Electric magnetic suspension double-frame momentum ball device

Abstract

The invention discloses an electric magnetic suspension double-frame momentum ball device which is used for a spacecraft attitude control system executing mechanism. The electric magnetic suspension double-frame momentum ball device is composed of an electric magnetic suspension driving motor module, an inner adjusting frame, an outer adjusting frame and an end bearing locking mechanism, wherein the electric magnetic suspension driving motor module is connected with the inner adjusting frame through a shaft and the bearing locking mechanism; and the inner adjusting frame is connected with theouter adjusting frame through the shaft and the bearing locking mechanism. The electric magnetic suspension driving motor module is composed of two layers of parallel stator arrays, a spherical rotorand a center retainer. The sinusoidal alternating current of different frequencies, amplitudes and phases is applied to a stator coil to form rotating magnetic fields in different directions, rotationdriving is achieved while the spherical rotor is driven to stabilize the magnetic suspension; and according to the principle of angular momentum conservation, and the locking and unlocking functionsof the bearing locking mechanism are switched, the three-axis stability and controllability of the spacecraft attitude are realized.

Description

technical field [0001] The invention belongs to the technical field of spacecraft, in particular to an electric magnetic levitation double-frame momentum ball device, which is used as an actuator of a spacecraft attitude control system. Background technique [0002] At present, momentum wheels and control moment gyroscopes are generally used as the actuators of spacecraft attitude control systems such as artificial satellites. [0003] However, a single flywheel can only provide attitude control relative to a specific direction of the spacecraft. Therefore, at least three momentum flywheels are required to achieve complete controllability of the three-axis attitude of the spacecraft. Usually 4 to 6 momentum flywheels are configured to achieve fault-tolerant design and control algorithm optimization, so it takes up a large space volume. The control torque gyro uses an additional torque motor to drive the frame to rotate and adjust the spatial orientation of the frame. Howeve...

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Problems solved by technology

[0005] The patent application number CN201410384117.4 "a four-degree-of-freedom dual-frame magnetic levitation control torque gyroscope" and the patent application number CN200710304236.4 "dual-frame magnetic levitation control torque gyroscope" have proposed a multi-degree-of-freedom dual-frame control torque gyroscope, However, its structure is complicated, and a torque motor is installed at the end of the frame to drive the frame to rotate, and the torque motor is relatively large, so that the entire double-frame magnetic levitation control torque gyro occupies a large space volume

The patent "A Magnetic Suspension Spherical Gyro Flywheel with Inner Rotor" with the application number CN201510813055.9 uses a spherical magnetic bearing as a supporting component, which can realize the active suspension of the maglev gyro flywheel with five degrees of freedom, but the adjustment range of the direction of the rotor shaft is limited.

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