摘要
大气层杀伤拦截器制导控制系统采用矢量喷管进行姿态与惯导控制,系统输出的开关特性具有强非线性,同时,姿态角指令进行突变时会相应地带来控制力矩指令突变,要求能够实现对姿态角指令的快速调节,且考虑姿控发动机喷气量。针对上述问题,设计了一种姿态角跟踪控制器,使用带有超前校正的死区迟滞继电控制律进行开关控制,并使用变结构模型参考自适应方法进行连续控制律设计,以提高开关控制器的工作效率,减少工作能耗。仿真结果表明,所设计的方法相较对比方法在快速性和精确性上均有提升,蒙特卡洛仿真结果显示,设计方法拦截精度为0.44 m,较对比拦截方法有较大提升。综上,设计方法能够以更快速的响应、更小的超调实现指令姿态角度的跟踪,且姿控发动机喷气用量有效减少,对工程实践有一定指导作用。
Vector nozzle is used for attitude and inertial navigation control in guidance and control system of atmospheric kill interceptor.The switching characteristics of the system output are strongly non linear.At the same time,the sudden change of atti tude angle command will bring about the sudden change of control moment command.It is required that the rapid adjustment of atti tude angle command can be realized,and attitude control trigger should be considered.In order to solve the above problems,this paper designs an attitude angle tracking controller,which uses dead time hysteretic relay control law with advanced correction for switching control.It also uses variable structure model reference adaptive method for continuous control law design to improve the ef ficiency of switching controller and reduce work energy consumption.The simulation results show that the proposed method is faster and more accurate than the comparative method.The Monte Carlo simulation results show that the interception accuracy of the pro posed method is 0.44 m,which is much better than that of the comparative interception method.To sum up,this method can track the command attitude angle with faster response and smaller overshoot.The amount of jet used in attitude control engine is reduced effectively,which has a certain guiding role for engineering practice.
作者
仲秦
闫杰
张晓峰
武文斌
ZHONG Qin;YAN Jie;ZHANG Xiaofeng;WU Wenbin(School of Astronautics,Northwestern Polytechnical University,Xi'an 710072,China;Unmanned System Research Institue,Northwestern Polytechnical University,Xi'an 710072,China;Xi'an Institute of Modern Control Technology,Xi'an 710065,China)
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2020年第1期115-119,共5页
Journal of Solid Rocket Technology
基金
国家自然科学基金面上项目(61503302)
关键词
大气层外动能拦截器
姿态控制系统
模型参考自适应
滑模控制
exoatmosphere killvehicle(EKV)
attitude control system
model reference control
sliding mode control
