PID Controller Design for Dynamic Motion of an Aircraft

Abstract

The development and implementation of automatic control systems have helped the aviation industry to grow in more efficient manner in terms of stability and performance of the Aircraft. But as improvement is the key for progress of technology the development and advancement in automatic control systems have also increased. In this paper, the performance of the Proportional- Integral- Derivative (PID) controller is studied for General Navion Aircraft by considering its longitudinal motion. The design is implemented using Model based Programming of MATLAB.. The reference input is the elevator deflection angle and the output is the Pitch angle. The gain values of the Controller is tuned using the PID toolkit. Simulation results shows that the design specifications in time domain and convergence to the design considerations.