自旋导弹的反馈线化控制器设计  

A Spin Missile Autopilot Designed Using Feedback Linearization

作　　者：邹晖[1,2] 陈万春[1,2] 殷兴良[1,2] 

机构地区：[1]北京航空航天大学宇航学院,北京100083 [2]中国航天科工集团,北京100830

出　　处：《弹箭与制导学报》2004年第S2期228-230,234,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：建立了自旋导弹在准弹体坐标系中的运动模型,运用动态反馈线化的方法设计自旋导弹的自动驾驶仪。通过时间尺度分离,将系统划分成快慢两个子系统,分别进行反馈线化设计。避免了不稳定零动态的出现。并实现了准弹体坐标系中的解耦控制。仿真结果表明该控制器具有一定的鲁棒性。Dynamic model of a spin missile was established in pseudo body coordinates.A three axes autopilot based on dynamic feedback linearization control was developed for it.The system was divided into"fast"and"slow" subsystems through time scale separate.Controllers was designed respectively.The instable zero dynamics was cancelled and de- couple coutrol in pseudo body coordinates was archived.Numerical simulations showed that this autopilot is of good performance and robustness.

关 键 词：自旋导弹 非线性 自动驾驶仪 时间尺度 反馈线化 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]