LabView based Conrol System Design for VTOL Aircraft System

Abstract

Vertical Take Off and Landing (VTOL) aircraft system is a highly complicated, nonlinear, and a multi variable large disturbances system. Hence an efficient control mechanism is a difficult task for such system. The key objective of this study is to design a controller which balances the VTOL system parallel to the ground (horizontal position) in spite of disturbances. Design of Proportional Integral Derivative (PID) Controller is chosen because of its simplicity, clear functionality and easy to apply algorithm. This appears to be intuitive but can be hard in practice if multiple objectives such as high stability and reduced oscillations are to be achieved. The system response is examined for various values of controller gains. Also, setpoint filters are introduced to improve the overall performance of the controller. Finally, the experimental and LabVIEW based simulation results for pitch angle and current response (current flowing through motor) are calculated and compared which demonstrate that a proper filter selection based PID controller is an effective algorithm.