机载捷联惯导系统振动性能提升研究
Research on Vibration Performance Improvement of Airborne Inertial Navigation System
成果达 1瞿晓东 2张懿2
作者信息
- 1. 西北工业大学自动化学院, 西安 710072;航空工业西安飞行自动控制研究所, 西安 710065
- 2. 航空工业西安飞行自动控制研究所, 西安 710065
- 折叠
摘要
针对振动条件下,惯性测量组件产生耦合角振动,进而引起圆锥误差导致惯性导航精度降低的问题,提出了一种考虑减振器刚度不一致性与各向异性情况下,惯性测量组件振动耦合角运动的分析方法.从力学分析出发,推导了惯导系统空间六自由度矩阵振动微分方程;建立了惯导系统振动方程的数值解计算模型.其次,基于工程实际,使用数值仿真软件分析减振器批次刚度一致性和刚度各向异性的影响;并通过有限元仿真分析对比验证了减振器刚度波动导致的偏心距引起耦合角速度计算结果.最后分析了减振系统不同谐振频率对角振动幅值的影响机理.
Abstract
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.
关键词
捷联惯导系统/振动性能/角振动Key words
Strapdown inertial navigation system/Vibration performance/Angular vibration引用本文复制引用
基金项目
航空基金重点项目(201908018001)
出版年
2024
NETL
NSTL
万方数据