摘要
针对带有姿控式直接侧向力/气动力复合控制系统导弹的控制律设计问题,建立了俯仰平面内姿态控制系统的数学模型,应用非线性系统理论对模型进行了分析,在此基础上建立了进行控制系统设计的简化模型。基于滑模变结构控制理论进行了复合控制律设计,并分别考虑气动力控制和直接侧向力控制的特点对所设计的控制律进行了实现。所设计的复合控制系统在进行快速攻角指令跟踪的同时,可以有效节省姿控发动机的使用数量。仿真结果说明了所提出方法的有效性。
For the controller design of missiles with blended lateral jets and aerodynamic control systems,the mathematical model of attitude control system in the pitch plane is constructed,and some nonlinear system theory is applied to analyze the characteristics of the attitude control model.In view of the above,a simplified model is built for control system design.A blended control law is designed by applying sliding-mode variable structure control theory,and the implementation of the controller is discussed based on the respective characteristics of lateral jet control and aerodynamic control.By using the proposed control law,fast tracking of angle-of-attack is realized,and the consumption of lateral jets is greatly reduced as well.Simulation results show the effectiveness of the proposed design.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2011年第2期310-316,共7页
Journal of Astronautics
基金
国家自然科学基金重点项目(60736022)
关键词
输出跟踪
侧喷发动机
姿态控制
变结构控制
复合控制
Output tracking
Lateral jet
Attitude control
Variable structure control
Blended control
