基于自抗扰控制的导弹三维制导规律  

Three-dimensional guidance law based on active disturbance rejection control

作　　者：肖增博[1] 雷虎民[1] 宋龙[2] 徐剑芸[2] 

机构地区：[1]空军工程大学导弹学院,三原713800 [2]中国空空导弹研究院,洛阳471009

出　　处：《固体火箭技术》2011年第5期548-552,563,共6页Journal of Solid Rocket Technology

基　　金：航空科学基金(20090196065)

摘　　要：针对导弹制导系统中存在模型不确定性和外部扰动的特点,提出了利用自抗扰控制器设计导弹三维制导规律的新方法。在建立导弹三维制导模型的基础上,把系统非线性部分、回路间耦合项以及目标机动加速度视为对制导系统的未知总扰动,从而将模型变换为适于自抗扰控制的仿射系统。通过为俯仰和偏航回路分别引入自抗扰控制器,实现了双回路的动态解耦,并使系统对扰动具有很好的适应能力,同时应用粒子群优化算法进行了控制器参数的自寻优设计。这种方法不依赖于系统精确的数学模型,且不需太多的观测信息。仿真结果表明,对于机动逃逸目标,该制导规律仍能取得很好的跟踪性能和鲁棒性。Considering the model uncertainty in guidance system and the external disturbance,a new three-dimensional（3-D） guidance law is proposed based on active disturbance rejection controller（ADRC） for homing missile.Based on the 3-D guidance model of missile,regarding the system nonlinear,inter-loop coupling terms,and the target acceleration as unknown total disturbances,the transformation is conducted into an affined one for the purpose of active disturbance rejection control.For the pitch and yaw channels,the ADRCS are designed respectively,realizing dynamic decoupling of both channels and allowing the system to get good adaptability for disturbances.And the controllers parameters are found automatically using particle swarm optimization algorithm.Such a strategy is independent of exact mathematical model,and requires little observation information.The simulation results show that the guidance law exhibits strong robustness and good tracking performance even against a maneuvering target.

关 键 词：制导规律 自抗扰控制 粒子群优化 机动目标 解耦控制 鲁棒性 

分 类 号：V448.15[航空宇航科学与技术—飞行器设计]