Optimal predictive sliding-mode guidance law for intercepting near-space hypersonic maneuvering target  

作　　者：Bolun ZHANG Di ZHOU 

机构地区：[1]School of Astronautics,Harbin Institute of Technology,Harbin 150001,China

出　　处：《Chinese Journal of Aeronautics》2022年第4期320-331,共12页中国航空学报（英文版）

基　　金：supported by the National Natural Science Foundation of China(No.61773142)。

摘　　要：The design of optimal guidance law for intercepting a near-space hypersonic maneuvering target with bounded inputs is considered. Firstly, a maneuvering model for near-space hypersonic aircraft is given. Then, the aircraft acceleration prediction can be obtained using this model with two neural networks. By using the target acceleration prediction, which is taken into account when calculating the Zero Effort Miss(ZEM), an optimal sliding-mode guidance law is proposed to fulfill the guidance task. An adaptive sliding-mode switch term is designed to deal with actuator saturation and prediction errors. Finally, numerical simulations show that the proposed guidance law can reduce the energy consumption and the terminal acceleration command of the interceptor effectively.

关 键 词：Adaptive sliding-mode control Near-space hypersonic aircraft Neural networks Optimal control Predictive guidance law 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]