Research on Vibration Performance Improvement of Airborne Inertial Navigation System
A method for analyzing the coupled angular motion of inertial measurement components under vibration conditions,which leads to cone errors and reduced inertial navigation accuracy,is proposed.This method takes into account the inconsistency and anisotropy of damper stiffness.Starting from mechanical analysis,the spatial six degree of freedom matrix vibration differential equation of the inertial navigation system was derived.A numerical solution calculation model for the vibration equation of the inertial navigation system has been established.Secondly,based on engineering practice,numerical simulation software is used to analyze the influence of batch stiffness consistency and stiffness anisotropy of shock absorbers.And through finite element simulation analysis,the calculation results of coupling angular velocity caused by eccentricity caused by stiffness fluctuation of the shock absorber were compared and verified.Finally,the influence mechanism of different resonant frequencies on the amplitude of diagonal vibration in the damping system was analyzed.
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