DISTURBED MOVEMENT OF THE MOVING PART OF THE GYRO SUSPENSION

Abstract

The development of hypersonic technology creates a new challenge for inertial navigation sensors, which are widely used in aviation navigation systems. Improving the accuracy of navigation equipment will reduce fuel consumption and reduce the impact of harmful emissions on the atmosphere. The operation of sensors that are part of navigation systems, such as gyroscopes, work in difficult conditions, which affects their accuracy. A float two-degree angular velocity sensor is considered. The reaction of a float two-stage angular velocity sensor to a simultaneous perturbation from the side of the hull - a kinematic perturbation - and penetrating acoustic radiation from the side of the rocket propulsion engines is determined. The article establishes when there is no penetrating acoustic effect, as well as the determining relationship between the steady angle of rotation of the float and a constant input value. The determination of the zero shift of the device, due only to the angular vibrations of the body and penetrating acoustic radiation, that is, in the absence of circulation on the trajectory, is analyzed. The response of a float gyroscope to the harmonic oscillations of the base is analyzed. The effect of zero shift of the device, caused only by angular vibrations of the launch vehicle body and penetrating acoustic radiation, is considered.