摘要
为提高弹道修正弹姿态控制精度,提出了一类固定翼/可动翼组合的双旋弹道修正弹工作原理,建立了滚转通道状态空间模型,基于指数趋近律的变结构控制理论,设计了双旋弹道修正弹滚转姿态控制器.利用Simulink软件进行数字仿真.仿真结果表明:在大动压和小动压条件下分别跟踪阶跃信号,弹道修正弹姿态调整时间均小于0.5s,该姿态控制方法有效.
To improve introduced for a type of the precision of spin-s spin-dual projectile eq was built in roll channel, and law based variable structure Attitude adjustment time of signals in condition of effective. the roll-attitude law. The contro 1 mode was simulated in trajectory correction projectile was less Simulink. The result indicated： than 0. 5 s, while tracking step dynamic pressure and small dynamic pressure. The control method proved
出处
《西安工业大学学报》
CAS
2015年第12期1016-1019,共4页
Journal of Xi’an Technological University
关键词
弹道修正弹
固定翼/可动翼
变结构控制
姿态控制
trajectory correction projectile
fix-wing and movable canard
variable structure control
attitude control
