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Computational Experimental Test on PID Controlled Fixed Wing Aircraft Systems
1
School of Engineering, University of the West of England, Bristol BS16 1QY, United Kingdom
* Corresponding Author:
Quanmin Zhu,
[email protected]
Volume 2, Issue 2
2025
Received: 14 February 2025
Accepted: 11 May 2025
Published: 18 May 2025
Article Information
Abstract
This paper focuses on the implementation of a control framework for a fixed wing aircraft system and the simulation demonstrations. The aim is to develop several Proportional Integral Derivative (PID) controllers to stabilise the altitude and attitude in a 2D environment by regulating the engine power, the pitch angle, and height in flight operation. In technique, a dynamic mathematical model is established by considering the degrees of freedom and the dynamics of motion of a fixed wing aircraft, which provide a foundation for design and simulation. A simplified aircraft dynamic model is tailored for testing the formed control systems, which can be flexibly modified with different aircraft configurations, for a showcase illustration a calculation of the moment of inertia is included. Further, several flight settings such as height differences and velocities are proposed and a feasible implementation of the PID controllers is introduced for adjusting the control variables, and further a switching mode with two controllers for the height with different speeds are simulated to select the height linked controllers.
Graphical Abstract
Keywords
aircraft dynamic modelling
control systems
PID
simulation
Matlab/Simulink
Data Availability Statement
Data will be made available on request.
Funding
This work was supported without any funding.
Conflicts of Interest
The authors declare no conflicts of interest.
Ethical Approval and Consent to Participate
Not applicable.
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APA Style
Horstkötter, E., & Zhu, Q. (2025). Computational Experimental Test on PID Controlled Fixed Wing Aircraft Systems. ICCK Transactions on Sensing, Communication, and Control, 2(2), 95–105. https://doi.org/10.62762/TSCC.2025.731885
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TY - JOUR AU - Horstkötter, Eileen AU - Zhu, Quanmin PY - 2025 DA - 2025/05/18 TI - Computational Experimental Test on PID Controlled Fixed Wing Aircraft Systems JO - ICCK Transactions on Sensing, Communication, and Control T2 - ICCK Transactions on Sensing, Communication, and Control JF - ICCK Transactions on Sensing, Communication, and Control VL - 2 IS - 2 SP - 95 EP - 105 DO - 10.62762/TSCC.2025.731885 UR - https://www.icck.org/article/abs/TSCC.2025.731885 KW - aircraft dynamic modelling KW - control systems KW - PID KW - simulation KW - Matlab/Simulink AB - This paper focuses on the implementation of a control framework for a fixed wing aircraft system and the simulation demonstrations. The aim is to develop several Proportional Integral Derivative (PID) controllers to stabilise the altitude and attitude in a 2D environment by regulating the engine power, the pitch angle, and height in flight operation. In technique, a dynamic mathematical model is established by considering the degrees of freedom and the dynamics of motion of a fixed wing aircraft, which provide a foundation for design and simulation. A simplified aircraft dynamic model is tailored for testing the formed control systems, which can be flexibly modified with different aircraft configurations, for a showcase illustration a calculation of the moment of inertia is included. Further, several flight settings such as height differences and velocities are proposed and a feasible implementation of the PID controllers is introduced for adjusting the control variables, and further a switching mode with two controllers for the height with different speeds are simulated to select the height linked controllers. SN - 3068-9287 PB - Institute of Central Computation and Knowledge LA - English ER -
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@article{Horstktter2025Computatio,
author = {Eileen Horstkötter and Quanmin Zhu},
title = {Computational Experimental Test on PID Controlled Fixed Wing Aircraft Systems},
journal = {ICCK Transactions on Sensing, Communication, and Control},
year = {2025},
volume = {2},
number = {2},
pages = {95-105},
doi = {10.62762/TSCC.2025.731885},
url = {https://www.icck.org/article/abs/TSCC.2025.731885},
abstract = {This paper focuses on the implementation of a control framework for a fixed wing aircraft system and the simulation demonstrations. The aim is to develop several Proportional Integral Derivative (PID) controllers to stabilise the altitude and attitude in a 2D environment by regulating the engine power, the pitch angle, and height in flight operation. In technique, a dynamic mathematical model is established by considering the degrees of freedom and the dynamics of motion of a fixed wing aircraft, which provide a foundation for design and simulation. A simplified aircraft dynamic model is tailored for testing the formed control systems, which can be flexibly modified with different aircraft configurations, for a showcase illustration a calculation of the moment of inertia is included. Further, several flight settings such as height differences and velocities are proposed and a feasible implementation of the PID controllers is introduced for adjusting the control variables, and further a switching mode with two controllers for the height with different speeds are simulated to select the height linked controllers.},
keywords = {aircraft dynamic modelling, control systems, PID, simulation, Matlab/Simulink},
issn = {3068-9287},
publisher = {Institute of Central Computation and Knowledge}
}
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