Study On The Dynamic Characteristics Of The Silicon Micro-machined Butterfly Gyroscope MIMU Damping System

The inertial navigation system is an autonomous navigation system in real sense,which can provide the navigation information of the vehicle autonomously through the inertial unit,such as acceleration,velocity,attitude and etc.With the development of MEMS technology,the inertial unit in the micro inertial navigation system appeared.The inertial unit in the micro inertial navigation system is directly fixed with the vehicle,while the vehicle is excited by many factors under the flight conditions,which the random error of the micro inertial unit is increased due to this vibration of the vehicle making the attitude angle error be increased,which can reduce the measurement accuracy of the whole micro inertial navigation system greatly.Therefore,it is necessary to study the damping structure and dynamic characteristics of MIMU system.In this paper,the vibration reduction design of the the Silicon Micro-machined Butterfly Gyroscope MIMU combination is carried out,and the detailed research and analysis is made from theory,simulation and experiment,the main contents are as follows:Firstly,the theory of vibration reduction of MIMU components is analyzed,and the general vibration system scheme is designed.The vibration characteristics of MIMU damping system in the practical application environment is analysis,and the model of dynamic analysis,dynamic differential equation is established;Based on the analysis of passive vibration isolation model of active vibration isolation system is established,and the dynamic analysis is carried out.Secondly,the structure dynamics simulation analysis of the MIMU vibration reduction system is carried out by using MSC.Patran/Nastran software.In view of the practical application environment of MIMU combination,the modal analysis,random vibration analysis and impulse response analysis are carried out.After analysis,the results show that the natural frequency of the system is reduced,which can be isolated from the vibration noise of lower frequency,and it is also shown that the design of the vibration system meets the requirements of space vibration.Finally,physical verification is carried out on the basis of the above analysis.The vibration and impact tests are carried out on the MIMU damping system,which verifies the situation where Micro inertial navigation system is in accordance with the requirements of the mechanical environment and control system.The experimental results show that the structure design of MIMU damping system is reasonable.It is verified that the design of the vibration reduction system of the finite element dynamic simulation analysis and the dynamic analysis of the vibration reduction system are feasible,and the design results are correct through the comparison between the experimental results and the simulation results.