飞行器最优末制导律的自适应PID滑模设计  

Adaptive PID Sliding Mode Control Design for Vehicle Terminal Optimal Guidance Law

作　　者：范金锁[1] 张合新[1] 孟飞[1] 吕永佳[2] 

机构地区：[1]第二炮兵工程学院自动化系 [2]中国人民解放军96612部队

出　　处：《宇航学报》2012年第9期1225-1232,共8页Journal of Astronautics

摘　　要：针对传统最优末制导律作用下再入飞行器易受外界因素干扰和气动力变化的影响,致使命中精度较低、鲁棒性较差的问题,在弹目运动方程存在参数不确定性情况下,提出一种基于自适应PID滑模扰动观测器技术的鲁棒最优末制导律。其中滑模扰动观测器能够在线消除系统扰动影响,而自适应PID滑模可以有效去除抖振。基于Lyapunov稳定性理论的证明过程及数值仿真结果均表明,该末制导律不仅使飞行器各项性能指标均达到指标要求,并且保证了较高的命中精度和较强的鲁棒性。Under the circumstance of the relative motion equation with parameter uncertainties, a new robust optimal terminal guidance law based on adaptive PID sliding mode control perturbation estimator is proposed for the problems existing in traditional optimal guidance law such as poor robustness and low impact accuracy induced by external disturbance and varying aerodynamic force. The sliding mode control perturbation estimator （SMCPE） is used to online eliminate the influence of perturbation, while the adaptive PID sliding mode control is used to remove chatting. The theoretic proof based on Lyapunov theorem stability and simulation results show that a demand-satisfied performance index, high impact accuracy and stronger robustness is ensured.

关 键 词：最优末制导律 滑模扰动观测器 自适应PID 强鲁棒性 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]