Dynamic drift of gas gyro under sweep-frequency vibration mode

Abstract

Gas gyro is an inertial gyro which measures the attitude angle of missile body by using propellant gas to drive for realizing the sample contro1 of airframe attitude. Based on the characteristics of high-speed rotor, the gyro can measure the attitude of the airframe directly through the gyro's frame deviation. Using Euler movement equations, we deduce the mechanical gyroscope measurement principle and the causes of drift, and analyze the effect of friction torque, unbalanced torque, and external moment on the gyro drift. The sweep-frequency vibration test is designed which find the sensing frequency of the gas gyro under the applied torque. The test show that the gyro drift of more than 3° can be reduced to 0.5° under 400~800 Hz sensitive frequencies through improving the assemble condition of the missile body.