A four-degree-of-freedom magnetic levitation flywheel

Abstract

The invention discloses a four-degrees-of-freedom magnetic suspension flywheel. The four-degrees-of-freedom magnetic suspension flywheel is capable of being used as an attitude control execution mechanism for spacecrafts of a satellite, an earth observation platform, a space telescope and the like, and is composed of a four-degrees-of-freedom magnetic bearing, a high-speed motor, a radial-axial integrated sensor, a radial sensor, an upper protection bearing, a lower protection bearing, a mandrel, a wheel body, a base, an upper sensor detection ring, a lower sensor detection ring and a shell, wherein the active portion of the four-degrees-of-freedom magnetic bearing controls the radial translation and deflection of the rotor of the flywheel, and the axial translation of the rotor of the flywheel is realized through the passive portion of the four-degrees-of-freedom magnetic bearing. Each component of the four-degrees-of-freedom magnetic suspension flywheel disclosed by the invention is compact in layout, thus reducing the volume and weight, eliminating the rotational speed zero-passage friction force and mechanical wear of the flywheel of the mechanical bearing, improving the control accuracy of the flywheel and prolonging the service life of the flywheel.

Description

technical field [0001] The invention relates to a magnetic levitation flywheel, which can be used as an actuator for attitude control systems of spacecraft such as satellites, earth observation platforms, spaceships and space telescopes. Background technique [0002] Attitude control actuators of spacecraft such as satellites, earth observation platforms, spacecraft, and space telescopes require small size, light weight, long life, low power consumption, and high reliability. At present, the flywheel 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 flywheel. Therefore, in order to achieve the required angular momentum, the weight and volume of the flywheel have to be increased. . In addition, mechanical bearings have problems such as mechanical wear, unbalanced vibration, and large zero-crossing friction torque, which seriously affect the service li...

AI Technical Summary

Problems solved by technology

At present, the flywheel 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 flywheel. Therefore, in order to achieve the required angular momentum, the weight and volume of the flywheel have to be increased.

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

The existing maglev flywheels based on magnetic bearing support can be divided into single-degree-of-freedom maglev flywheels to five-degree-of-freedom maglev flywheels according to the degree of freedom of suspension. Due to the small number of degrees of freedom in suspension, the volume of the control system and the overall quality of the flywheel can be reduced. Therefore, active and passive magnetic suspension flywheels have been widely used. The existing four-degree-of-freedom magnetic suspension flywheel 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. The axial "displacement" between them realizes the passive suspension of the flywheel rotor, and uses the current control of two radial magnetic bearing coils to realize the radial translation and deflection control of the four degrees of freedom of the flywheel rotor, but the existing structure uses two Radial magnetic bearings with greatly increased axial dimensions

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