New flight control design scheme using optimal dynamic output feedback

Chiu Pin Cheng, Tzuu-Hseng S. Li, Ching Fang Lin

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

This paper applies a newly developed optimal dynamic output feedback control method to control the angle of attack α and pitch angle θ (for longitudinal control), and the angle of sideslip β and roll angle φ (for lateral-directional control), so that pilot can maneuver and control the airplane to the desired flight attitude precisely. The control design model is based on the linearized aircraft model. The unmodeled high frequency dynamics are ignored in this model. Singular perturbation method is used to analyze the effects of the unmodeled high frequency dynamics of the proposed controller. It is shown that the unmodeled dynamics affect the poles of the closed-loop system in the order of O(ε) only. The computer simulations verify the desired performance of the proposed scheme.

Original languageEnglish
Title of host publicationProceedings of the American Control Conference
PublisherPubl by American Automatic Control Council
Pages1529-1533
Number of pages5
ISBN (Print)0780302109
Publication statusPublished - 1992 Dec 1
EventProceedings of the 1992 American Control Conference - Chicago, IL, USA
Duration: 1992 Jun 241992 Jun 26

Publication series

NameProceedings of the American Control Conference
Volume2
ISSN (Print)0743-1619

Other

OtherProceedings of the 1992 American Control Conference
CityChicago, IL, USA
Period92-06-2492-06-26

All Science Journal Classification (ASJC) codes

  • Electrical and Electronic Engineering

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