Table of Contents
ISRN Aerospace Engineering
Volume 2014 (2014), Article ID 409408, 10 pages
http://dx.doi.org/10.1155/2014/409408
Research Article

Designing Stipulated Gains of Aircraft Stability and Control Augmentation Systems for Semiglobal Trajectories Tracking

1Department of Mechanical Engineering, Faculty of Engineering, Alexandria University, Alexandria 21544, Egypt
2Whirlpool Corporation, Saint Joseph Technology Center, 303 Upton Drive, Saint Joseph, MI 49085, USA
3CNH Industrial, 6900 Veterans Ave., Burr Ridge, IL 60527, USA

Received 29 August 2013; Accepted 11 December 2013; Published 30 January 2014

Academic Editors: J. Yao and C. Yuan

Copyright © 2014 Mohamed Mostafa Y. B. Elshabasy et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Abstract

The main objective of the current investigation is to provide a simple procedure to select the controller gains for an aircraft with a largely wide complex flight envelope with different source of nonlinearities. The stability and control gains are optimally devised using genetic algorithm. Thus, the gains are tuned based on the information of a single designed mission. This mission is assigned to cover a wide range of the aircraft’s flight envelope. For more validation, the resultant controller gains were tested for many off-designed missions and different operating conditions such as mass and aerodynamic variations. The results show the capability of the proposed procedure to design a semiglobal robust stability and control augmentation system for a highly maneuverable aircraft such as F-16. Unlike the gain scheduling and other control design methodologies, the proposed technique provides a semi-global single set of gains for both aircraft stability and control augmentation systems. This reduces the implementation efforts. The proposed methodology is superior to the classical control method which rigorously requires the linearization of the nonlinear aircraft model of the investigated highly maneuverable aircraft and eliminating the sources of nonlinearities mentioned above.