Fuzzy-Logic-Based Fixed-Time Geometric Backstepping Control on SO(3) For Spacecraft Attitude Tracking

This paper addresses the fuzzy-logic-based fixed-time geometric backstepping attitude tracking for the rigid-body spacecraft modeled on the nonlinear differential manifold three-dimensional special orthogonal group [SO(3)]. The fixed-time geometric controller is deduced by the backstepping method. Moreover, an adaptive fuzzy logic system is employed to compensate the unknown disturbances. The almost globally fixed-time stabilization of the closed-loop system is verified via Lyapunov analysis. Simulation results demonstrate the effectiveness of the proposed controller.