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Robust flutter analysis and control of a wing

Fatehi, M ; Sharif University of Technology | 2012

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  1. Type of Document: Article
  2. DOI: 10.1108/00022661211272981
  3. Publisher: 2012
  4. Abstract:
  5. Purpose - The purpose of this paper is to present a novel approach in aeroservoelastic analysis and robust control of a wing section with two control surfaces in leading-edge and trailing-edge. The method demonstrates how the number of model uncertainties can affect the flutter margin. Design/methodology/approach - The proposed method effectively incorporates the structural model of a wing section with two degrees of freedom of pitch and plunge with two control surfaces on trailing and leading edges. A quasi-steady aerodynamics assumption is made for the aerodynamic modeling. Basically, perturbations are considered for the dynamic pressure models and uncertainty parameters are associated with structural stiffness and structural damping and are accounted for in the model by a Linear Fractional Transformation (LFT) model. The control commands are applied to a first and second order electro-mechanical actuator. Findings - Dynamic performance of aeroelastic/aeroservoelastic system including time responses, system modal specifications, critical flutter speeds, and stability margins are extracted and compared with each other. Simulation results are validated through experiments and are compared to other existing methods available to the authors. Results of simulations with four structural uncertainties and first order controllers have a good agreement with experimental test results. Furthermore, it is shown that by using a high gain second order controller, the aeroservoelastic (ASE) system does not have any coupling nature in frequency response. Originality/value - In this study, modeling, simulation, and robust control of a wing section have been investigated utilizing the μ-Analysis method and the wing flutter phenomenon is predicted in the presence of multiple uncertainties. The proposed approach is an advanced method compared to conventional flutter analysis methods (such as V-g or p-k) for calculating stability margin of aeroelastic/aeroservoelastic systems
  6. Keywords:
  7. Linear fractional transformation ; Nominal flutter margin ; Robust flutter margin ; Structured singular value ; Aerodynamic modeling ; Aeroservoelastic systems ; Aircraft engineering ; Analysis method ; Control command ; Design/methodology/approach ; Dynamic performance ; Dynamic pressures ; Experimental test ; First-order controller ; Flutter analysis ; Flutter margin ; Flutter speed ; High gain ; Leading edge ; Linear Fractional Transformations ; Model uncertainties ; Quasi-steady aerodynamics ; Robust flutter analysis ; Second orders ; Stability margins ; Structural damping ; Structural models ; Structural stiffness ; Structural uncertainty ; Structured singular values ; Time response ; Two degrees of freedom ; Uncertainty parameters ; Wing section ; Actuators ; Aircraft ; Control surfaces ; Control systems ; Electromechanical devices ; Flight control systems ; Flutter (aerodynamics) ; Frequency response ; Model structures ; Robust control ; Structural analysis ; System stability ; Uncertainty analysis ; Aeroservoelasticity
  8. Source: Aircraft Engineering and Aerospace Technology ; Volume 84, Issue 6 , 2012 , Pages 423-438 ; 00022667 (ISSN)
  9. URL: http://www.emeraldinsight.com/doi/abs/10.1108/00022661211272981