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      Lift Regulation During Transverse Gust Encounters Using a Modified Goman–Khrabrov Model

      research-article
      * ,
      AIAA Journal
      American Institute of Aeronautics and Astronautics
      Angle of Attack, angle of attack, angle-of-attack, angles of attack, lift coefficient, Closed-Loop Control, Closed-loop control, LQR, Open-Loop, Open-loop, closed-loop, closed-loop control, linear quadratic regulator, open-loop, proportional control, Reynolds number, aerodynamic loading, downwash, freestream, freestream velocity, lift force, airfoil chord, camber, chord line, fluid density, velocity profile, pitching kinematics, lift of a wing, NACA 0012, Thin airfoil theory, airfoil profile, pitching airfoil, thin airfoil, thin airfoil theory, EKF, Kalman filter, UKF, extended Kalman filter, unscented Kalman filter, vortex, vortex sheet, vortex's, vortices

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          Abstract

          This paper presents a framework for the estimated state regulation of the lift force for a maneuvering wing during a transverse gust encounter. An expression for the effective angle of attack of the wing is derived and used to construct a modified Goman–Khrabrov (GK) model for wing–gust encounters. Experiments were carried out in the University of Maryland water towing facility to identify parameters in the modified GK model and to evaluate its ability to represent gust encounters of varying gust strengths. Using this gust-encounter model, an observer-based feedback controller for pitch actuation is constructed to regulate the coefficient of lift of a wing during a transverse gust encounter. Closed-loop control simulations provided pitching kinematics that mitigated the transient force response. Gust encounter experiments were performed using the control signal from simulation as an open-loop control signal during an encounter with a known gust. The lift force time histories of the gust encounter experiments with control show effective mitigation of the peak lift force. The wing experienced transient forces that merit further investigation, including an initial transient peak and a later undershoot that may be due to uncertainty in the start of the gust region.

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          Most cited references34

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          Airfoil Theory for Non-Uniform Motion

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                Author and article information

                Conference
                aiaaj
                AIAA Journal
                AIAA Journal
                American Institute of Aeronautics and Astronautics
                1533-385X
                28 April 2020
                September 2020
                : 58
                : 9
                : 3788-3798
                Affiliations
                University of Maryland , College Park, Maryland 20742
                University at Buffalo, The State University of New York , Buffalo, New York 14260
                Author notes
                [*]

                Graduate Research Assistant, Department of Aerospace Engineering. Student Member AIAA.

                [†]

                Associate Professor, Department of Aerospace Engineering. Associate Fellow AIAA.

                [‡]

                Assistant Professor, Department of Mechanical and Aerospace Engineering. Senior Member AIAA.

                Article
                J059127 J059127
                10.2514/1.J059127
                2b7e136d-3d45-4706-accd-b9e7ea210add
                Copyright © 2020 by Girguis Sedky. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-385X to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.
                History
                : 7 October 2019
                : 30 March 2020
                : 30 March 2020
                Page count
                Figures: 11, Tables: 0
                Funding
                Funded by: Air Force Office of Scientific Researchhttp://dx.doi.org/10.13039/100000181
                Award ID: FA9550-16-1-0508
                Categories
                Regular Articles
                p2263, Fluid Dynamics
                p2132, Aircraft Operations and Technology
                p2228, Aerospace Sciences
                p2073, Aeronautics
                p2089, Guidance, Navigation, and Control Systems
                p20543, Aerodynamic Performance
                p1927, Control Theory
                p1804, Aerodynamics
                p20613, Airfoil Nomenclature
                p3278, Fluid Flow Properties
                p20592, Aircraft Kinematics
                p1830, Fixed-Wing Aircraft
                p1812, Airfoil
                p6227, Kalman Filter
                p1973, Vortex Dynamics

                Engineering,Physics,Mechanical engineering,Space Physics
                unscented Kalman filter,vortices,closed-loop,lift force,lift of a wing,angle-of-attack,closed-loop control,freestream velocity,extended Kalman filter,freestream,linear quadratic regulator,downwash,aerodynamic loading,Angle of Attack,angles of attack,open-loop,Reynolds number,UKF,proportional control,vortex's,Kalman filter,lift coefficient,EKF,thin airfoil theory,angle of attack,Closed-Loop Control,thin airfoil,vortex sheet,pitching airfoil,Closed-loop control,airfoil profile,Thin airfoil theory,LQR,NACA 0012,vortex,pitching kinematics,Open-Loop,velocity profile,fluid density,Open-loop,chord line,camber,airfoil chord

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