NDLI: Approximate controller design for singularly perturbed aircraft systems

Content Provider	IEEE Xplore Digital Library
Author	Graziosi, J.E. Sawan, M.E. Watkins, J.M.
Copyright Year	2014
Description	Author affiliation: Dept. of Electr. Eng. & Comput. Sci., Wichita State Univ., Wichita, KS, USA (Graziosi, J.E.; Sawan, M.E.; Watkins, J.M.)
Abstract	The purpose of this paper is to extend the Quasi-Steady State Approximation and Matrix Block Diagonalization methods utilized in the Approximate Controller Design for Singularly Perturbed Aircraft Systems [1]. In that paper, it was shown that an approximate controller solution could be developed by relocating only the slow poles for two-time scale aircraft dynamics. In addition, it showed the difference between the approximate solutions and the exact solutions were bounded within limits as O(ε) and $O(ε^{2}).$ This technique was successfully applied to the lateral dynamics of the DeHaviland Canada DHC-2 Beaver. In this paper, the same technique is applied to the NASA F-8 Aircraft dynamics in order to show that the method is not unique to the Beaver and can be applied to other aircraft models. It also extended the method to consider the singularly perturbed stochastic system and confirmed stability was maintained.
Starting Page	161
Ending Page	164
File Size	648759
Page Count	4
File Format	PDF
ISBN	9781479941346
ISSN	15483746
e-ISBN	9781479941322
DOI	10.1109/MWSCAS.2014.6908377
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2014-08-03
Publisher Place	USA
Access Restriction	Subscribed
Rights Holder	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subject Keyword	Aircraft Approximation methods Aerospace control Aircraft propulsion Atmospheric modeling Stability analysis Aircraft manufacture
Content Type	Text
Resource Type	Article
Subject	Electronic, Optical and Magnetic Materials Electrical and Electronic Engineering

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