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Satellite attitude control method and system

A technology for satellite attitude control and moving parts, which is applied in the directions of artificial satellites, aerospace vehicles, transportation and packaging, etc., can solve the problem of difficult control methods, and achieve the effect of simple and easy engineering implementation and improved stability.

Active Publication Date: 2022-06-28
INNOVATION ACAD FOR MICROSATELLITES OF CAS +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] The purpose of the present invention is to provide a satellite attitude control method and system to solve the problem that the existing control method for eliminating the influence of moving parts on the satellite on the satellite attitude is difficult

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  • Satellite attitude control method and system
  • Satellite attitude control method and system
  • Satellite attitude control method and system

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Embodiment Construction

[0061] The satellite attitude control method and system proposed by the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. The advantages and features of the present invention will become apparent from the following description and claims. It should be noted that, the accompanying drawings are all in a very simplified form and in inaccurate scales, and are only used to facilitate and clearly assist the purpose of explaining the embodiments of the present invention.

[0062] Furthermore, unless stated otherwise, features in different embodiments of the invention may be combined with each other. For example, a feature in the second embodiment may be replaced with a corresponding feature in the first embodiment with the same or similar function, and the resulting embodiment also falls within the scope of disclosure or description of the present application.

[0063] The core idea of ​​the present inve...

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Abstract

The invention provides a satellite attitude control method and system, including: according to the motion law and interference characteristics of the moving parts on the star, setting the feedforward compensation torque, and calculating the advance compensation time; according to the motion law of the moving parts on the star, obtaining the commutation At the end of the process; according to the end of the commutation process, the advance compensation time and the theoretical motion curve, select the end threshold of the feedforward compensation torque angular velocity and the start threshold of the angle; read the angle and angular velocity information of the moving parts on the star in real time, and arrive at the At the moment of deceleration, the feedforward compensation torque is applied to the satellite and lasts until the first threshold time, so that the satellite obtains the threshold compensation angular momentum; The angular momentum is equal in magnitude.

Description

technical field [0001] The invention relates to the technical field of spacecraft attitude control, in particular to a satellite attitude control method and system. Background technique [0002] Remote sensing satellites often have moving parts, such as scanning mirrors, pendulum mirrors, turntables, etc. The movement of moving parts on the satellite will affect the accuracy and stability of the satellite's attitude control, which in turn affects the pointing accuracy and pointing stability of the moving parts and loads. [0003] For the interference of moving parts that move according to specific rules, typically such as scanning mirrors and pendulum mirrors that perform periodic reciprocating motions according to a certain designed motion curve, the methods that can be used include motion compensation of moving parts, feedforward torque compensation, etc. [0004] Compensation of existing moving parts requires an additional balance wheel or a dedicated torque compensation ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24B64G1/10
CPCB64G1/244B64G1/245Y02T10/72
Inventor 阳应权谢祥华杨光王磊陈宏宇付碧红黄志伟张锐严玲玲赵璟本立言
Owner INNOVATION ACAD FOR MICROSATELLITES OF CAS