Abstract:

The issue of attitude maneuver of a flexible spacecraftis investigated with single gimbaled control moment gyroscopes(SGCMGs) as an actuator. To solve the inertia uncertainty of thesystem, an adaptive attitude control algorithm is designed by applyinga radial basis function (RBF) neural network. An improvedsteering law for SGCMGs is proposed to achieve the optimal outputtorque. It enables the SGCMGs not only to avoid singularity,but also to output more precise torque. In addition, global, uniform,ultimate bounded stability of the attitude control system is provedvia the Lyapunov technique. Simulation results demonstrate theeffectiveness of the new steering law and the algorithm of attitudemaneuver of the flexible spacecraft.