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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, and achieve the effect of reducing the volume

Inactive Publication Date: 2020-06-12
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] like 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. The first driving device and the first flywheel body 12 drive connection to drive the first flywheel body 12 to rotate, the second drive device is drive-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] In 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, the weight can be distributed at a position far from the rotation center, thereby increasing the size of the second flywheel body 22 Relative to the moment of inertia of the rotation center, relative to the axial series arrangement of two flywheels,...

Embodiment 2

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

[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, which is not repeated here.

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

[0048] That is, the spin axis of each flywheel pair is parallel to one axis of the whole star body, which realizes the one-to-one correspondence between the flywheel pair and the attitude control channel of the whole star. Tha...

Embodiment 3

[0053] like 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, which is not repeated here.

[0055] In addition, each flywheel pair is installed close to the whole star's wall plate, which shortens the force transmission path between the flywheel body and the whole star structure, which not only reduces the loss of power during the transmission process, but also reduces the influence of 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 particularly relates to a satellite attitude control flywheel pair, a satellite attitude control system comprising the satellite attitude control flywheel pair and a satellite comprising the satellite attitude control system. The satellite attitude controls the flywheel pair comprises a first flywheel body, a second flywheel body, a first driving device and a second driving device, wherein the first driving device is in transmission connection with the first flywheel body to drive the first flywheel body to rotate, the second driving 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 radial outer side of the second flywheel body. According to the satellite attitude control flywheel pair provided by the invention, the technical problems of large occupied space and disturbance caused by zero-crossing of the rotating speed of a flywheel pair in the prior art can be solved, the space occupied by the flywheel pair is reduced under the condition of ensuring the moment of inertia, and the satellite attitude control precision is improved.

Description

technical field [0001] 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 above-mentioned satellite attitude control flywheel pair, and a satellite including the above-mentioned satellite attitude control system. Background technique [0002] With the continuous improvement of the satellite on-orbit attitude control accuracy and stability index, the reaction flywheel has become the main actuator for attitude control during long-term on-orbit operation. As an angular momentum exchange device, the reaction flywheel has a direct corresponding relationship between the output active control torque and the input current / voltage, which can achieve extremely high attitude control accuracy and stability; the operation of the flywheel only consumes on-board electric energy, which can be controlled by The continuous supply of solar panels is beneficial to ...

Claims

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Application Information

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Patent Type & Authority Applications(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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