摘要
针对激光陀螺捷联惯导系统在地面动态导航测试中圆概率误差偏大的现象,要求给激光陀螺捷联惯导系统设计出性能优良的减振系统。分析激光惯导的振动模型,结合对比原有惯导减振系统提出双层减振。在对双层减振系统的分析中,把整个安装支架作为减振系统的一部分,充分考虑弹载设备的可安装性,应用有限元法设计出动态性能良好的安装支架和减振器来改善减振效果。通过地面大量振动试验的验证以及反复对支架和减振器参数的优化设计,使得新构建的减振系统的谐振频率避开激光陀螺的机抖频率以及其它需要减振的频率段,减振效果达到了预期的设计要求,可以在飞行器上使用。
Contrapose the phenomenon that the circler error probability is a little larger in the ground dynamic navigation test of the laser gyroscope strapdown inertial navigation system, a better vibration damping system needs to be designed for SINS with laser gyroscope. Through analyzing the model of the vibration and the old vibration damping system, a new system of the double free degree be brought forward to reduce the response of random vibration on inertial navigation system. During the design, considering the installing plate is part of the vibration damping system and reckoning the inner space of the tactical missile carefully, using the finite element dynamic optimization method, a satisfactory installing plate and a damper with better dynamic characteristics is designed, then through ground vibration experiment and the repetition parameter optimal design, the new vibration damping system now can work effectively and the effect of vibration absorbing has satisfied the requirement, which can be applied to the aircraft.
出处
《航天控制》
CSCD
北大核心
2007年第6期81-85,89,共6页
Aerospace Control
关键词
激光惯导
双层减振
减振器
Laser strapdown IMU
Double-layer vibration absorbing
Damper
