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

作　　者：杨豪 张士峰[1,2] 杨华波 周颉鑫[3,4] 祝海 朱效洲 YANG Hao;ZHANG Shifeng;YANG Huabo;ZHOU Jiexin;ZHU Hai;ZHU Xiaozhou(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China;Hunan Provincial Key Laboratory of Aerospace Cross-Domain Flight Vehicle Systems and Control Technology,Changsha 410073,China;Defense Innovation Institute,Chinese Academy of Military Science,Beijing 100071,China;Intelligent Game and Decision Laboratory,Beijing 100071,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073 [2]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 [3]中国军事科学院国防创新研究所,北京100071 [4]智能博弈与决策实验室,北京100071

出　　处：《航天控制》2024年第3期9-15,共7页Aerospace Control

基　　金：国家自然科学基金(U21B2028)。

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。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,effectiveness 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 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]