弹载激光陀螺惯导系统安装支架设计

Design of mounting plate for a missile-borne laser gyro SINS

以某型号武器控制系统使用激光陀螺的任务为背景,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。通过双自由度分析法以及振动试验,指出原安装板刚性不足,导致谐振频率出现在激光陀螺的机抖频率附近以及其它需要减振的频率段,这些成为导航误差偏大的主要原因。把安装支架作为减振系统的一部分,应用有限元动态优化法设计出刚性增强的安装板和动态结构性能良好的安装支架来改善减振效果。经地面振动试验验证,新构建的减振系统的减振效果达到预期的设计要求,在国内战术武器激光陀螺应用方面取得很大进展,可以在飞行器上使用。

Since the circler error probability is a little larger in ground dynamic navigation test of a weapon laser gyroscope SINS, an improved vibration-damping system should be designed. The two-freedom analysis and vibration experiments showed that the initial installing plate was not very stiff, so the resonance frequency appears improperly. Using the finite element dynamic optimization method, a stiffer installing plate was designed, and another fixing bracket with better dynamic characteristics was developed. These help to improve the efficiency of the vibration damping. The ground vibration experiments show that the new vibration-damping system achieves the expected results, and can be applied into the aircraft.