In this paper we present classical PID controller approach in designing longitudinal Stability Augmentation System and pitch attitude control (SCAS) at nonlinear flight region for a high fidelity F-16 model including aerodynamic uncertainty. In high angle of attack, nonlinear effects of aerodynamic coefficients and atmospheric turbulence are the main challenge in designing and robustness of flight control system. A design scenario that combines deadbeat response and robust control (aerodynamic uncertainties and atmospheric turbulence) is presented. Simulation results show that the designed PI controller exhibits robustness property to system uncertainties.
| Published in | American Journal of Aerospace Engineering (Volume 1, Issue 1) |
| DOI | 10.11648/j.ajae.20140101.11 |
| Page(s) | 1-7 |
| Creative Commons |
This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited. |
| Copyright |
Copyright © The Author(s), 2014. Published by Science Publishing Group |
Aircraft Pitch Control, Deadbeat Controller, Robust Controller, Modern Type Aircraft
| [1] | L. Sonneveldt, E.R. van Ort, Q.P. Chu and J.A. Mulder, "Nonlinear Adaptive Flight Control Law Design and Handling Qualities Evaluation," IEEE Conference on Decision and Control, China, December 16-18, 2009. |
| [2] | Michael V. Cook, "Flight Dynamics Principles", Second Edition, ISBN:978-0-7506-6927-6, 2007. |
| [3] | Yake, Bradley Gerald, "Investigation of Fore body Strakes on Aircraft Stability at High Angle of Attack", Master of Science in aerospace engineering, University of Texas at Arlington 1991. |
| [4] | Russell M. Cummings, James R. Forsythe, Scott A. Morton, , Kyle D.Squires," Computational challenges in high angle of attack flow prediction", Aerospace Engineering Department, California Polytechnic State University, San Luis Obispo, CA 93407, USA ,2003. |
| [5] | David Allerton, "PRINCIPLES OF FLIGHT SIMULATION", Aerospace Series, ISBN: 978-0-470-75436-8 (Hbk), the University of Sheffield, 2009. |
| [6] | B. Kada, Y. Ghazzawi, "Robust PID Controller Design for an UAV Flight Control System" , Proceedings of the World Congress on Engineering and Computer Science, Vol II, ISSN: 2078-0966 (Online), 2011. |
| [7] | L. T. Nguyen, M. E. Ogburn, W. P. Gilbert, K. S. Kibler, P. W. Brown, and P. L. Deal, "Simulator study of stall post-stall characteristics of a fighter airplane with relaxed longitudinal static stability", tech. rep., NASA Langley Research Center, 1979. |
| [8] | B. L. Lewis and F. L. Stevens," Aircraft Control and Simulation", pp. 1–54,110–115. John Wiley & Sons, 1992. |
| [9] | Chao Wang, "Aircraft Autopilot Design using a Sampled Data Gain Scheduling Technique", Master of Science, College of Engineering and Technology Ohio University, March, 1999. |
| [10] | Albert Farre Gabernet," Controllers for Systems with Bounded Actuators: Modeling and control of an F-16 aircraft", Master of Science, University of California, Irvine, 2007. |
| [11] | Brent R. Cobleigh, "Development of the X-33 Aerodynamic Uncertainty Model", Dryden Flight Research Center, Edwards, California 93523-0273, NASA/TP-1998 -206544 , 1998. |
| [12] | Jan Roskam," Airplane Flight Dynamics and Automatic Flight Controls", Part I, ISBN 1-884885-17-9, Copyright ©1995-2001 by Dr. Jan Roskam in United States of America. |
| [13] | Ashish Tewari, "Modern Control Design with Matlab and Simulink", Indian Institute of Technology, Kanpur, India, ISBN 0 471 496790, Copyright © 2002 by John Wiley & Sons Ltd. |
| [14] | Military Standard - Flying Qualities of Piloted Airplane, MIL-F-8785C, 1980. |
| [15] | Dryden Wind Turbulence Model Continous), MATHWORKS, [Online]. Available: http://www.mathworks.com/help/aeroblks/drydenwindturbulencemodeldiscrete.html. [Accessed 5 March 2013]. |
| [16] | P. W. Gibbens,D. P. Boyle, " FLIGHT MECHANICS 2", Lecture Notes, AERO 4500, University of Sydney Department of Aeronautical Engineering, 1999. |
