摘要
为降低单兵制导火箭弹的成本,同时确保其具有较远的作用距离和较高的命中精度,针对静止目标,设计了单兵火箭弹简易制导控制律。首先,将飞行弹道进行分段设计,以瞄准线作为基准弹道,采用虚拟目标导引法实现对基准弹道的跟踪;然后,进行STT控制器的设计,基于典型设计点处控制器的参数插值,得到实时飞行过程中的控制器参数,确保火箭弹在整个飞行过程中具有较高的控制精度;最后,进行了仿真计算,通过仿真结果分析可知,所设计的制导控制系统具有较高的鲁棒性。
To reduce the cost of guided individual rocket projectile,and to ensure that it has a longer striking distance and higher accuracy,the simply guidance control law of the individual rocket projectile was designed aiming at the static target in this paper. First,the flight trajectory was segmented,aiming line was used as the standard trajectory,the standard trajectory tracking was realized by the virtual target guidance method. Then the STT controller was designed to get the controller parameters in real time flight based on the parameter interpolation of the controller at typical design points,so as to ensure the rocket has a higher control accuracy in the whole flight envelop. Last,the simulation analysis shows that the designed guidance control system has high robustness.
作者
陈伟
谭晓军
孙传杰
冯高鹏
薛晓中
CHEN Wei TAN Xiao-jun SUN Chuan-jie FENG Gao-peng XUE Xiao-zhong(Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang 621000, China School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing 210094, China)
出处
《飞行力学》
CSCD
北大核心
2016年第6期54-57,共4页
Flight Dynamics
关键词
火箭弹
简易制导
虚拟目标
STT控制器
rocket projectile
simply guidance
virtual target
STT controller
