摘要
针对拦截弹的攻击角约束制导问题,提出了一种基于反演滑模和扩张状态观测器(ESO)的制导控制一体化(IGC)设计方法。首先,基于弹目相对运动方程和拦截弹的非线性动力学方程,建立了拦截弹IGC模型,设计了ESO估计目标加速度和自动驾驶仪回路的干扰;在此基础上,基于干扰估计值和反演滑模方法,设计了IGC算法获取虚拟控制力矩,同时基于李雅普诺夫理论分析了闭环系统的稳定性;然后,利用动态控制分配技术将所获取的期望控制力矩分配到实际执行机构;最后,通过仿真结果验证了所设计的IGC+ESO算法的有效性。
A novel integrated guidance and control（ IGC） design method based on the backstepping sliding mode and extended state observer（ ESO） is proposed for the interceptor with terminal angle constraint. Firstly,the IGC model is employed by combining the interceptor-target relative motion model with the nonlinear dynamic equation of the interceptor. Then,the ESO is constructed to estimate the target acceleration and autopilot loop disturbance. Based on the estimated value and backstepping sliding mode method,the IGC algorithm is given to obtain the virtual control moment. The stability of the closed-loop IGC system is also proven based on the Lyapunov theory. Moreover,a new dynamic control allocation algorithm is proposed to distribute the above virtual control moment among the corresponding actuators. Finally,simulation results illustrate the effectiveness of the proposed IGC ＋ ESO algorithm.
作者
郭超
宋琛
赵玉杰
GUO Chao SONG Chen ZHAO Yu-jie(The 18th Research Institute, China Airborne Missile Academy, Luoyang 471000, China)
出处
《飞行力学》
CSCD
北大核心
2017年第2期44-48,53,共6页
Flight Dynamics
基金
航空科学基金资助(2016ZC12005)
关键词
制导控制一体化
反演滑模
扩张状态观测器
动态控制分配
攻击角约束
integrated guidance and control
backstepping sliding mode
extended state observer
dynamic control allocation
terminal angle constraint
