带落角与舵面饱和约束的三维制导控制一体化设计
Three-Dimensional Integrated Guidance and Control Design Under Constraints of Impact Angle and Rudder Surface Saturation
杨豪 1张士峰 1杨华波 1周颉鑫 2祝海 2朱效洲2
作者信息
- 1. 国防科技大学空天科学学院,长沙 410073;空天跨域飞行器总体与控制技术湖南省重点实验室,长沙 410073
- 2. 中国军事科学院国防创新研究所,北京 100071;智能博弈与决策实验室,北京 100071
- 折叠
摘要
为使制导控制系统在实际应用过程中适用所面对的多种约束条件,同时避免制导与控制系统设计过程中反复迭代带来的巨大工作量,提出了 一种带有落角与舵面饱和约束的三维制导控制系统一体化设计方法.根据导弹六自由度非线性模型以及三维弹目相对运动模型建立全状态耦合的制导控制一体化模型,基于动态面控制器原理,采用4级滑模面设计,构建了能够满足落角与舵面饱和约束的控制器,并给出了控制系统闭环稳定性证明.通过仿真实验有效验证了所提方法的正确性、有效性及鲁棒性.
Abstract
In order to avoid the huge workload caused by repeated iterations in the process of guidance and control system design,a three-dimensional integrated guidance and control design under impact angle and rudder surface saturation constraints is proposed,which is more applicable in practice.Based on the 6 DOF nonlinear model of missile and the 3 DOF missile-target relative motion model,an integrated guidance and control model with full-state coupling is established.Based on the dynamic surface control method,a four-stage sliding surface design is applied to establish a controller which satisfies the impact angle and rudder surface saturation constraints,and the closed-loop stability of the system is proven.The correctness,effec-tiveness and robustness of the proposed method are effectively verified by simulation results.
关键词
制导控制一体化/落角约束/舵面饱和约束/动态面控制器Key words
Integrated guidance and control/Impact angle constraint/Rudder surface saturation con-straint/Dynamic surface control method引用本文复制引用
出版年
2024
NETL
NSTL
万方数据