摘要
对中远距空空导弹大离轴角发射导引规律进行了研究。导弹在转弯阶段采用BTT控制模式,分析了实现快速转弯的机理及要求,研究了实现快速转弯的最佳升力面,确定了导弹滚转控制指令,建立了导弹转弯动力学模型,利用剩余转弯角度关系,设计攻角控制指令;提出旋转坐标系方法对滚转控制指令进行了优化,解决了指令跳变问题,实现了转弯过程最小滚转偏差控制,利用最佳升力面法向矢量投影关系,进一步判定攻角指令控制逻辑,实现与最小滚转偏差控制指令的匹配。最后通过数字仿真验证了设计方法的正确性和有效性。
The guidance law of air⁃to⁃air missile with large off⁃axis launch angle is studied in this paper.The BTT control mode is applied to missile cruise in the turning stage.The mechanism and requirements of fast turning of missile are briefly analyzed,and the optimal lift surface for fast turning is studied and the missile roll control command is determined.The dynamic model of missile is established in turning phase,and the control command of angle of attack is designed by using the relation of residual turning angle.The rotation coordinate system is proposed to optimize the roll control command,solve the problem of command jump and achieve the minimum roll deviation control in the turning process.The projection of the best nor⁃mal vector of lift surface is used to determine the control logic of the command of angle of attack and realize matching with the minimum roll deviation control commands.In the end,the correctness and effectiveness of design method are verified by digitalized simulation of typical scenes.
作者
李瑞康
陈淼
钟永建
LI Ruikang;CHEN Miao;ZHONG Yongjian(Shanghai Electro-Mechanical Engineering Institute,Shanghai 201109,China)
出处
《航天控制》
CSCD
2024年第1期58-64,共7页
Aerospace Control
基金
上海航天科技创新基金项目(SAST2019-10)。
