Loading...
Approximate controller design for singularly perturbed aircraft
Graziosi, Joseph E.
Graziosi, Joseph E.
Citations
Altmetric:
Files
Authors
Other Names
Location
Time Period
Advisors
Original Date
Digitization Date
Issue Date
2014-05
Type
Thesis
Genre
Keywords
Subjects (LCSH)
Electronic dissertations
Electronic dissertations
Electronic dissertations
Citation
Abstract
The purpose of this thesis was to extend the quasi-steady-state approximation and matrix block diagonalization methods utilized in the work of Shim and Sawan [1]. These authors showed that an approximate controller solution could be developed by relocating only the slow poles for two-time-scale aircraft dynamics. In addition, they showed that the difference between approximate solutions and exact solutions was bounded within limits as O(epsilon) and O(epsilon2). This technique was successfully applied to the lateral dynamics of the de Haviland Canada DHC-2 Beaver aircraft.
In this thesis, the same technique was 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 showed that a finite solution to the Lyapunov equation existed as a result of the stability.
Table of Contents
Description
Thesis (M.S.)--Wichita State University, College of Engineering, Dept. of Electrical Engineering and Computer Science
Publisher
Wichita State University
Journal
Book Title
Series
Digital Collection
Finding Aid URL
Use and Reproduction
Copyright 2014 Joseph E. Graziosi