The main task of an earth observation satellite is to deliver accurate and valid earth surface information to the ground station. In order to perform this task, the satellite is equipped with an attitude control system. The control system establishes closed-loop with attitude sensors, especially in the imaging operation. However, the limitation of satellite power supply capacity causes the restriction of attitude control operation, which in turn, limits the satellite imaging capacity. The aim of this paper is to analyze the power performance of optimal satellite design by observing the effects of a Proportional Integral Differential (PID) parameter changes to satellite power consumption. In this paper, firstly optimal satellite parameters are chosen. The parameter choice is based on a quadratic objective function that representing power consumption. In the sequence, the PID attitude control system is designed for the satellite. Through simulation, the effects of various PID parameters have been studied.