Impact time control using biased proportional navigation for missiles with varying velocity  

作　　者：Guoxin SUN Qiuqiu WEN Zhiqiang XU Qunli XIA 

机构地区：[1]School of Aerospace,Beijing Institute of Technology,Beijing 100081,China [2]Harbin Jiancheng Industry Company Limited,Harbin 150030,China

出　　处：《Chinese Journal of Aeronautics》2020年第3期956-964,共9页中国航空学报（英文版）

摘　　要：A feasible guidance scheme with impact time constraint is proposed for attacking a stationary target by missiles with time-varying velocity.The main idea is to replace the constant velocity with the future mean velocity;therefore, the existing time-to-go estimation algorithm of the proportional navigation guidance law can be improved to adapt to varying conditions.In order to obtain the prediction of the velocity profile, the velocity differential equation to the downrange is derived, which can be numerically integrated between the current downrange and the target position by the on-board computer.Then, a third-order polynomial is introduced to fit the velocity profile in order to calculate the future mean velocity.At the beginning of each guidance loop, the future mean velocity is predicted and the time-to-go information is updated, based on which a novel biased proportional navigation guidance law is established to achieve the impact time constraint.Finally,numerical simulation results verified the effectiveness of the time-to-go estimation algorithm and the proposed law.

关 键 词：GUIDANCE Homing missiles Impact time Proportional navigation guidance Time-varying velocity 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]