Three-body cooperative active defense guidance law with overload constraints:A small speed ratio perspective  

作　　者：Shuangxi LIU Zehuai LIN Yichong WANG Wei HUANG Binbin YAN Yong LI 

机构地区：[1]College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China [2]Hypersonic Technology Laboratory,National University of Defense Technology,Changsha 410073,China [3]School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China [4]Shanghai Electro-Mechanical Engineering Institute,Shanghai 201109,China

出　　处：《Chinese Journal of Aeronautics》2025年第2期226-243,共18页中国航空学报(英文版)

基　　金：support provided by the National Natural Science Foundation of China(No.62173274);the National Key R&D Program of China(No.2019YFA0405300);the Natural Science Foundation of Hunan Province of China(No.2021JJ10045);Shanghai Aerospace Science and Technology Innovation Fund,China(No.SAST2020-004);Postdoctoral Fellowship Program of CPSF(No.GZB20240989);the Open Research Subject of State Key Laboratory of Intelligent Game,China(No.ZBKF-24-01).

摘　　要：In air combat,one effective way to counter an incoming missile attacking an aircraft is to launch a defense missile compared with traditional passive defense strategies such as decoy and electronic countermeasures.To address this issue,this paper proposes a three-body cooperative active defense guidance law with overload constraints from the perspective of a small speed ratio.First,a cooperative guidance-oriented model for active defense is established and linearized to provide a foundation for the design of the guidance law.Then,the essential quantity known as Zero-Effort-Miss(ZEM)is analyzed during the engagement process.In order to minimize the influence of inaccurate estimates of remaining flight time in the ZEM,the concept of Zero-Effort-Velocity(ZEV)is introduced.Subsequently,utilizing the sliding mode control method,the guidance law is designed by selecting the ZEM and ZEV as sliding mode surfaces,combined with the fast power reaching law,and its finite-time stability is analyzed using the Lyapunov method.Furthermore,to quantitatively evaluate the performance of the proposed active defense guidance law,the interception rendezvous angle index is introduced.The proposed active defense guidance law considers integrating information from the incoming missile,aircraft,and defense missile with fewer simplifications and assumptions,and ensures that the aircraft is effectively protected with less overload required for the defense missile.Finally,simulation experiments demonstrate the effectiveness and adaptability of the proposed active defense guidance law.

关 键 词：Three-body active defense Cooperative guidance Guidance law Overload constraint Small speed ratio Sliding mode control 

分 类 号：TJ7[兵器科学与技术—武器系统与运用工程]