Angle control of a single-degree-of-freedom mechanical helicopter model

A helicopter has a lot of uncertainties and disturbances affecting its aerodynamics, which raises the need for robust control. In this thesis a single-degree-of-freedom (1- DOF) laboratory scale helicopter model is designed and controlled via Proportional Integral Derivate (PID) control and Sliding Mode Control (SMC), both of which have solid performances to reject disturbances. The PID and SMC controllers are tested in presence of different types of uncertainties. The helicopter model consists of one arm that rotates on a rigid base with brushless Direct Current (DC) motor driven propeller on one side and counterweight on the other side. Proposed control methodologies are applied to improve the control performance of 1-DOF helicopter model. A potentiometer is used to measure the rotation angle, DAQ-6353 card is used for communication between computer and the Electronic Speed Controller (ESC). The performances are observed in terms of how fast arm angle follows the desired setpoint and also the steady state error. Results show that the desired robustness is obtained using the SMC and the control performance for the SMC is better than the PID. Keyword: 1-DOF helicopter, PID, SMC, Brushless DC motor.