Study on the attitude control of the micro satellite using magnetic torquer
- Paper number
IAC-05-E2.P.07
- Author
Mr. Tasuku Wakatsuki, Kyushu University, Japan
- Coauthor
Dr. Yuji Sakamoto, Tohoku University, Japan
- Coauthor
Prof. Toshiya Hanada, Kyushu University, Japan
- Coauthor
Prof. Tetsuo Yasaka, Kyushu University, Japan
- Year
2005
- Abstract
This paper describes the attitude controlling for the micro satellite QTEX using magnetic torquers. QTEX (KYUshu university Tethered satellite Experiments) is the project to develop satellites at Kyushu University on students’ initiative. QTEX consists of a pair of almost same satellites called QTEX-PR,which is 50x50x25cm in size and 50kg in weight. They are docked in launch then separate on orbit to extend 2km tether between them. It is required that the attitude is stabilized when the satellites separate and start the extension of the tether to reach targeted tether length successfully. Moreover, both satellites have 3-axis attitude controlling components so that they can be stabilized independently after the tether extension. A three-axis magnetic sensor, a pair of three-axis sun sensors and thee gyro sensors are used for attitude determination, and three magnetic torquers are used as actuators. Magnetic torquer is suitable for the small satellites because of advantages of lightweight and low power consumption. This study shows the results of numerical simulations to control the satellites only with the magnetic torquers. The result shows that it is possible to keep the attitude errors within required ranges.
- Abstract document