摘要
针对采用推力矢量控制的拦截弹,首先给出了推力矢量和气动力的归一化设计方法,通过引入等效舵偏角的概念,将多控制输入问题转化为单控制输入问题,并进行求解,设计了推力矢量偏心和气动舵偏转的控制分配策略,给出了气动舵偏转角及推力矢量偏心角的数学表达式,解决了多控制量之间相互争斗的问题。在此基础上,通过模型标准化,采用Backstepping方法(反步法),借助Lyapunov再设计工具,对导弹制导与控制系统进行一体化设计,得到了俯仰平面内的制导控制律。仿真结果表明,和常规制导与控制方法分别设计相比,采用该制导控制一体化设计方法能够使拦截弹有效拦截机动目标,并且导弹的姿态和执行机构偏角的变化也更加平稳。
Aiming at interceptor with thrust vector control,a method for integrated guidance and control was proposed.Based on the introduction of equivalent elevator angle,multiple-inputs control problem was transformed into a single input problem,and the problem of normalizing the thrust vector and aerodynamic force was resolved.The strategy of control distribution was designed,and expressions of elevator angle and thrust vector deflection angle were given.On the basis of the simplified and standardized model of attack-defense confrontation,integrated guidance and control law was obtained by using backstepping method and Lyapunov redesign method. Numerical simulation results show that the interceptors with this law of integrated guidance and control cannot only get targets effectively,but also make attitudes and the angles of actuators change smoothly compared with conventional method of guidance law and control law designed respectively.
出处
《弹道学报》
CSCD
北大核心
2015年第4期1-6,共6页
Journal of Ballistics
基金
航空科学基金项目(20140152002)
南京航空航天大学研究生创新基地(实验室)开放基金(kfjj201458)
中央高校基本科研业务费专项基金项目
关键词
拦截弹
推力矢量
控制分配
制导控制一体化
反步法
interceptor
thrust vector control
control distribution
integrated guidance and control
backstepping
