Application of sliding-mode control to an aircraft with pitching moment nonlinearity

S. W. Liu; T. Singh

Application of sliding-mode control to an aircraft with pitching moment nonlinearity

S. W. Liu
, T. Singh

Department of Mechanical and Aerospace Engineering

SUNY Buffalo

Research output: Contribution to conference › Paper › peer-review

1 Scopus citations

Abstract

A flight control law is designed using the sliding mode control strategy for an aircraft containing pitching moment nonlinearities due to angle-of-attack variation. The performance of this control law is evaluated using the C* criterion. Results indicate that the robustness is superior to that of a traditional PPI control system for full range of pilot commands. To minimize control chattering which is characteristic of the sliding-mode controller, we incorporate a boundary layer around the sliding surface.

Original language	English
Pages	1094-1101
Number of pages	8
State	Published - 1995
Event	Guidance, Navigation, and Control Conference, 1995 - Baltimore, United States Duration: Aug 7 1995 → Aug 10 1995

Conference

Conference	Guidance, Navigation, and Control Conference, 1995
Country/Territory	United States
City	Baltimore
Period	08/7/95 → 08/10/95

Cite this

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title = "Application of sliding-mode control to an aircraft with pitching moment nonlinearity",

abstract = "A flight control law is designed using the sliding mode control strategy for an aircraft containing pitching moment nonlinearities due to angle-of-attack variation. The performance of this control law is evaluated using the C* criterion. Results indicate that the robustness is superior to that of a traditional PPI control system for full range of pilot commands. To minimize control chattering which is characteristic of the sliding-mode controller, we incorporate a boundary layer around the sliding surface.",

author = "Liu, \{S. W.\} and T. Singh",

note = "Publisher Copyright: {\textcopyright} 1995 by S-W Liu.; Guidance, Navigation, and Control Conference, 1995 ; Conference date: 07-08-1995 Through 10-08-1995",

year = "1995",

language = "English",

pages = "1094--1101",

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TY - CONF

T1 - Application of sliding-mode control to an aircraft with pitching moment nonlinearity

AU - Liu, S. W.

AU - Singh, T.

PY - 1995

Y1 - 1995

N2 - A flight control law is designed using the sliding mode control strategy for an aircraft containing pitching moment nonlinearities due to angle-of-attack variation. The performance of this control law is evaluated using the C* criterion. Results indicate that the robustness is superior to that of a traditional PPI control system for full range of pilot commands. To minimize control chattering which is characteristic of the sliding-mode controller, we incorporate a boundary layer around the sliding surface.

AB - A flight control law is designed using the sliding mode control strategy for an aircraft containing pitching moment nonlinearities due to angle-of-attack variation. The performance of this control law is evaluated using the C* criterion. Results indicate that the robustness is superior to that of a traditional PPI control system for full range of pilot commands. To minimize control chattering which is characteristic of the sliding-mode controller, we incorporate a boundary layer around the sliding surface.

UR - https://www.scopus.com/pages/publications/84959149795

M3 - Paper

AN - SCOPUS:84959149795

SP - 1094

EP - 1101

T2 - Guidance, Navigation, and Control Conference, 1995

Y2 - 7 August 1995 through 10 August 1995

ER -

Application of sliding-mode control to an aircraft with pitching moment nonlinearity

Abstract

Conference

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