基于预测碰撞点带落角约束的导引律设计  

Design of Guidance Law with Impact Angle Constraint Based on Predicted Crack Point

作　　者：史绍琨 赵久奋 尤浩 SHI Shao-kun;ZHAO Jiu-fen;YOU Hao(Rocket Force University of Engineering,Xi’an 710025,China)

机构地区：[1]火箭军工程大学

出　　处：《火力与指挥控制》2019年第10期148-152,共5页Fire Control & Command Control

摘　　要：为提高导弹导引精度,增强对落角的控制,针对带倾角运动的目标,推导了攻击运动目标带落角约束的偏置比例导引律。通过在偏置项中加入导弹-目标的相对运动状态,实现对带倾角运动目标指定角度攻击;考虑到导弹带落角约束攻击运动目标时传统剩余飞行时间估计精度不高的问题,通过对弹目碰撞点的预测,在推导的导引律基础上设计了基于预测碰撞点的剩余飞行时间估计方法。仿真结果表明:在不同的落角约束下,设计的基于预测碰撞点的剩余飞行时间估计方法估计精准;推导的攻击运动目标带落角约束的偏置比例导引律攻击精度高,对落角控制强,过载分布合理。In order to improve the guidance precision and to enhance the control of the falling angle, the bias proportional navigation guidance law to moving targets with impact angle constraint is derived according to tilted moving targets. By adding the relative motion state between missile and target in bias term, the specified angle attack to the moving targets is realized. Considering imprecision of traditional time-to-go estimation under the moving targets with impact angle constraint, by predicting missile -target crack point, the time -to -go estimation method with impact angle constraint based on predicted crack point is designed under the deduced guidance law. The simulation results show that the estimation of designed time-to-go estimation method based on predicted crack point is precise under different angle constraint, the deduced bias proportional navigation guidance law to the fast-moving targets with impact angle constraint has better effect on high impact accuracy, control impact angle and overload.

关 键 词：预测碰撞点 运动目标 落角约束 偏置比例导引律 剩余飞行时间 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]