Modelling and control of flexible structure for satellite attitude maneuvers using pole placement and PID controller

Abstract

This thesis describes the studies on vibration of flexible structure of satellite (solar panel) by using cantilever beam for performance analysis. Nearly ideal cantilever beam model is studied to provide basic understanding in vibration solar panel of satellite operation, follow by a mathematical model of cantilever beam, containing relationships for vibration reaction, angular momentum, power consumption and disturbances. From the cantilever model with consist of parameters to studies about response on vibration. To solve this problem, MATLAB/SIMULINK is used to obtain the transfer function of the cantilever beam modeling. From simulation results shows a transfer function modeling providing the slow time response. For this case, fast response controller design was implemented in this modeling. Pole Placement controller and PID controller are designed and compared the performance on the modeling system by using MATLAB/SIMULINK. Simulation results show PID adding Pole Placement controller gives better performance in term of rise time, settling time, percentage overshoot, steady state error and performance indices than Pole Placement controller.