Attitude stabilization of a rigid spacecraft in actuator failure mode.

摘要

A stabilising feedback control system is designed for a rigid spatial body (spacecraft). The body is characterised by a three axes rotation. The method is based on a Lie bracket extension of the original system and can be applied to completely controllable systems without derivatives. The approach is not constrained by any particular choice of a Lyapunov function. The resulting control algorithm is composed of a standard feedback control of the extended system and of a periodic continuation of a solution of a parametrized open loop control with a finite and defined horizon.