摘要
为了描述自振荡阻尼回路的设计方法,以某小型战术导弹为例,设计了基于固体燃气姿控舵机的自振荡阻尼回路原理,详细描述了阻尼回路校正网络参数设计方法和设计过程,并对阻尼回路进行了仿真验证,结果表明参数设计正确,满足要求。
In order to describe the design method of the self sustained oscillations damping loop, the loop based on solid gas vane is designed, the design method and the design procedure of the correction parameter of the damping loop are described in detail, and the damping loop is emulated. The results indicate that the parameter design is perfect and meet the challenge.
出处
《弹箭与制导学报》
CSCD
北大核心
2009年第1期68-70,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
燃气舵机
阻尼回路
自振荡
战术导弹
姿态控制
hot pneumatic actuator
damping loop
self sustained oscillations
tactical missile
attitude control