摘要
A single gimbal control moment gyro system is the best choice for large spacecraft attitude control systems, as executive components of spacecraft guidance, navigation, and control system. But the phenomenon of singularity exists in this system. This increases the difficulty in designing the steering law. Singularity of SGCMG system is analyzed in this paper. The singularity measurement is determined making use of a fuzzy decision. A singularity avoidance steering law of large spacecraft SGCMG system based on fuzzy decision is designed according to the idea of searching the singularity measurement's gradient. The simulation experiments show this method guarantees singularity avoidance of SGCMG system. This method provides a new idea for the steering law of large spacecraft.
A single gimbal control moment gyro system is the best choice for large spacecraft attitude control systems, as executive components of spacecraft guidance, navigation, and control system. But the phenomenon of singularity exists in this system. This increases the difficulty in designing the steering law. Singularity of SGCMG system is analyzed in this paper. The singularity measurement is determined making use of a fuzzy decision. A singularity avoidance steering law of large spacecraft SGCMG system based on fuzzy decision is designed according to the idea of searching the singularity measurement's gradient. The simulation experiments show this method guarantees singularity avoidance of SGCMG system. This method provides a new idea for the steering law of large spacecraft.
