Double-frame magnetic suspension control moment gyro

Abstract

The invention relates to a magnetic suspension controlled moment gyro with double frames, essentially consisting of a flywheel, an inner frame system and an outer frame system. The flywheel is arranged in the middle of the magnetic suspension controlled moment gyro with the double frames and essentially comprises a rotary shaft, a radial mixed magnetic bearing, an axial magnetic bearing, a radial displacement sensor, an axial displacement sensor, a high-speed motor and a gyro room; the inner frame system and the outer frame system essentially comprise the frames, a mechanical bearing, a moment motor, a reducer, an angle position sensor, a conductive slip ring a control system; the inner frame system is connected with a shaft hole on one end of the gyro room through the reducer and at the same time the conductive slip ring and the angle position sensor are connected with the shaft hole on the other end of the gyro room; the outer frame system is connected with a shaft hole on one end of the inner frame through the reducer and at the same time the conductive slip ring and the angle position sensor are connected with the shaft hole on the other end of the inner frame. The invention reduces noise, size and weight of the system through the mixed magnetic bearing, and eliminates bearing friction, and thus prolongs life span and promotes control accuracy of the controlled moment gyro.

Description

technical field [0001] The invention relates to a double-frame magnetic levitation control moment gyroscope, which can be used as an actuator for attitude control systems of large-scale spacecraft such as spacecraft and space stations that operate for a long time or require large maneuverability and quick response. Background technique [0002] The control moment gyro is a kind of inertial actuator applied to the spacecraft. It is mainly composed of a flywheel and a frame system. The direction of the angular momentum of the flywheel is controlled by the frame servo system, so that the gyro torque is output to control the attitude of the spacecraft. The attitude control actuators of spacecraft requiring large maneuverability and quick response and large spacecraft such as space stations require large output torque, long life, high reliability, fast response, high precision, small size, light weight, and low power consumption. This requires that the rotational speed of the fly...

AI Technical Summary

Problems solved by technology

As the supporting part of the flywheel rotor, the existing double-frame control moment gyroscope is supported by mechanical bearings, which fundamentally limits the increase of the rotor speed, reduces the service life and reliability of the system, and increases the power consumption, vibration and The noise is high and the control accuracy is low. In order to make the control moment gyro output the required angular momentum, the weight and volume of the control moment gyro have to be increased

Therefore, the main disadvantages of the existing dual-frame control moment gyroscopes are large volume and weight, low control accuracy, poor reliability, and relatively short service life.

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