Method of stably controlling spacecraft attitudes through internal vibration isolation structure

A technology for stability control and spacecraft, applied in attitude control and other directions

Active Publication Date: 2016-01-20
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to solve the problem that the vibration generated by the control moment gyroscope can be effectively suppressed without adding additional volume, thereby improving the performance of spacecraft attitude control. Methods

Method used

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  • Method of stably controlling spacecraft attitudes through internal vibration isolation structure
  • Method of stably controlling spacecraft attitudes through internal vibration isolation structure
  • Method of stably controlling spacecraft attitudes through internal vibration isolation structure

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Embodiment 1

[0097] An internal vibration isolation structure of a control moment gyroscope, which is composed of a plurality of flexible support structures 1; the flexible support structure 1 is located between the rotor 2 and the frame 3 and between the frame 3 and the spacecraft; when the control moment gyroscope is working, the flexible support The structure 1 will then start to produce a vibration isolation effect, thereby suppressing the disturbance generated by the rotor 2.

[0098] The number of the plurality of flexible support structures 1 is at least four, two of which are fixedly connected between the rotor 2 and the frame 3, and the other two are fixedly connected between the frame 3 and the spacecraft;

[0099] The flexible support structure includes a rigid support part 4 and a flexible deformation part 5, and the rigid support part 4 and the flexible deformation part 5 are fixedly connected;

[0100] The rigid supporting part 4 is made of titanium alloy material; the flexib...

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Abstract

The invention relates to a method of stably controlling spacecraft attitudes through an internal vibration isolation structure, belonging to the high frequency vibration control field. The internal vibration isolation structure is composed of a plurality of flexible supporting structures which are arranged between a rotor and a framework, and between the framework and a spacecraft. When a control moment gyroscope operates, the flexible supporting structures start to isolate vibration so as to restrain the disturbance generated by the rotor. Part of the flexible supporting structures are fixedly connected between the rotor and the framework, and the rest part of the flexible supporting structures are fixedly connected between the framework and a spacecraft. The internal vibration isolation structure can effectively solve the vibration problem of a single gimbal control moment gyroscope, and possess a decoupling characteristic so as to effectively and rapidly realize the parameter design of vibration isolation elements; in addition, the vibration isolation elements can greatly improve satellite attitude stability.

Description

technical field [0001] The invention relates to a method for realizing stable attitude control of a spacecraft through an internal vibration isolation structure, and belongs to the field of high-frequency vibration control. Background technique [0002] At present, the main vibrating components on spacecraft are actuators with high-speed rotors such as flywheels or control moment gyroscopes. Their vibration is mainly caused by the static and dynamic unbalance of the high-speed rotor and the installation error of the mechanical bearing, and the resulting vibration will directly affect the imaging quality of the optical load. Combining a Design Method of Flywheel Attitude Control System for Flexible Aircraft (Geng Yunhai, Cui Hutao, Cui Haiying, Yang Di. Design of Flywheel Attitude Control System for Flexible Aircraft[J]. System Engineering and Electronic Technology. 2001, 23(6) :55-58), and adding the vibration generated by the flywheel, it can be known that the attitude acc...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
Inventor 张景瑞郭子熙李文博王有懿张尧
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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