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Design method for configuration-adjustable single-framework control moment gyro system

A technology for controlling moment gyroscopes and single frames, applied in computing, special data processing applications, instruments, etc., can solve problems such as deformation of the envelope of gyroscope angular momentum and abnormal operation of gyroscope groups, and achieve configuration efficiency and controllable benefits Improve the torque output capability and improve the effect of abnormal operation

Inactive Publication Date: 2012-07-25
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0006] The purpose of the present invention is to provide a single-frame control torque gyroscope with adjustable configuration to solve the problems of serious deformation of the angular momentum envelope of the gyroscope group and abnormal operation of the gyroscope group after some gyroscopes in the control moment gyroscope group of the traditional fixed structure fail. Gyro Group Design Method

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  • Design method for configuration-adjustable single-framework control moment gyro system
  • Design method for configuration-adjustable single-framework control moment gyro system
  • Design method for configuration-adjustable single-framework control moment gyro system

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Embodiment

[0032] A design method for a single-frame control moment gyroscope group with adjustable configuration of the present invention adopts a pyramid configuration structure composed of four single-frame control moment gyroscopes, and the device for realizing the method includes: a single-frame control moment gyroscope 1, a slide rail 4. On-board control module 5, locking module 2, positioning module 3, such as figure 1shown;

[0033] First, the slide rail is designed to be fixed to the spacecraft body, and each single-frame control moment gyro is slidingly connected to the slide rail through a positioning module, and the included angle β between the gyro frame axis of the four single-frame control moment gyros and the plane of the slide rail i (i=1, 2, 3, 4) are the same, both are 32.9°, such as figure 2 As shown, each single-frame control moment gyro is fixed with a locking module; the spaceborne control module is designed to connect with each single-frame control moment gyro, ...

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Abstract

The invention relates to a design method for a configuration-adjustable single-framework control moment gyro system, which belongs to the field of spacecraft attitude control. The method disclosed by the invention comprises the following steps of: firstly fixing a slide rail on the circumference of a connecting line at a position for fixing the single-framework control moment gyro system on an original spacecraft body, wherein all the single-framework control moment gyros are fixed with the slide rail and kept in symmetrical distribution relative to the slide rail, and the included angles between the gyro framework shafts of all the single-framework control moment gyros and a vertical line passing through the circle center of a plane of the slide rail are the same; and when the single-framework control moment gyro is failed, controlling the failed single-framework control moment gyro to close, and driving the rest effective single-framework control moment gyros to slide on the slide rail to keep the symmetrical distribution relative to the slide rail again. Through the design method disclosed by the invention, the changeability of an installation angle is introduced, the very limited utilization and control to the gyro after being failed at present are changed, the utilization ratio of the control moment gyro system is increased, and the operation abnormity problem of the gyrosystem is effectively improved.

Description

technical field [0001] The invention relates to a design method for a single-frame control moment gyro group with adjustable configuration, belonging to the field of spacecraft attitude control. Background technique [0002] At present, the actuators of the spacecraft attitude control system mainly include three categories: (1) thrusters; (2) flywheel actuators: including reaction wheels, (bias) momentum wheels, frame momentum wheels and control moment gyroscopes; (3) ) Environmental torque actuator. The Control Moment Gyro (CMG) can not only generate a large control moment, but also achieve high-precision attitude control without consuming non-renewable working fluid. It is an ideal actuator for spacecraft attitude control. Single frame control moment gyroscope (SGCMG) has become the best choice for sensitive small spacecraft attitude control actuator because it only generates control moment of one degree of freedom, simple structure, large output torque and good dynamic r...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
Inventor 张景瑞罗杨靳瑾
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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