海豚头气动外形导弹主动段过载驾驶仪设计  

Design of Acceleration Autopilot for Dolphin Head Shaped Missile in Boost Phase

作　　者：吴光辉 赵宏宇 钟继鸿 张佳梁 许新鹏 WU Guanghui;ZHAO Hongyu;ZHONG Jihong;ZHANG Jialiang;XU Xinpeng(Shanghai Electro-Mechanical Engineering Institute,Shanghai 201109,China)

机构地区：[1]上海机电工程研究所,上海201109

出　　处：《航天控制》2024年第4期29-34,共6页Aerospace Control

摘　　要：针对海豚头气动外形导弹主动段飞行过程中存在快速变化的俯仰干扰力矩导致驾驶仪过载指令不跟随的问题,研究了一种基于自适应控制的三回路过载驾驶仪在线调参方法。首先,对纵向短周期下的导弹动力学进行建模,建立三回路过载驾驶仪状态方程,在标称状态下采用极点配置对三回路过载驾驶仪的控制参数进行设计;其次,将标称状态下的驾驶仪视为参考模型,采用模型参考自适应方法,通过设计Lyapunov函数对自适应更新律进行设计。为了增强在建模不确定条件下自适应算法的稳定性,引入投影算子和死区的概念;最后,在气动拉偏条件下对海豚头气动外形导弹的主动段进行三回路自适应过载驾驶仪指令跟踪仿真。仿真结果表明,三回路自适应过载驾驶仪在海豚头气动外形导弹的主动段具有较好的动态跟踪特性。An online tuning method for a three-loop autopilot based on adaptive control theory is presented in this paper.Due to the rapidly changing disturbance of a dolphin head shaped missile in boost phase,the autopilot is unable to follow commands accurately,which overloads by pitch disturbance torque.In order to solve the problem,firstly,the state equation of the three-loop autopilot is established based on short period dynamics,and the pole placement method is applied to design the control parameters in the nominal state.Then,the nominal autopilot is designed as a reference model,and the control parameters are designed by a Lyapunov function using the model reference adaptive method.Aiming at enhancing the stability of the adaptive controller under modeling uncertainties,the projection operators and dead zones are introduced.Finally,the three-loop adaptive autopilot tracking simulation is conducted for the dolphin head shaped missile in boost phase.The simulation results of the three-loop adaptive autopilot show fairly good tracking performance of the dolphin head shaped missile.

关 键 词：自适应控制 过载驾驶仪 极点配置 海豚头导弹 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]