NDLI: Comparison of SDRE and SMC control approaches for flutter suppression in a nonlinear wing section

Content Provider	IEEE Xplore Digital Library
Author	Elhami, M.R. Narab, M.F.
Copyright Year	2012
Abstract	The effect of flutter phenomenon on dynamic stability of aeroelastic systems is a main interest of recent studies. Among many approaches for suppression of flutter, in this paper two control strategies are introduced and their results are compared. State-Dependent Riccati Equation (SDRE) approach and Sliding Mode Control (SMC) approach are used for stabilization of an Aeroservoelastic system with structural nonlinearities at subsonic flight speed regime. These two control techniques suppress flutter as well as reduce the vibration level in sub-critical and post-flutter speeds. The developed aeroservoelastic model describes the pitch and plunge motion of a wing section associated with a single control surface. For state-space representation of the model, the measured pitch angle, plunge displacement and their derivatives are allocated as state vector, and control surface deflection as input command. For a given initial state conditions, two modes of open loop and closed loop control system are simulated. It is shown that, with a nonlinear structure in subsonic regime, the open loop system is unstable and Limit Cycle Oscillations (LCOs) are generated. However, the closed loop system is asymptotically stable and converges to the origin. Therefore, the proposed approaches have a good performance on suppressing flutter and LCOs. However, comparing between the two approaches shows that SMC method requires larger control input, as well as a shorter time response with respect to SDRE method.
Sponsorship	IEEE Control Syst. Soc.
Starting Page	6148
Ending Page	6153
File Size	1651813
Page Count	6
File Format	PDF
ISBN	9781457710957
ISSN	07431619
e-ISBN	9781457710964
e-ISBN	9781467321020
DOI	10.1109/ACC.2012.6314699
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2012-06-27
Publisher Place	Canada
Access Restriction	Subscribed
Rights Holder	American Automatic Control Council(AACC)
Subject Keyword	Mathematical model Closed loop systems Time factors Aircraft Equations Symmetric matrices Aerodynamics
Content Type	Text
Resource Type	Article
Subject	Electrical and Electronic Engineering

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