Four-freedom-degree single-frame magnetic suspension control torque gyroscope

Abstract

A four-freedom-degree single-frame magnetic suspension control torque gyroscope can serve as a gesture control execution mechanism of a large satellite, an earth observation platform, a space station and other large spacecrafts and is composed of a four-freedom-degree magnetic bearing, a high-speed motor, a radial and axial integrated sensor, a radial sensor, an upper protective bearing, a lower protective bearing, a central spindle, a wheel body, a base, an upper sensor detection ring, a lower sensor detection ring, a shell, frame central spindles, a frame motor, a frame, mechanical bearings, an angle position sensor and an electric conduction sliding ring. The driving part of the four-freedom-degree magnetic bearing controls a gyroscope rotor to move in a translational mode and deflect, and the gyroscope rotor moves in a translational mode in the axial direction through the driven part of the four-freedom-degree magnetic bearing. All the components are compact in layout, the size and the weight are reduced, noise of a system is lowered, the size and the weight of the system are reduced, bearing friction force is eliminated, then the service life of the single-frame control torque gyroscope is prolonged, and the control precision of the single-frame control torque gyroscope is improved.

Description

technical field [0001] The invention relates to a single-frame magnetic levitation control moment gyroscope, which can be used as an actuator for attitude control systems of large spacecraft such as large satellites, earth observation platforms and space stations. Background technique [0002] Attitude control actuators of large spacecraft such as large satellites, earth observation platforms, and space stations require small size, light weight, long life, low power consumption, and high reliability. At present, the control torque gyroscope used as the actuator of the spacecraft attitude control system is generally still supported by mechanical bearings, which fundamentally limits the increase in the speed of the control torque gyroscope. Therefore, in order to achieve the required angular momentum, the control torque has to be increased. Gyro weight, increase volume. In addition, mechanical bearings have problems such as mechanical wear, uncontrollable unbalanced vibration...

AI Technical Summary

Problems solved by technology

At present, the control torque gyroscope used as the actuator of the spacecraft attitude control system is generally still supported by mechanical bearings, which fundamentally limits the increase in the speed of the control torque gyroscope. Therefore, in order to achieve the required angular momentum, the control torque has to be increased. Gyro weight, increase volume

In addition, mechanical bearings have problems such as mechanical wear, uncontrollable unbalanced vibration, and large zero-crossing friction torque, which seriously affect the service life of the control moment gyroscope and the accuracy and stability of spacecraft attitude control.

The existing single-frame magnetic suspension control torque gyroscope based on magnetic bearing support can be divided into single-degree-of-freedom single-frame magnetic suspension control torque gyroscope and five-degree-of-freedom single-frame magnetic suspension control torque , can reduce the volume of the control system and the overall quality of the control torque gyroscope, so the active and passive single-frame magnetic suspension control torque gyroscope has been widely used. The existing four-degree-of-freedom single-frame magnetic suspension control torque gyroscope is supported by two radial magnetic bearings , the axial lengths of the stator and rotor cores of the two radial magnetic bearings are exactly the same, and the axial "dislocation" between the stator and the rotor is used to realize the passive suspension of the control moment gyro rotor, and the current control of the two radial magnetic bearing coils is used , to control the radial translation of the torque gyro rotor and the control of four degrees of freedom in deflection, but the existing structure uses two radial magnetic bearings, and the axial dimension is greatly increased

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