Authors
Ho-Nien Shou*
Department of Aviation & Communication Electronics, Air Force Institute of Technology, Gangshan, Kaohsiung, Taiwan (R.O.C.)
*Email: [email protected]
Corresponding Author
Ho-Nien Shou
Received 15 September 2019, Accepted 23 June 2020, Available Online 31 December 2020.
DOI
https://doi.org/10.2991/jrnal.k.201215.007How to use a DOI?
Keywords
Three axis magnetometer; earth magnetic field; Kalman filtering; processor-in-the-loop
Abstract
The missions of micro-satellites range from early military usages to weather forecast, resources exploration, communication, and scientific experiment. The advantages of micro-satellites are simple mechanical structures, great reliability, low prices, and precise researchers and equipment. Therefore, due to the limits of weight and power, this kind of micro-satellite with low design cost and high precision requires reducing unnecessary attitude sensors and controllers to ensure the precision of attitude control. Besides, it adapts the least hardware constituting attitude system, which is the future trend in the satellite engineering. In this article, an estimating technology about measuring angle speed with a gyro less is mentioned. This technology is based on the period change which the earth magnetic field gets along the track. Only by using a three axis magnetometer, it can produce the data from the micro-satellite measuring the earth magnetic field. Besides, the measures of three axis angle speed and attitude angle can be gotten through Kalman filtering. The purpose of this article is mainly to explore the problem on attitude detumbling control of micro-satellites departing away a carrier to enter a track. It is realized by a thruster to proceed the confinement of the satellite moving, the attitude stable control and processor-in-the-loop.
Copyright
© 2020 The Authors. Published by ALife Robotics Corp. Ltd.
Open Access
This is an open access article distributed under the CC BY-NC 4.0 license (http://creativecommons.org/licenses/by-nc/4.0/).

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