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Flywheel zero-crossing avoidance method for remote sensing satellite

A flywheel and satellite technology, applied in the aerospace field, can solve the problems of light weight, low cost, increased flywheel production cost and production difficulty, etc., to improve the stability of data production, reduce the probability of flywheel zero crossing, and simple principle Effect

Pending Publication Date: 2021-12-21
CHANGGUANG SATELLITE TECH CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Among them, the first strategy will increase the production cost and difficulty of flywheels, which is not in line with the current trend of lightweight and low-cost commercial aerospace

Method used

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  • Flywheel zero-crossing avoidance method for remote sensing satellite
  • Flywheel zero-crossing avoidance method for remote sensing satellite
  • Flywheel zero-crossing avoidance method for remote sensing satellite

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Embodiment Construction

[0059] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them; based on this The embodiments in the invention, and all other embodiments obtained by persons of ordinary skill in the art without creative efforts, all belong to the scope of protection of the present invention.

[0060] to combine Figure 1 to Figure 3 ,

[0061] A flywheel zero-crossing avoidance method for remote sensing satellites,

[0062] Described method specifically comprises the following steps:

[0063] Step 1, calculate the whole star angular momentum vector under the satellite's own system during the sun mode;

[0064] Step 2, calculate the whole star angular momentum vector in the reference frame:

[0065] Step 3, calculate the rotational sp...

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Abstract

The invention provides a flywheel zero-crossing avoidance method for a remote sensing satellite. The method specifically comprises the following steps: calculating a whole satellite angular momentum vector under a satellite body system during a sun-facing mode; calculating a whole satellite angular momentum vector under a reference system: calculating the rotating speed of a three-axis flywheel when the satellite is imaged to the ground, and judging a zero-crossing condition according to the rotating speed of the three-axis flywheel; during the sun-facing mode, carrying out the steps 1 to 3, calculating the number of zero-crossing times of imaging of the sun-facing rotating speed in the core area, and calculating the optimal sun-facing rotating speed; and by establishing the conversion relation of the two mode postures, setting the flywheel rotating speed in the sun-facing mode, and enabling the flywheel rotating speed in the ground mode to be away from the zero point.

Description

technical field [0001] The invention belongs to the technical field of aerospace, and in particular relates to a flywheel zero-crossing avoidance method for remote sensing satellites. Background technique [0002] The reaction flywheel (hereinafter referred to as "flywheel") is the main executive component of the satellite attitude control system. Its main function is to generate reaction torque through the change of rotational speed to realize the maneuver or stability control of the satellite attitude. [0003] When the flywheel works near zero speed, its speed switches between positive and negative, and the friction torque will change direction and undergo a step jump, resulting in insufficient flywheel speed control ability, resulting in jitter. Flywheel zero crossing will greatly reduce attitude control accuracy. For high-resolution remote sensing satellites, the zero crossing of the flywheel may cause image data to be blurred, distorted, false-colored, and even the im...

Claims

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Application Information

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IPC IPC(8): B64G1/28B64G1/24
CPCB64G1/283B64G1/244Y02E60/16
Inventor 刘洁冰陈茂胜戴路范林东韩霜雪
Owner CHANGGUANG SATELLITE TECH CO LTD