速度相关初制导拐弯规律设计  

A Turning Regulation with Velocity for the Launch Guidance

作　　者：郑国栋 石琛 韦亚利 王磊 ZHENG Guodong;SHI Chen;WEI Yali;WANG Lei(School of Automation, Nanjing University of Science and Technology, Nanjing 210094;Shanghai Electro-Mechanical Engineering Institute, Shanghai 201109)

机构地区：[1]南京理工大学自动化学院,南京210094 [2]上海机电工程研究所,上海201109

出　　处：《飞控与探测》2022年第2期24-29,共6页Flight Control & Detection

摘　　要：防空导弹初制导的任务是实现向目标射向拐弯,使得初制导段结束时刻导弹姿态、速度达到要求。针对助推发动机推重比小,导致初制导段时间长且参数散布大的问题,提出了速度相关初制导拐弯规律,并在姿态指令中加入重力补偿项,用于解决助推飞行段初制导精度差的问题。仿真结果表明,这种拐弯规律可以有效适应不同推力状态下初制导精度要求,且初制导结束时刻攻角小,有利于初、中制导交班。The goal of missile launch guidance is that makes the missile turn to the target,and make the missile attitude and velocity meet requirements at the end of launch guidance.But under the condition that the engine has small thrust-weight radio,the time of launch guidance is long and has a large disseminate.This paper presents a turning regulation with velocity for the launch guidance,and adds gravitational compensation to the instruction of the attitude angle error,in order to solve the problem.The simulation shows that this turning regulation can adapt to the required precision under different conditions of the engine,and the angle of attack is small at the end of launch guidance which is propitious to the shift from the launch guidance to the middle guidance.

关 键 词：初制导 拐弯规律 重力补偿 制导精度 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]