摘要
为实现导弹武器在约束条件下精确打靶,对导弹末制导律进行研究。考虑到一般比例制导方法不能满足先进的制导要求,对纯比例导引法进行改进,建立弹-目一体化模型分析末制导阶段角度变化关系,根据相关条件约束等增加控制项,分别设计了具有重力补偿项与具有落角约束的比例制导律;验证了综合脱靶量、法向负载、攻击时间等条件下的制导性能。
In order to realize the accurate target shooting of missile weapon under the constraint condition,the terminal guidance law of missile is studied by using the proportional guidance method with mature theory and rich achievements.Considering that the traditional proportional guidance method cannot meet the advanced guidance requirements,the improvement is considered on the basis of pure proportional guidance.The angle change relationship in the terminal guidance stage is analyzed by establishing the missile-target integration model.According to the relevant condition constraints,the control items are added,and the relevant parameters are discussed and analyzed.A gravity compensation item and a proportional guidance law with angle constraint are designed respectively.The guidance performance is verified by simulation under the conditions of miss distance,normal load and attack time.
作者
赵子恒
包长春
ZHAO Ziheng;BAO Changchun(College of Aviation, Inner Mongolia University of Technology, Hohhot 010051, China)
出处
《兵器装备工程学报》
CSCD
北大核心
2022年第S01期206-210,共5页
Journal of Ordnance Equipment Engineering
基金
内蒙古自治区自然科学基金项目(2021LHMS01002)
内蒙古自治区自然科学基金项目(2019LH01003)。
关键词
导弹
比例制导
重力补偿
落角约束
脱靶量
missiles
proportional guidance
gravity compensation
angle constraint
miss distance constraint
