This paper presents an approach for realizing a phase difference measurement of a new gyro. A silicon micromachined gyro was mounted on rotating aircraft for aircraft attitude control. Aircraft spin drives the silicon pendulum of a gyro rotating at a high speed so that it can sense the transverse angular velocity of the rotating aircraft based on the gyroscopic precession principle when the aircraft has transverse rotation. In applications of the rotating aircraft single channel control system, such as damping in the attitude stabilization loop, the gyro signal must be kept in sync with the control signal. Therefore, the phase difference between both signals needs to be measured accurately. Considering that phase difference is mainly produced by both the micromachined part and the signal conditioning circuit, a mathematical model has been established and analyzed to determine the gyro’s phase frequency characteristics. On the basis of theoretical analysis, a dynamic simulation has been done for a case where the spin frequency is 15 Hz. Experimental results with the proposed measurement method applied to a silicon micromachined gyro driven by a rotating aircraft demonstrate that it is effective in practical applications. Measured curve and numerical analysis of phase frequency characteristic are in accordance, and the error between measurement and simulation is only 5.3%.

https://www.mdpi.com/1424-8220/13/8/11051/pdf

Measurement of phase difference for micromachined gyros driven by rotating aircraft.

The bandwidth property of the dynamic characteristics of laser gyro has been researched in this work.The bandwidth characteristics of laser gyro were analyzed firstly and revealed that the laser gyro had a wide theoretical bandwidth.Then the factors affecting the actual bandwidth were analyzed and the bandwidth of the laser gyro was tested in practice.The laser gyro was installed in an IMU body,using sine excitation method in the test.According to the predetermined frequency and amplitude,a sine excitation was applied to the angle vibration table and the signal outputs of the laser gyro and the angle vibration table were collected respectively.The obtained data from each frequency point were processed with FFT algorithm and the important conclusions were obtained.To deeply investigate the dynamic characteristics of laser gyro,two vibration tables were chosen through the tests,and two styles of rigid connection and connection with vibration isolator were used between IMU and the test tool.The test data indicates that the bandwidth of laser gyro is higher than 120 Hz,according with the theoretical analysis,and fully satisfies the bandwidth requirements of modern missiles for laser gyro.This test can be used as reference for laser gyro signal filtering and laser IMU system design.

Yan Yuhui

Papers

Research on the Dynamic Characteristics of Laser Gyroscope(Part One)