某型惯性测量组件结构谐振频率仿真分析  

Simulation Analysis of Resonant Frequency of a Certain Inertial Measurement Module

作　　者：罗锐 曹翌军 LUO Rui;CAO Yijun(Hanzhong Military Agent Office of Naval Armament Department,Hanzhong 723000)

机构地区：[1]海装驻汉中地区军事代表室,汉中723000

出　　处：《舰船电子工程》2020年第7期112-116,共5页Ship Electronic Engineering

摘　　要：为了研究飞机惯导系统中的惯性测量组件整体结构的振动性能,初步验证惯性测量组件的结构设计是否合理,测量计算惯性测量组件的结构谐振频率,防止惯性测量组件装机后出现共振现象,利用Ansys软件对惯性测量组件进行仿真分析,对惯性测量组件进行结构模态分析,模拟组件在激励频率作用下所发生的拉伸、弯曲和扭转及其组合等空间变形的形态。结果表明:惯性测量组件的前6阶模态均在900 Hz以上,与GJB150.16A中给出的飞机在着陆冲击和机动飞行时为低频振动频率相比较,仿真结果远离机上常见的长时间低频机械振动频段,从而避免了谐振现象的发生。In order to study the vibration performance of inertial measurement device in aircraft inertial navigation system,the structural design of inertial measurement device preliminarily is verified,the resonant frequency of inertial measurement device is calculated,the resonance phenomenon of inertial measurement device after installation is prevented,the aircraft inertial measurement device is simulated by Ansys. The structural modal analysis of inertial measurement devices is carried out,the spatial deformation of the product,such as stretching,bending,torsion and its combination,which is simulated under the excitation frequency.The results show that the 6 modes of inertial measurement devices are all above 900 Hz. Compared with the low-frequency vibration frequency of aircraft in landing impact and maneuvering flight given in GJB 150.16 A,the simulation results are far away from the low frequency mechanical vibration frequency.

关 键 词：惯性测量器件 谐振频率仿真 模态分析 

分 类 号：V241.5[航空宇航科学与技术—飞行器设计]