Rigid body assumption of a satellite model has been a common practice in spacecraft attitude manoeuvring. However, with the increasing demand for greater functionality of space activities, requires bigger and wider solar panels to cater the power needs. In this paper, simple rigid and flexible multi-body satellite model is derived using basic Newton’s second law and Assumed Mode Method. The response from both model are then simulated using MATLAB software while comparison is done to illustrate the significance of the flexible behaviour that inherited in the satellite system. With the negligence of flexible interference in the rigid model, it is likely to execute an exact attitude motion while the flexible model would yield a harmonic motion that is due to the vibratory motion of the solar panels.
