Methodology for the development of combined energy and attitude control systems for satellites

The Combined Energy and Attitude Control System (CEACS) is a promising technologically advanced concept for space applications which could replace the conventional separate Electrical Power System (EPS) and Attitude Control System (ACS). In the past years this system was proposed for larger spacecraft but until today neither the feasibility of CEACS on small spacecraft, such as the Micro/Nanosatellites, nor end-to-end system demonstration was performed. Additionally, the existing literature does not emphasize extensively mathematical models for a precise analysis of the CEACS. Therefore, the study presented here deals with an initial investigation of useful models that allow for a systematic analysis of CEACS independent of the satellite types. The concept discussed is based on a double counter rotating flywheel assembly in the pitch axis. For the presentation of the methodology, a reference mission is chosen to demonstrate the feasibility of CEACS on smaller satellites. The capabilities of energy storage and attitude control are especially demonstrated. The critical limitations are analyzed and the simulation results are presented. Finally, the general feasibility of CEACS on Micro/Nanosatellites is discussed.