Design and Simulation of a Guidance Control System for a 2.75-inch Rocket Using Pole Placement and PI Control
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Abstract
This research focuses on the design and simulation of an autopilot system for a 2.75-inch Wrap-Around Fin Aerial Rocket (WAFAR), incorporating a guidance system into the traditional unguided airframe. The control system was designed using a combination of pole placement techniques and proportional-integral (PI) control to enable precise directional control and maintain stability during flight. The design process takes into account the dynamics and aerodynamic characteristics of the rocket. The pole placement technique was employed to define the pole locations in the system's transfer function, achieving the desired stability and response characteristics. Concurrently, the PI control enhances the system's responsiveness and tracking accuracy. The guidance of the rocket is achieved through acceleration control, enabling it to follow the desired trajectory. A nonlinear simulation of the rocket under different launch-to-target distances and LOS errors demonstrates the effectiveness and accuracy of the proposed control system in target tracking. Although the control system was designed based on a linearized model of the rocket dynamics, it was evaluated on a nonlinear plant model to verify its practical performance.
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