Vibration Control in Aerospace Structures Using PID controller

The demand for high-performance and lightweight structures in the Aerospace Industry has led to vibration-related challenges. Vibration in aerospace structures can lead to fatigue, structural failure, and reduced performance. This paper investigates the application of the Proportional-Integral-Derivative (PID) Controller to manage and control vibration in aerospace structures. PID Controller is used due to its effectiveness, simplicity and adaptability for controlling the dynamic systems. A mathematical model of a mass-spring-damper system is developed and simulated in MATLAB/Simulink under free and forced vibration conditions. The PID controller is tested using manual tuning, Ziegler-Nichols, and Cohen-Coon methods. Results show that PID control reduces vibration amplitude by up to 80%, with manual tuning achieving a balanced response of 4.2 second settling time with overshoot of 3.5%, Ziegler-Nichols offering faster damping (3.2 s settling time) but higher overshoot($\mathbf{8. 2 \%}$), and Cohen-Coon providing maximum stability (overshoot 2.1%) with a slower response(5.5s). These results confirm PID control as a viable method for vibration suppression in real-time aerospace applications.