I-O map inversion, zero dynamics and flight control

Author

Romano, James J. ; Singh, Sahjendra N.

Author_Institution

Dept. of Comput. Sci. & Electr. Eng., Nevada Univ., Las Vegas, NV, USA

Volume

26

Issue

6

fYear

1990

fDate

11/1/1990 12:00:00 AM

Firstpage

1022

Lastpage

1029

Abstract

The trajectory control of aircraft in rapid, nonlinear maneuvers is discussed. Based on nonlinear invertibility theory, a control law is derived to independently control roll, pitch, and sideslip angles using rudder, elevator, and aileron. Integral feedback is introduced in order to obtain robustness in the control system to parameter uncertainty. The stability of the zero dynamics is examined. Simulation results are presented to show that in a closed-loop system, precise simultaneous lateral and longitudinal maneuvers can be performed despite the presence of uncertainty in the stability derivatives

Keywords

aircraft control; closed loop systems; feedback; nonlinear control systems; stability; I-O map inversion; aileron; aircraft; closed-loop system; control law; elevator; flight control; integral feedback; longitudinal maneuvers; nonlinear invertibility theory; nonlinear maneuvers; parameter uncertainty; pitch; robustness; roll; rudder; sideslip angles; simulation; stability; trajectory control; zero dynamics; Aerospace control; Aircraft; Control systems; Elevators; Feedback; Nonlinear dynamical systems; Robust control; Stability; Uncertain systems; Uncertainty;

fLanguage

English

Journal_Title

Aerospace and Electronic Systems, IEEE Transactions on

Publisher

ieee

ISSN

0018-9251

Type

jour

DOI

10.1109/7.62254

Filename

62254