Five-degree-of-freedom gyro case structure

Abstract

The invention discloses a five-degree-of-freedom gyro case structure. The five-degree-of-freedom gyro case structure mainly consists of a motor shaft, a single radical magnetic bearing, a repeatable type locking mechanism, an axial magnetic bearing, a motor, an upper gyro case, a coded disc shaft, a lower gyro case, a radial electrical eddy current sensor probe, a rotor outer hub, a lower protective bearing cover, an axial electrical eddy current sensor probe and a rotor inner hub, wherein a magnetic suspension bearing adopts the single radical bearing, and is used for controlling radical translation and rotation of a rotor. The repeatable type locking mechanism adopts a fire work pin puller to realize unlocking of the rotor when a spacecraft is in in-orbit operation, and meanwhile, a movable threaded chuck structure capable of manually adjusting degree of tightness is adopted, so that ground staff carries out installation and debugging for many times conveniently. The axial flow electrical eddy current sensor probe and the radical electrical eddy current sensor probe are fixedly mounted on the inner part of the gyro case, are integrated and are used for detecting the axial displacement and the radical displacement of the high-speed rotor respectively. According to the five-degree-of-freedom gyro case structure, the gyro case sensor is integrally designed and the single radical magnetic bearing is adopted, so that the gyro structure is simplified in structure, reduced in size, reduced in weight and relatively high in reliability.

Description

technical field [0001] The invention relates to a five-degree-of-freedom gyroscope structure, which is mainly used for controlling high-speed rotating components of inertial actuators such as moment gyroscopes. Background technique [0002] With the diversification of spacecraft missions, the attitude of spacecraft needs to be controlled with higher precision and higher stability. The dual-frame magnetic levitation control moment gyro is one of the executive components of the spacecraft control system. It can change the direction of the high-speed rotor angular momentum through the servo control system according to the spacecraft attitude control signal, thereby outputting the gyro torque to control the attitude of the spacecraft. [0003] The high-speed rotor has six rigid body degrees of freedom, three translations in the x, y, and z directions and rotation around the x, y, and z axes. The z-axis rotation in the five-degree-of-freedom gyroscope is controlled by the motor, ...

AI Technical Summary

Problems solved by technology

[0006] Therefore, the existing structure adopts radial magnetic bearings installed in pairs, which has a complex structure. The paired installation requires high installation accuracy and is inconvenient for multiple disassembly and assembly. The repeatable locking mechanism used in the existing structure requires power such as a motor The equipment and control system have a complex structure and a large volume. The sensors used in the existing structure are fixed inside the gyro room by the assembly relationship. The structure is complex, the volume is large, and the weight is heavy.

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