基于二阶滑模控制的导弹自动驾驶仪设计  

Missile Autopilot Design Based on the Second-order Sliding Modes Control

作　　者：顾文锦[1] 尚安利[2] 李聪颖[2] 袁玉满[2] 

机构地区：[1]海军航空工程学院自动控制系,山东烟台264001 [2]海军航空工程学院研究生一队,山东烟台264001

出　　处：《飞行力学》2004年第4期29-32,共4页Flight Dynamics

摘　　要：讨论了一类非最小相位系统的输出跟踪问题。通过坐标转换将原系统转换为正规形,采用输出重定义技术,设计转换后的系统输出和期望输出,并根据它们构造滑模变量︴。在有限时间内,采用全局二阶滑模控制算法使得︴=︴　·=0,同时保证对原系统输出的跟踪。仿真结果表明,该方法设计的控制系统有比较理想的稳定性和鲁棒性。In this paper, the output tracking of a class of nonminimum phase systems is considered. The systems are transformed into normal form through coordination change, then output-redefinition approach is adopted to design the modified systems output and desired output. The difference between them is regarded as sliding modes variable σ. The global second-order sliding modes control is used in such a way that σ=σ·=0 in finite time, at the same time, ensure asymptotic tracking of the original system output. Simulations show that the effectivity and robustness of the algorithm.

关 键 词：非最小相位 零动态 输出重定义 二阶滑模 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]