Single end support type magnetic suspension control moment gyro of single framework

A technology for controlling moment gyroscopes and single frames, which is applied in the direction of aerospace vehicle guides, etc., can solve the problems of large size and weight of the frame system, affecting the stability of spacecraft, and large mechanical interfaces of satellites, so as to reduce the volume and weight, Effects of improving reliability and service life and eliminating frictional torque

Inactive Publication Date: 2007-10-10
BEIHANG UNIV
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AI Technical Summary

Problems solved by technology

The existing single-frame control moment gyroscope and the gyroscope rotor system are all supported by mechanical bearings. Due to the wear of the mechanical bearings, there are still many restrictions on the speed and service life. The system brings a disturbing torque, thereby affecting the stability of the spacecraft; the existing single frame control moment gyroscope adopts the mode of two-end support, as shown in Figure 1, the frame system has two support points (support points 1, 2) , the frame system of the control moment gyroscope with this structure needs to provide a turning space for the rotor system, so the volume and weight of the frame system are relatively large, and the mechanical interface with the satellite is also relatively large, which is not suitable for the control moment gyroscope with small and medium torque output

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  • Single end support type magnetic suspension control moment gyro of single framework
  • Single end support type magnetic suspension control moment gyro of single framework
  • Single end support type magnetic suspension control moment gyro of single framework

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Embodiment Construction

[0017] As shown in Figure 2, the present invention is mainly composed of two parts, the magnetic levitation rotor system and the frame system, wherein the magnetic levitation rotor system is mainly composed of a gyro rotor 1, an axial magnetic bearing 2, a radial magnetic bearing 3, a radial displacement sensor 4, an axial displacement Sensor 5, protective bearing 6, driving motor 7, and gyro room 8. Two driving motors 7 are located in the middle of the magnetic levitation rotor system, and the two sides are radial magnetic bearing 3, radial displacement sensor 4, and protective bearing in sequence from the inside to the outside. 6. Axial displacement sensor 5, two axial magnetic bearings 2 are located on the outside of the drive motor 7 in the radial direction, wherein the gyro rotor 1, the radial magnetic bearing 3 rotor part and the drive motor 7 rotor part form the rotor assembly of the magnetic levitation rotor system , the rest is the stator assembly, the stable suspensio...

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Abstract

A single end supported single-frame magnetic-levitation torque-controlling gyro is composed of magnetically levitated rotor system and frame system. Said magnetically levitated rotor system consists of gyro rotor, axial and radial magnetic bearings, and axial and radial displacement sensors, protecting bearing, drive motor and gyro room. Said frame system comprises frame jointer, end covers, mandrel, torque motor, angular position sensor, electrically conductive slide ring, mechanical bearing, and base. It has high rotation speed and long service life.

Description

technical field [0001] The invention relates to a single-end supported single-frame magnetic levitation control moment gyroscope, which can be used for large-angle maneuvering attitude control of small and medium-sized spacecraft such as small satellites or microsatellites. Background technique [0002] Modern satellite platforms or small spacecraft used in earth observation or scientific research put forward higher and higher requirements for stability and flexibility of large-angle maneuvering. Satellites capable of large-angle maneuvering can improve the efficiency of earth observation and quality. The single-frame control moment gyro is one of the main actuators used for attitude control of spacecraft. The existing single-frame control moment gyroscope and the gyroscope rotor system are all supported by mechanical bearings. Due to the wear of the mechanical bearings, there are still many restrictions on the speed and service life. The system brings a disturbing torque,...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/28
Inventor 房建成韩邦成叶全红刘刚魏彤孙津济刘珠荣
Owner BEIHANG UNIV
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