Earth Observation (EO) missions are characterized by high pointing performance. Also, spacecraft payloads are becoming more capable, demanding more power (and solar array area). This additional array area including its structural flexibilities has to be taken into account in the modeling of satellite dynamics, as well as disturbances and the components of attitude control system. A modeling task is undertaken to accurately represent the satellite and its components in the simulation environment. The pointing performance metrics are defined and implemented in the simulation loop as a part of this task. The effect of solar array configuration on the pointing performance is investigated.