Robust Output Feedback Control For Aeroelastic Vibration Suppression Of A 2-Dof Airfoil Under Quasi-Steady Flow

Keywords

Aeroservoelasticity; disturbance mitigation; MIMO control; nonlinear control; robust control

Abstract

In this paper, a robust output feedback control design is developed for suppression of aeroelastic vibration of a 2-DOF nonlinear wing section system. The aeroelastic system operates in a quasi-steady aerodynamic incompressible flowfield and is actuated using a combination of a leading-edge (LE) and a trailing-edge (TE) flap. By only utilizing measurements of pitching and plunging deflections, an innovative Lyapunov-based procedure is used to design sliding mode control inputs for the LE and TE control surface deflections. The closed-loop system is shown to have semi-global asymptotic stability even in the presence of model uncertainty and unknown external gust loading. Extensive simulation results under a variety of scenarios show the effectiveness of the control strategy.

Publication Date

10-1-2018

Publication Title

JVC/Journal of Vibration and Control

Volume

24

Issue

19

Number of Pages

4604-4619

Document Type

Article

Personal Identifier

scopus

DOI Link

https://doi.org/10.1177/1077546317731209

Socpus ID

85045340254 (Scopus)

Source API URL

https://api.elsevier.com/content/abstract/scopus_id/85045340254

This document is currently not available here.

Share

COinS