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

A control torque gyroscope, support type technology, applied in the direction of rotating gyroscope, aerospace vehicle guidance device, etc., can solve the problems of large volume and weight, affecting the stability of spacecraft, large mechanical interface, etc., to reduce the combined area, Improve reliability and service life, increase the effect of speed

Inactive Publication Date: 2008-09-17
BEIHANG UNIV
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  • Application Information

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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 moment, which affects the stability of the spacecraft; the existing single-frame control moment gyroscopes are supported at both ends, such as attached figure 1 , the frame system has two support points (support point 1, 2), the frame system of the control moment gyroscope of this structure needs to provide the turning space for the rotor system, so the volume and weight of the frame system are relatively large, and it is different from the satellite’s mechanical The interface is also relatively large, not suitable for control torque gyroscopes with small and medium torque output

Method used

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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

[0018] like figure 2 , the present invention is mainly composed of a magnetic levitation rotor system and a 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, The protective bearing 6, the drive motor 7, and the gyro room 8 are composed of two drive motors 7 located in the middle of the magnetic levitation rotor system, and the two sides are radial magnetic bearing 3, radial displacement sensor 4, protective bearing 6, shaft To the displacement sensor 5, two axial magnetic bearings 2 are located outside the radial direction of the drive motor 7, 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, and the rest are The stator assembly, the stable suspension of non-mechanical contact is realized between...

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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 moment,...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C19/24B64G1/28
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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