多约束下的敏捷导弹大离轴转弯规律研究  

Research on Big Off-axis Turning Law Under Multiple Constraints for Agile Missile

作　　者：韦亚利 殷玮 刘印田 王鑫 胡春朝 WEI Yali;YIN Wei;LIU Yintian;WANG Xin;HU Chunchao(Shanghai Electro-Mechanical Engineering Institute,Shanghai 201109,China)

机构地区：[1]上海机电工程研究所,上海201109

出　　处：《空天防御》2020年第3期96-102,共7页Air & Space Defense

摘　　要：针对一种尾部采用发动机引流提供侧向直接力的敏捷导弹方案,面对转弯快速性约束、弹速约束、速度到位角约束、姿态到位角约束等约束条件,引入最佳轴控制原则、最快转弯速率原则以及导弹速度限制条件,设计了一种初始转弯规律。仿真结果表明该转弯规律实现了导弹速度到位和姿态到位,且能保证飞行过程中的弹速。For an agile missile that uses direct lateral force provided by engine plume,under the constraints of turning rapidity,missile speed,expected speed angle and expected attitude angle,this paper designs a turning law employing the optimal axis control principle,the fastest turning rate principle,and the conditions of missile speed limit.Simulation results show that this turning law realizes the turning speed and the turning attitude of the missile,and can guarantee the speed of the missile in flight.

关 键 词：直接侧向力 越肩发射 多约束 转弯规律 姿态角控制 攻角控制 

分 类 号：TJ762.23[兵器科学与技术—武器系统与运用工程]