Title

I-O Map Inversion, Zero Dynamics and Flight Control

Document Type

Article

Publication Date

11-1990

Publication Title

Institute of Electrical and Electronics Engineers Transactions on Aerospace and Electronic Systems

Volume

25

First page number:

1022

Last page number:

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

Aerospace control; Aircraft; Airplanes – Control systems; Elevators; Feedback control systems; Flight control; Nonlinear dynamical systems; Nonlinear systems; Robust control; Stability; Stability of airplanes; Uncertain systems; Uncertainty

Permissions

Use Find in Your Library, contact the author, or use interlibrary loan to garner a copy of the article. Publisher copyright policy allows author to archive post-print (author’s final manuscript). When post-print is available or publisher policy changes, the article will be deposited

Identifier

DOI: 10.1109/7.62254

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