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Novel Active Control Strategy for LCO and Flutter Suppression by a Coordinated Use of Multiple Distributed Surface Actuators

[+] Author Affiliations
M. Cassaro, M. Battipede

Politecnico di Torino, Turin, Italy

A. Nágy

Budapest University of Technology & Economics, Budapest, Hungary

P. Marzocca, G. Ahmadi

Clarkson University, Potsdam, NY

Paper No. IMECE2014-36905, pp. V001T01A049; 7 pages
  • ASME 2014 International Mechanical Engineering Congress and Exposition
  • Volume 1: Advances in Aerospace Technology
  • Montreal, Quebec, Canada, November 14–20, 2014
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-4642-1
  • Copyright © 2014 by ASME


The effectiveness of a novel actuation architecture developed to control flutter and post-flutter is investigated in this paper. To this purpose, the performance of an active control strategy in various operational conditions is experimentally examined. A physical prototype, consisting of a wing section with multiple spoilers mounted on an aeroelastic apparatus, has been designed and assembled to carry out open- and closed-loop operations. Wind tunnel aeroelastic testing are performed with a plunging and pitching apparatus specifically designed to simulating wing sections with prescribed stiffness characteristics, including torsional structural nonlinearities responsible of a stable nonlinear post-flutter limit cycle behavior. Five surface mounted spoilers located at 15% of the chord from the leading edge are used to control aeroelastic vibrations in pre- and post-flutter. The spoilers design, including selection of best size and chord position and considering the geometrical constraints, has been carried out by CFD simulation, with the objective of maximizing the aerodynamic pitching moment used to stabilize the lifting surface at the various speeds. The spoiler actuations are commanded by an active control system as to extend the flight region in the natural post-flutter condition. A simple PID algorithm is implemented to test the efficiency of the control system design to suppress flutter oscillation. A trial and error tuning of the gain has been executed on-site during the experimental campaign. Only the pitch angle is used as state feedback in the control laws to stabilize the system above the open-loop flutter velocity. Results and pertinent conclusions are outlined.

Copyright © 2014 by ASME



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