The regulation of satellite orientation in an orbit is an essential task for the success of a space mission. To reorient the attitude of a satellite from an initial point to the desired attitude, efficient control law needs to be developed. In this paper, the attitude control law is proposed to achieve a necessary shortest path of the Eigen-axis rotation between two attitudes. Moreover, it is also shown that the optimization of input energy required for the optimal Eigen-axis rotation can also be done through the proposed approach. The stability analysis of the proposed methodology is proved using the Lyapunov theory. Furthermore, the proposed scheme is also validated through numerical simulation.
Attitude Regulation of Spacecraft Using Large Angle Eigen-axis Rotations
2020-11-08
399932 byte
Conference paper
Electronic Resource
English