Flight Control Law Using Nonlinear Dynamic Inversion Combined With Quantitative Feedback Theory-Reference-Cited by-同舟云学术

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

Published:1998-06-01 Issue:2 Volume:120 Page:208-215
ISSN:0022-0434
Container-title:Journal of Dynamic Systems, Measurement, and Control
language:en
Short-container-title:

Author:

Snell S. A.¹,Stout P. W.¹

Affiliation:

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

Abstract

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.

Publisher

ASME International

Subject

Computer Science Applications,Mechanical Engineering,Instrumentation,Information Systems,Control and Systems Engineering

Link

http://asmedigitalcollection.asme.org/dynamicsystems/article-pdf/120/2/208/5601043/208_1.pdf

Reference26 articles.

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3. Bugajski D. J. , and EnnsD. F., 1992, “Nonlinear Control Law with Application to High Angle-of-Attack Flight,” J. Guidance, Control and Dynamics, Vol. 15, No. 3, pp. 761–767, May–June.

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