This paper formulated an algorithm for coarse sun acquisition with sun sensors, specifically for the case of microsatellites. In contrast to a larger satellite, a microsatellite has limited power and thus generally lacks a functional attitude estimator in the launching stage. After the detumbling stage, the microsatellite must acquire the sun’s position as soon as possible using the designated algorithm. This paper presents the development of an algorithm for the blind search of the sun’s position in the case where only coarse sun sensors are used. We also considered the case of a solar eclipse. A model with 6 degrees of freedom was developed for a Monte Carlo simulation to verify the developed algorithm. The developed algorithm can be used in any microsatellite with similar equipment.
關聯:
Journal of Aeronautics, Astronautics and Aviation 53(1), p.95-104
