Practical finite-time control of missiles — A terminal sliding mode approach

This paper investigates the missile attitude control problem. The model used in this paper is with respect to the Euler attitude angles and their derivatives which can be measured and computed easily. A robust practical finite-time control algorithm is proposed based on the terminal sliding mode approach. It is proved that all of the signals in the closed-loop system are bounded and the tracking error can be driven into a given small neighborhood of the origin in the pre-specified time. The simulation results show the effectiveness of the proposed results.