Finite time eigenaxis rotation using quaternion feedback

The attitude of the spacecraft is its angular orientation in space. Attitude control design of a satellite system is an important area of space technology. An efficient controller is required to take the satellite system to its target orientation. In some cases, the maneuver need to be completed within a finite time. This paper introduces a novel control law which achieves finite time convergence to the required orientation. The control laws are shown to converge in a finite time for the satellite system by using Lyapunov theory and are also illustrated via simulation results.