Finite‐time output feedback attitude stabilisation for rigid spacecraft with input constraints

This study deals with finite‐time output feedback attitude stabilisation problem for rigid spacecraft systems subject to input constraints. First, a continuous saturated state feedback controller is proposed based on the homogeneous method, after which can guarantee the closed‐loop system is global finite‐time stable. Then, a switched saturated output feedback controller is developed under a state observer, after which can guarantee the closed‐loop system is semi‐global finite‐time stable. Simulation results are given to demonstrate the effectiveness of the proposed method.