良好的执行器在弹道修正系统中不仅能够简化控制器的设计,降低功耗,而且能够有效提高弹道修正效率,因此,执行机构的设计也是进行弹道修正控制的一个重要环节。文中以一种尾翼微旋火箭弹为研究对象,在分析弹道修正系统对执行机构输出和响应时间要求的基础上,设计了一种适用引信头锥摆动的电机驱动和齿轮传动的执行机构,并提出一种驱动执行算法。

Good actuators in ballistic correction system can not only simplify the controller design, lower power consumption, but also can effectively improve the trajectory correctional efficiency, therefore, the design of actuators for trajectory correction control is one of important links. A kind of tail micro rotary rocket was taken as research object in this paper, then a kind of applicable fuze nose cone motor drive and gear drive actuator were designed, and a kind of drive algorithm was put forward based on the analysis of trajectory correction system for actuator output and response time on the basis of the requirement.