Fuzzy PID Controller Analysis for the Hexacopter Aircraft Using Simulink Simulation

Jiahui Feng, Yuhui Luo, Zixian Huang, Rueiyuan Wang, Rongguei Tsai, Raojun Luo, Chaoxiong Su, Hosheng Chen

Hexacopter Aircraft, Unmanned Aerial Vehicle (UAV), Classical PID (Proportion Integration Differentiation) Control, Fuzzy PID Control, Simulink Simulation

This study aims to investigate the control benefits of rotary wing aircraft systems through the Simulink simulation platform. A hexacopter aircraft is a small unmanned aerial vehicle (UAV) powered by the operation of six rotors, which has important theoretical and practical application value. Firstly, the body structure and working principle of the hexacopter aircraft are proposed. Then, a mathematical model of the hexacopter aircraft is established to support the design of subsequent control strategies. Next, compare the differences between the classical PID controller design and the fuzzy PID controller design methods for aircraft control systems and verify them through simulation experiments. The simulation results show that compared with the classical PID controller, the fuzzy PID controller can stabilize the aircraft at the target position faster when subjected to various types of disturbances and have good practicality, stability, speed, and accuracy. Based on this, future research can further explore the application of other advanced control strategies in aircraft control systems and their prospects in practical engineering.

Received: 23 Sep 2024, Receive in revised form: 25 Oct 2024, Accepted: 01 Nov 2024, Available online: 06 Nov 2024

10.22161/ijaers.1111.2