Magnetically suspended gyroscope flywheel

A magnetic levitation gyro and flywheel technology, which is applied in the direction of aerospace vehicle guides, etc., can solve the problem that the magnetic levitation flywheel can only be used as an attitude actuator but not an attitude sensitive mechanism, and achieve good performance.

Inactive Publication Date: 2010-05-19
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technical solution of the present invention is to overcome the problem that the existing magnetic levitation flywheel can only be used as an attitude actuator and cannot be used as an attitude sensitive mechanism, and provides a magnetic levitation gyro flywheel

Method used

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  • Magnetically suspended gyroscope flywheel
  • Magnetically suspended gyroscope flywheel
  • Magnetically suspended gyroscope flywheel

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Embodiment Construction

[0018] like figure 1 As shown, the present invention is composed of a stationary part and a rotating part. The stationary part includes: the stator part of the axial magnetic bearing 1, the seal cover 2, the stator part of the radial magnetic bearing 3, the upper protective bearing 4, the lock nut 5, the motor The stator part of 7, the displacement sensor 8, the installation shaft 9, the base 10 and the lower protective bearing 11; the rotating part includes: the rotor part of the axial magnetic bearing 1, the rotor part of the radial magnetic bearing 3, the flywheel rotor 6 and the motor 7 The rotor part; the rotor part of the axial magnetic bearing 1 is installed at the rim of the flywheel rotor 6, and the rotor part of the motor 7 is installed at the hub of the flywheel rotor 6, which is located at the radial inner side of the rotor part of the axial bearing 1, and the radial magnetic bearing 3 The rotor part is composed of radial magnetic bearing stator end cover 13 and ra...

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Abstract

The invention relates to a magnetically suspended gyroscope flywheel which can be used as a three-free degree attitude control actuator and a two-free degree attitude sensor of a spacecraft like a satellite and the like, and the magnetically suspended gyroscope flywheel mainly comprises a flywheel rotor, an axial magnetic bearing, a radial magnetic bearing, a protection bearing, a displacement sensor, a seal cover, a mounting shaft, a base, a motor, and other parts. The magnetic bearing is adopted for carrying out five-free degree suspension on the flywheel rotor, the flywheel rotor is driven to rotate around a rotating shaft by the motor, and the axial free degree control torque is outputted; the flywheel rotor is controlled to realize the torsion around an X axis or a Y axis of a housing by the axial magnetic bearing, and the radial two-free degree control torque is outputted; and the two-free degree attitude angular velocity of the spacecraft relative to inertia space can be sensed. The magnetically suspended gyroscope flywheel integrates the three-free degree attitude control actuator and the two-free degree attitude sensor of the spacecraft into a whole, thereby reducing the volume of an attitude control system of the spacecraft, reducing the weight of the attitude control system and being particularly applicable to being applied as the attitude control system of the spacecraft like the satellite and the like.

Description

technical field [0001] The invention relates to a magnetic levitation gyro flywheel, which is used in the attitude control system of spacecraft such as satellites, and simultaneously performs three-degree-of-freedom attitude control and is sensitive to the two-degree-of-freedom angular rate of the spacecraft. Background technique [0002] The attitude control system is an important subsystem of spacecraft such as satellites, and its attitude control performance directly affects the performance of the spacecraft. The demand for low power consumption, high reliability, and functional integration is becoming stronger and stronger. The attitude control system consists of two parts: an attitude sensitive mechanism and an attitude control actuator. For example, a three-axis stabilized satellite requires a three-degree-of-freedom angular rate-sensitive mechanism and a three-degree-of-freedom momentum exchange mechanism. The flywheel is the most important actuator for inertial atti...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/28
Inventor 房建成刘彬王志强李光军王曦刘刚
Owner BEIHANG UNIV
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