Suppression of effects on model error in attitude control of spacecraft using two reaction wheels considering initial angular momentum

Abstract

The attitude control of a spacecraft utilizing only two reaction wheels is proposed in [5]. However, the model error and initial angular momentum are not considered in the model base controller, and that may become a problem when it has been applied to actual spacecraft. In this study, considering the case of unknown initial angular momentum and a model error existing in inertia matrix, we propose an adaptive modification of model parameters. The validity of the proposed method is verified by numerical simulations.