A Pitch Control System Design for Bicopter UAVs

Uddin, Nur and Harno, Hendra G. and Manurung, Auralius and Nasucha, Mohammad (2021) A Pitch Control System Design for Bicopter UAVs. International Conference on Information Technology, Computer and Electrical Engineering (ICITACEE) (213842). pp. 1-6. ISSN 978-1-6654-3998-5

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Abstract

A study to design a pitch control system for bicopters is presented. The bicopters are a type of unmanned aerial vehicle (UAV) that only utilizes two rotors. The pitch control system is to manipulate the bicopter flight attitude such that flies at a desired pitch angle. The pitch control system is designed based on a bicopter dynamics model by applying the Lyapunovbased control method. The control design results in a state feedback controller that has structure of proportional-derivative (PD) control. Applying the controller results in a closed loop pitch control system that is globally asymptotically stable (GAS). Performance of the designed pitch control system is demonstrated through computer simulation. The simulation results show that the designed pitch control system is able to make the bicopter fly at the desired pitch angle. The bicopter is able to change the pitch angle from 0 to 15 degrees without steady state error within 1.19 seconds. Index Terms

Item Type:	Artikel
Uncontrolled Keywords:	bicopter, pitch control, system modeling, control design, Lyapunov-based control
Subjects:	T Technology > T Technology (General)
Divisions:	Fakultas Teknologi dan Desain > Informatika
Depositing User:	Admin Repository
Date Deposited:	22 Jun 2022 00:57
Last Modified:	16 Jan 2023 03:13
URI:	http://eprints.upj.ac.id/id/eprint/2697

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