Design and Faulty Diagnosis for Microsatellite Attitude Control System

As one of the core subsystems of satellites, the normal operation of attitude determination and control system (ADCS) guarantee the overall function of the satellite. With the development of microsatellites, mass, size, power consumption and reliability are the important factors to be considered when designing ADCS. In addition, the ADCS may have various faults during the whole mission, which will cause serious effect to the entire satellite and even lead to mission failure. Under the research background of the Lancang-Mekong Cooperation Pu'er microsatellite (LM-1), this paper conducts program design and algorithm simulation of the attitude control system. The main tasks are summarized as follows. According to the input conditions and functional indexes of the attitude control system provided by the specific mission requirements, this paper proposes reasonable and effective attitude control strategies to ensure the completion of the flight mission. The core modes include rate damping, sun capture, three-axis stability and attitude maneuvering modes. The latter two modes are designed to satisfy the requirements of remote sensing imaging. After modeling the attitude control system, this paper designs the attitude estimation algorithm based on the combination of star sensor and gyroscope, and the dual-vector attitude algorithm based on the combination of sun sensor and three-axis magnetometer. Subsequently, corresponding algorithms are designed for each operating mode of attitude control strategy, and the effectiveness of the algorithms is verified by simulation. In summary, this paper completes the design and verification of the attitude control system scheme for LM-1 microsatellite, providing relatively complete scheme for the subsequent research work of microsatellite.