Completely non - contacting magnetic suspension control moment gyro of single framework

A technology for controlling torque gyroscopes and magnetic levitation, which is applied to the guidance devices of space navigation vehicles, etc., can solve the problems of large size and weight of the frame system, affect the stability of the spacecraft, and interfere with the spacecraft system, so as to reduce the size and weight, improve the Reliability and service life, the effect of reducing the bonding area

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, the gyroscope rotor system and the frame 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 of the rotor system. At the same time, due to the friction torque of the mechanical shaft of the frame system It is non-linear, which will bring a disturbance torque to the spacecraft system, thereby affecting the stability of the spacecraft; the existing single-frame control moment gyroscopes are supported at both ends, as shown in Figure 1, the frame system has two support points (support points 1 and 2), the frame system of the control moment gyroscope of 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 relatively large. Not suitable for control torque gyroscope with small and medium torque output

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  • Completely non - contacting magnetic suspension control moment gyro of single framework
  • Completely non - contacting magnetic suspension control moment gyro of single framework
  • Completely non - contacting magnetic suspension control moment gyro of single framework

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Embodiment Construction

[0022]As shown in Figure 2, the present invention is mainly composed of two parts: a magnetic levitation rotor system and a magnetic levitation frame system, wherein the magnetic levitation rotor system is mainly composed of a sealing cover 1, a gyro rotor 2, a radial magnetic bearing 3, a left axial magnetic bearing 4, and a protective bearing 5 , shaft seat 6, rotor system radial / axial integrated displacement sensor 7, rotor system base 8, drive motor 9, rotor system connector 10, right axial magnetic bearing 11, of which gyro rotor 2, radial magnetic bearing 3 The rotor part, the driving motor 9 The rotor part, the left axial magnetic bearing 4 The rotor part, the right axial magnetic bearing 11 The rotor part constitutes the rotor assembly of the magnetic levitation rotor system, the rest is the stator assembly, and the stator assembly and the rotor assembly are connected by a radial The magnetic bearing and the axial magnetic bearing realize stable suspension without mecha...

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Abstract

A fully non-contact single-frame magnetic- levitation torque-controlling gyro is composed of magnetically levitated frame system and magnetically levitated rotor system. Said magnetically levitated frame system consists of frame jointer, protecting bearing, mandrel, torque motor, angular position sensor, radial and axial magnetic bearings, integrated radial / axial displacement sensor, electrically conductive slide ring and base. Said magnetically levitated rotor system comprises gyro rotor, axle holder, axial and radial magnetic bearings, integrated radial / axial displacement sensor, protecting bearing, drive motor, sealing cover, base and jointer.

Description

technical field [0001] The invention relates to a completely non-contact single-frame magnetic levitation control moment gyroscope, which can be used for attitude control of large spacecraft such as space stations or small spacecraft such as agile maneuvering satellites. Background technique [0002] Modern satellite platforms or small spacecraft used in earth observation or scientific research have higher and higher requirements for stability and flexibility of maneuvering at large angles. Satellites that can maneuver at large angles can improve the efficiency and quality of Earth observation. 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, the gyroscope rotor system and the frame 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 of the rotor system. At the s...

Claims

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Application Information

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IPC IPC(8): B64G1/28
Inventor 房建成叶全红孙津济韩邦成刘刚魏彤
Owner BEIHANG UNIV
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