性通过李亚普诺夫稳定性理论得到了严格的数学证明,然后针对作动器的位置、速率饱和对于系统性能的影响,采用非线性优化方法,避免了用通常回馈递推方法继续回推分析作动器动态过程的复杂性,得出了一种折衷考虑作动器动态特性、导弹飞行性能和鲁棒性的控制器。仿真表明了本方案的有效性。

A Robust Control Approach to Missile Autopilot Design Based on Backstepping

Firstly, the nonlinear dynamics model of a slide-to-turn (STT) missile is transformed to benefit from backstepping. Secondly, the autopilot controller is designed based on backstepping, and the astringency of the system is mathematically improved strictly by using lyapunov stability theorem. Afterwards, the influence of actuator position/velocity saturation on the autopilot system's stability is researched, and a nonlinear optimization solution considering the dynamics of the actuators is proposed, which can avoid the complexity of the backstepping process. By this way, a controller which makes compromise between actuator saturation and the missile's autopilot performance as well as robustness is proposed. Finally, the autopilot system's stability and robustness is verified by a great deal of simulation.