| [17] | Borja Martos, "Identifying and Correcting First Order Effects in Explanatory Variables for Longitudinal Real Time Parameter Identification Methods in Atmospheric Turbulence", University of Tennessee, Knoxville, Trace: Tennessee Research and Creative Exchange, Doctoral Dissertations, Copyright © 2013 by Borja Martos. |
| [18] | Mullapudi Jyothi, Tadikonda Poojitha, Y V Pavan Kumar, Dr. K Babulu, "A Comparative Study on Flight Control Systems Design Using Conventional vs. Statistical Methods", IJSR -INTERNATIONAL JOURNAL OF SCIENTIFIC RESEARCH, Volume : 2 :Issue : 7 • SSN No 2277 - 8179, July 2013. |
| [19] | T.Hanis, V. Kucera, M. Hromcik, "Low Order Optimal Control for ACFA Blended Wing Body Aircraft", EUROPEAN CONFERENCE FOR AEROSPACE SCIENCES (EUCASS), ACFA2020 special session, 2011. |
| [20] | Mingwei Sun, Zengqiang Chen, Zhuzhi Yuan, "A Practical Solution to Some Problems in Flight Control", Joint 48th IEEE Conference on Decision and Control and 28th Chinese Control Conference, Shanghai, P.R. China, December 16-18, 2009. |
APA Style
Mohammad Salem, Mohammad Ali Shahi Ashtiani. (2014). Robust PID Controller Design for a Modern Type Aircraft Including Handling Quality Evaluation. American Journal of Aerospace Engineering, 1(1), 1-7. https://doi.org/10.11648/j.ajae.20140101.11
ACS Style
Mohammad Salem; Mohammad Ali Shahi Ashtiani. Robust PID Controller Design for a Modern Type Aircraft Including Handling Quality Evaluation. Am. J. Aerosp. Eng. 2014, 1(1), 1-7. doi: 10.11648/j.ajae.20140101.11
AMA Style
Mohammad Salem, Mohammad Ali Shahi Ashtiani. Robust PID Controller Design for a Modern Type Aircraft Including Handling Quality Evaluation. Am J Aerosp Eng. 2014;1(1):1-7. doi: 10.11648/j.ajae.20140101.11
Share This Article
Twitter
Linked In
Facebook
Copy
Download@article{10.11648/j.ajae.20140101.11,
author = {Mohammad Salem and Mohammad Ali Shahi Ashtiani},
title = {Robust PID Controller Design for a Modern Type Aircraft Including Handling Quality Evaluation},
journal = {American Journal of Aerospace Engineering},
volume = {1},
number = {1},
pages = {1-7},
doi = {10.11648/j.ajae.20140101.11},
url = {https://doi.org/10.11648/j.ajae.20140101.11},
eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajae.20140101.11},
abstract = {In this paper we present classical PID controller approach in designing longitudinal Stability Augmentation System and pitch attitude control (SCAS) at nonlinear flight region for a high fidelity F-16 model including aerodynamic uncertainty. In high angle of attack, nonlinear effects of aerodynamic coefficients and atmospheric turbulence are the main challenge in designing and robustness of flight control system. A design scenario that combines deadbeat response and robust control (aerodynamic uncertainties and atmospheric turbulence) is presented. Simulation results show that the designed PI controller exhibits robustness property to system uncertainties.},
year = {2014}
}
TY - JOUR T1 - Robust PID Controller Design for a Modern Type Aircraft Including Handling Quality Evaluation AU - Mohammad Salem AU - Mohammad Ali Shahi Ashtiani Y1 - 2014/03/30 PY - 2014 N1 - https://doi.org/10.11648/j.ajae.20140101.11 DO - 10.11648/j.ajae.20140101.11 T2 - American Journal of Aerospace Engineering JF - American Journal of Aerospace Engineering JO - American Journal of Aerospace Engineering SP - 1 EP - 7 PB - Science Publishing Group SN - 2376-4821 UR - https://doi.org/10.11648/j.ajae.20140101.11 AB - In this paper we present classical PID controller approach in designing longitudinal Stability Augmentation System and pitch attitude control (SCAS) at nonlinear flight region for a high fidelity F-16 model including aerodynamic uncertainty. In high angle of attack, nonlinear effects of aerodynamic coefficients and atmospheric turbulence are the main challenge in designing and robustness of flight control system. A design scenario that combines deadbeat response and robust control (aerodynamic uncertainties and atmospheric turbulence) is presented. Simulation results show that the designed PI controller exhibits robustness property to system uncertainties. VL - 1 IS - 1 ER -
Email: