Satellite Vibration Elimination Method and System

Abstract

This patent discloses a satellite vibration elimination system and method. The system includes a satellite vibration elimination device, which mainly includes: an upper flange, a middle flange and a lower flange. Between the lower surface of the upper flange and the upper surface of the middle flange, four first-group driving devices are arranged at intervals of 90 degrees; between the lower surface of the middle flange and the upper surface of the lower flange are arranged There are four second sets of drive means at 90 degree intervals; a 45 degree phase angle between said first set of drive means and said second set of drive means; a control means that converts low frequency vibrations into power plant drive signal. The transmission of high-frequency vibration can be reduced by the above solution, and the working life of the device can be improved.

Description

technical field [0001] The invention relates to satellite technology, in particular to a satellite vibration elimination device and a satellite vibration elimination method. Background technique [0002] The problem of vibration elimination of optical satellites is a common problem in the prior art. Since the movement of various components in the satellite will cause vibrations and this vibration can be easily transmitted in the vacuum of space, it will cause significant damage to the shooting of optical satellites. influences. [0003] In the prior art, better solutions have been proposed for isolation of satellite vibrations. For example, CN106218920A has provided a satellite vibration isolation device and method. This method can effectively isolate satellite vibrations to improve the shooting effect of satellites. It uses flexible hinges to solve high-frequency vibration isolation, and uses power devices to offset low-frequency vibrations, which has played a very good ro...

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Problems solved by technology

[0004] However, the above-mentioned solutions in the prior art have the following problems, that is, when isolating low-frequency vibrations, there is actually a rigid connection between the upper flange, the lower flange, and the power unit. Although the low-frequency vibrations can be better offset at this time, the High-frequency vibration will be transmitted to the satellite payload through a rigid connection to cause optical axis jitter

[0005] And due to the repetitiveness and periodicity of low-frequency vibration, the power unit often performs repetitive operations when counteracting low-frequency vibration, which causes the hinge to be easily fatigued and accelerates the damage of components, which affects the life of the overall system

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