Design and Analysis of Nonlinear Constrained Control Algorithm for Rigid Aircraft ?

摘要

In this paper, a method to the problem of the attitude stabilization control for the rigid aircraft under angular velocity constrains is presented. Firstly, a finite-time controller with time-vary state-dependent gains is proposed. Then, based on the homogeneous theory, demonstrates the rigid body spacecraft with angular velocity constrains can be stabilized in a finite time. At the end, the effectiveness and validity of the developed method is verified by numerical simulation.