Research on the method of vertically launched missiles flying around and attacking targets

垂直发射战术导弹绕射打击目标方法研究

¹ School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China
² Xi'an Mordern Control Technology Research Institute, Xi'an 710065, China

Received: 1 July 2024

Abstract

A multi-stage combination trajectory design and pose switching control strategy is proposed to address the problem of vertical launch missiles flying around and attacking targets in the opposite direction. Firstly, a model for vertical launch tactical missile motion was established, by using quaternions to represent the attitude rotation matrix. By timely switching the rotation order, it was calculated as the missile attitude angle, adapting to the range of attitude angles for vertical launch diffraction attacks. Secondly, a segmented design was carried out for the diffraction attack trajectory, dividing the entire trajectory into four sections: vertical turning section, diffraction preparation section, diffraction turning section, and final strike section. The control strategies for pitch/yaw/roll three channels of each section of the trajectory were provided; and the transition models for different stages of trajectory were established, and the control methods under different control strategies were provided to achieve the stable flight diffraction and target attack of vertically launched missiles. Finally, taking a certain type of vertically launched tactical missile as an example, the effectiveness of the present method was verified through the comparative simulation. Monte Carlo simulation showed that the miss distance was less than 0.15 m, and the expected yaw angle error of the strike was less than 2°.

摘要

针对垂直发射战术导弹绕射打击目标的问题, 提出一种多段组合的弹道设计与位姿切换的控制策略。建立了垂直发射战术导弹运动的数学模型, 采用四元数表示姿态旋转矩阵, 通过适时切换旋转顺序, 将其解算为导弹姿态角, 适应垂直发射绕射打击的姿态角范围; 对绕射打击弹道进行了分段设计, 将全段弹道分为垂直转弯段、绕射准备段、绕射转弯段、末段打击段, 并给出了各段弹道俯仰/偏航/滚转三通道的控制策略; 建立了不同阶段弹道的过渡模型, 给出了不同控制策略下的控制方法, 实现垂直发射战术导弹的稳定飞行绕射并打击目标。以某型垂直发射战术导弹为例, 通过对比仿真校验了所提方法的有效性, 蒙特卡洛仿真统计脱靶量小于0.15 m, 期望打击偏航角误差小于2°。