Three-axis active control system for gravity gradient stabilised microsatellite |
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| Authors: | A.M. Si Mohammed M. Benyettou Y. Bentoutou A. Boudjemai Y. Hashida M.N. Sweeting |
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| Affiliation: | 1. Centre National des Techniques Spatiales, Arzew, Algeria;2. Université des Sciences et de la Technologie, Oran, Algeria;3. Surrey Satellite Technology Limited, Guidlford, UK;1. Department of Mechanical Engineering, Chennai Institute of Technology, Chennai 600069, Tamilnadu, India;2. Department of Mechanical Engineering, Vel Tech High Tech Dr RR & Dr SR Engineering College, Chennai 600062, Tamilnadu, India;1. Saint Petersburg State University, 7-9 Universitetskaya Nab., St. Petersburg, 199034, Russia;2. Saint Petersburg Mining University, 2, 21st Line, St. Petersburg, 199106, Russia;1. Keldysh Institute of Applied Mathematics of RAS, Miusskaya Sq., 4, Moscow 125047, Russia;2. Moscow Aviation Institute, Volokolamskoe Shosse, 4, Moscow 125993, Russia;1. Department of Aeronautics and Astronautics, Tokyo Metropolitan University, 6-6 Asahigaoka, Hino, Tokyo, Japan;2. Department of Space and Astronautical Science, SOKENDAI (The Graduate University for Advanced Studies), 3-1-1 Yoshinodai, Chuo-ku, Sagamihara, Kanagawa, Japan;3. Department of Spacecraft Engineering, Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-ku, Sagamihara, Kanagawa, Japan;4. Department of Mechanical and Aerospace Engineering, Tokyo Institute of Technology, 2-12-1 Ookayama, Meguro, Tokyo, Japan;5. Department of Electrical and Electronic Engineering, Tokyo Institute of Technology, Tokyo Institute of Technology, 2-12-1 Ookayama, Meguro, Tokyo, Japan;6. Department of Mechanical Engineering, Tokyo Institute of Technology, 2-12-1, Ookayama, Meguro, Tokyo, Japan |
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| Abstract: | In this paper, the control system of the first Algerian microsatellite in orbit Alsat-1 is presented. Alsat-1 is a 3-axis stabilised microsatellite, using a pitch momentum wheel and yaw reaction wheel, with dual redundant 3-axis magnetorquers. A gravity gradient boom is employed to provide a high degree of platform stability. Two vector magnetometers and four dual sun sensors are carried in order to determine the attitude. This paper examines the low Earth orbit (LEO) control system requirements and design in the context of a real system, the Surrey Satellite Technology Limited (SSTL) advanced microsatellite platform and puts forward designs for the control system to match the advanced capability of the enhanced microsatellite platform. Numerical results show the effectiveness of the implementation. Comparison with in orbit results is presented to evaluate the performance of the control system during accurate Nadir pointing control. |
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