Show simple item record

dc.contributor.advisorSawan, M. Edwin
dc.contributor.advisorWatkins, John Michael
dc.contributor.authorGraziosi, Joseph E.
dc.date.accessioned2014-11-17T16:22:39Z
dc.date.available2014-11-17T16:22:39Z
dc.date.issued2014-05
dc.identifier.othert14012
dc.identifier.urihttp://hdl.handle.net/10057/10958
dc.descriptionThesis (M.S.)--Wichita State University, College of Engineering, Dept. of Electrical Engineering and Computer Science
dc.description.abstractThe 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.
dc.format.extentviii, 24 p.
dc.language.isoen_US
dc.publisherWichita State University
dc.rightsCopyright 2014 Joseph E. Graziosi
dc.subject.lcshElectronic dissertations
dc.titleApproximate controller design for singularly perturbed aircraft
dc.typeThesis


Files in this item

Thumbnail

This item appears in the following Collection(s)

Show simple item record