基于状态依赖Riccati方程的复合控制导弹自动驾驶仪设计  

Design of autopilot for blended controlled missiles via state-dependent Riccati equation

作　　者：李权[1] 周荻[1] 

机构地区：[1]哈尔滨工业大学航天学院,黑龙江哈尔滨150001

出　　处：《系统工程与电子技术》2012年第7期1445-1451,共7页Systems Engineering and Electronics

基　　金：国家自然科学基金(61174203);教育部新世纪优秀人才支持计划(NCET-08-0153);航空科学基金(20110177002)资助课题

摘　　要：针对直接侧向力与气动力复合控制拦截导弹的非线性控制问题,设计了基于状态依赖Riccati方程的自动驾驶仪。根据俯仰和偏航通道的非线性动力学模型,通过扩展线性化将其转化为具有状态依赖参数的类线性结构,并针对该类线性结构设计了基于状态依赖Riccati方程的加速度指令跟踪控制器。考虑到直接侧向力由脉冲发动机提供时具有离散特性,分析了实际控制量不能达到理想值时系统的非线性容限,给出闭环系统保持局部渐近稳定的充分条件。仿真实例验证了这种设计策略的有效性。A missile autopilot is designed via the state-dependent Riccati equation （SDRE） approach for an interceptor with blended lateral thrust and aerodynamic force. A nonlinear dynamic model describing pitch and yaw motion of the blended missile is transformed into a linear-like structure with state-dependent coefficient （SDC） matrices by an extended linearization. Based on this linear-like structure, an SDRE feedback controller is designed to steer the missile to track an acceleration commands. Since the lateral thrust provided by some pulse thrusters is considered as a discrete-time variable, the nonlinear tolerance of the feedback system is analyzed whenever the control cannot be implemented ideally. Some sufficient conditions are given to guarantee that the closed system is locally asymptotically stable. Simulation results vitrify the proposed control strategy.

关 键 词：复合控制导弹 非线性控制 状态依赖Riccati方程 非线性容限 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]