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Overall structure of a modular miniature control moment gyroscope

A technology of miniature control and torque gyroscope, which is applied in the direction of gyro effect for speed measurement, gyroscope/steering sensing equipment, instruments, etc. Effect of small size and simplified assembly process

Active Publication Date: 2019-10-22
BEIJING INST OF CONTROL ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Whether it is an ordinary gyro structure or a cantilever structure, both have the characteristics of complex structure and large size, which cannot meet the needs of miniature control moment gyroscopes

Method used

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  • Overall structure of a modular miniature control moment gyroscope
  • Overall structure of a modular miniature control moment gyroscope

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Embodiment Construction

[0016] Such as figure 1 As shown, the present invention provides a modular micro control moment gyroscope overall structure, including a frame rotor assembly 1, a connecting positioning ring 3, and a frame driving assembly 4; the frame rotor assembly 1 and the frame driving assembly 4 are positioned by connecting the positioning ring 3 Make sure that the frame rotor assembly 1 passes through the center of rotation of the frame drive assembly 4 without any adjustment.

[0017] The frame rotor assembly 1 and the frame drive assembly 4 are connected at one end, which can effectively reduce the number of components, reduce the volume and weight of the control torque gyroscope, and realize miniaturization and light weight.

[0018] Such as figure 2 As shown, the frame driving assembly 4 adopts the structure that the inner ring is fixed and the outer ring rotates; Lock nut 27, bearing 25 and frame motor 28 are formed;

[0019] The inner loading ring 24 and the outer loading ring...

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Abstract

the invention discloses an overall structure of a modular miniature control moment gyroscope overall structure. The modular miniature control moment gyroscope overall structure comprises a frame rotorassembly, a frame driving assembly and a connecting positioning ring. The frame driving assembly is composed of a rotating shell, a fixed shaft, an internal loading ring, an external loading ring, arotating shell locking nut, a fixed shaft locking nut, a bearing and a frame motor. An outer shell of the frame motor is installed in the fixed shaft. The frame rotor assembly and the frame driving assembly are positioned through the connecting positioning ring to ensure that the center of mass of a rotor is precisely in the rotating centre of the frame driving assembly. The rotating shell of theframe driving assembly, the frame rotor assembly and the connecting positioning ring are connected by screws. An output shaft of the frame motor of the frame driving assembly is connected with a frameof the frame rotor system and fixed through a connecting top wire. The modular miniature control moment gyroscope overall structure can realize rapid manufacturing, rapid assembly and rapid test, caneffectively reduce the weight and the contour dimension of the control moment gyroscope, and can ensure that the center of mass of the frame rotor assembly is precisely in the rotating center of theframe driving assembly.

Description

technical field [0001] The invention relates to an overall structure of a modular miniature control moment gyroscope, in particular to a miniature control moment gyroscope capable of realizing rapid manufacturing, rapid assembly and rapid testing. Background technique [0002] The control moment gyro belongs to the attitude control execution part of the spacecraft. It is the most ideal attitude control execution part of the long-life and high-precision spacecraft, and it is also the ideal attitude control execution part of the agile satellite platform with attitude maneuvering requirements. The United States and Russia carried out the research and development of the control moment gyroscope as early as the 1950s, and since the 1960s, the developed control moment gyroscope has been successfully applied to large-scale space stations such as the Mir space station, the sky laboratory and the international space station. on the spacecraft. [0003] At present, there are two stru...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C19/00B64G1/28
Inventor 李刚来林田兴武登云伏蓉魏大忠闫素娜刘景辉
Owner BEIJING INST OF CONTROL ENG
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