Satellite attitude control flywheel pair, satellite attitude control system and satellite

A satellite attitude control and attitude controller technology, applied in the satellite field, can solve the problem of large space occupied by the flywheel group

Inactive Publication Date: 2021-10-15
北京微动航科技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Aiming at the defects in the prior art, the present invention provides a flywheel pair for satellite attitude control, which can solve the technical problem that the flywheel set in the prior art takes up a large space

Method used

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  • Satellite attitude control flywheel pair, satellite attitude control system and satellite
  • Satellite attitude control flywheel pair, satellite attitude control system and satellite
  • Satellite attitude control flywheel pair, satellite attitude control system and satellite

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0028] Such as figure 1 As shown, a satellite attitude control flywheel pair provided in this embodiment includes a first flywheel body 12 and a second flywheel body 22, and a first driving device and a second driving device, and the first driving device and the first flywheel body 12 transmission connection to drive the first flywheel body 12 to rotate, the second driving device is connected to the second flywheel body 22 to drive the second flywheel body 22 to rotate, the first flywheel body 12 is arranged in the radial direction of the second flywheel body 22 outside.

[0029] The satellite attitude control flywheel pair provided in this embodiment, by arranging the first flywheel body 12 on the outside of the second flywheel body 22, can distribute the weight at a position farther away from the rotation center, thereby increasing the size of the second flywheel body 22 Compared with the moment of inertia of the rotation center, compared with the axial series layout of two...

Embodiment 2

[0045] Such as figure 2 As shown, the satellite attitude control system provided in this embodiment includes any one of the satellite attitude control flywheel pairs described above.

[0046] Since the satellite attitude control system provided in this embodiment includes the above-mentioned satellite attitude control flywheel pair, it has the technical effect of the above-mentioned satellite attitude control flywheel pair, and will not be repeated here.

[0047] In a preferred embodiment, the number of satellite attitude control flywheel pairs is three pairs, specifically, including the first flywheel pair 41, the second flywheel pair 42, and the third flywheel pair 43, and the three pairs of satellite attitude control flywheel pairs are vertically arranged in pairs.

[0048] That is to say, the spin axis of each flywheel pair is parallel to the first axis of the whole star body, realizing the one-to-one correspondence between the flywheel pair and the attitude control chann...

Embodiment 3

[0053] Such as image 3 As shown, the satellite provided in this embodiment includes the above-mentioned satellite attitude control system.

[0054] Since the satellite provided in this embodiment includes the above-mentioned satellite attitude control system, it has the technical effect of the above-mentioned satellite attitude control system, and will not be repeated here.

[0055] In addition, each flywheel pair is installed close to the wall plate of the whole star, which shortens the force transmission path between the flywheel body and the whole star structure, not only reduces the loss of power during the transmission process, but also reduces the satellite attitude control system. The occupied space leaves plenty of room for other equipment layouts.

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Abstract

The invention belongs to the technical field of satellites, and in particular relates to a satellite attitude control flywheel pair, a satellite attitude control system including the satellite attitude control flywheel pair and a satellite including the satellite attitude control system. Wherein, the satellite attitude control flywheel pair includes a first flywheel body and a second flywheel body, and a first drive device and a second drive device, and the first drive device is connected with the first flywheel body to drive the first flywheel body to rotate , the second drive device is in transmission connection with the second flywheel body to drive the second flywheel body to rotate, and the first flywheel body is arranged on the radially outer side of the second flywheel body. The satellite attitude control flywheel pair provided by the present invention can solve the technical problems that the flywheel pair in the prior art takes up a large space and the disturbance caused by the zero-speed crossing of the rotation speed, and can reduce the space occupied by the flywheel pair while ensuring the moment of inertia, and improve the efficiency of the satellite. Attitude control precision.

Description

technical field [0001] The invention belongs to the technical field of satellites, in particular to a satellite attitude control flywheel pair, a satellite attitude control system including the satellite attitude control flywheel pair and a satellite including the satellite attitude control system. Background technique [0002] With the continuous improvement of satellite attitude control accuracy and stability indicators, the reaction flywheel has become the main actuator of attitude control during long-term on-orbit operation. As an angular momentum exchange device, the reaction flywheel has a direct relationship between the output active control torque and the input current / voltage, which can achieve extremely high attitude control accuracy and stability; The continuous supply of solar panels is conducive to improving the life of satellites in orbit. [0003] At present, most of the flywheels used for satellite attitude control adopt the configuration of "three orthogona...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/28
CPCB64G1/283
Inventor 姜亮
Owner 北京微动航科技术有限公司
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