The response of the float two-stage angular velocity sensor to the simultaneous perturbation from the rocket body—kinematic perturbation—and the penetrating acoustic radiation from the propulsion engines of the launch vehicle were determined. The solution of two equations was successively analyzed: the first and second approximations, and the synchronous and asynchronous fuselage pitch. The reaction of the float gyroscope to harmonic oscillations of the base was analyzed. The effect of the zero shift of the device due only to the angular oscillations of the launch vehicle body and the penetrating acoustic radiation was considered. The presented results reveal the nature of the appearance of inertia forces acting on the impedance surface of the gyroscope float suspension. Acoustic radiation that passes into a device generates many vibration modes on the surface and can have a considerable effect on the precision of float two-stage angular velocity sensor and gyro-stabilized platforms.
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.
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