Flight Control Law Using Nonlinear Dynamic Inversion Combined With Quantitative Feedback Theory

[+] Author and Article Information
S. A. Snell, P. W. Stout

Department of Mechanical & Aeronautical Engineering, University of California at Davis, Davis, CA 95616

J. Dyn. Sys., Meas., Control 120(2), 208-215 (Jun 01, 1998) (8 pages) doi:10.1115/1.2802411 History: Received July 23, 1996; Online December 03, 2007


A method of designing control laws for uncertain nonlinear systems is presented. Dynamic inversion is used to partially linearize the dynamics and then a nonlinear version of quantitative feedback theory (QFT) is applied to the resulting system which assures robustness to plant uncertainty. The design yields good performance with low bandwidth. An application to the design of flight control laws for a high performance aircraft is presented. The control laws demonstrate good performance by accurately following large angle of attack commands at flight speeds ranging from 53 to 150 m/s. Robustness is verified by including ±20 percent variations in pitching moment derivatives. The reduced bandwidth compared to a fixed-gain, linear design, leads to greatly reduced actuator transients, which should give improved reliability and longer life for the actuators and associated structure.

Copyright © 1998 by The American Society of Mechanical Engineers
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