Introducing of Attitude Determination System of a LEO Satellite with Orbital Maneuver Mission

New algorithm is presented in this paper for attitude determination of LEO nanosatellite with 2 accuracy in attitude determination independent of time. The most important limitation in nanosatellites is about subsystems’s masses so, reduction of subsystems’s masses is always considered. ADS plays the important role in the successful orbital maneuver missions. ADS accuracy is connected with increasing of sensors and complex processors which lead to increase the ADS mass. The presented algorithm uses one magnetometer sensor and one horizon sensor and position data receiving by GPS sensor as minimum required sensors. The selected configuration is resulted to minimum ADS mass and mission cost. Finally, error analysis at two most important orbit zones is done and the performance of the presented algorithm is confirmed.