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Background/Introduction: <p>Flutter suppression in important for improving the safety and reliability of aircrafts. Due to aeroelasticity in aircraft wings, flutter and limit cycle oscillations may appear. This phenomenon degrades the performance of the aircraft or may even lead to fatigue and failure of the wing’s structure. Flutter is one of the most typical aeroelastic problems.</p> Purpose: <p>Flutter should be suppressed, otherwise the performance of an aircraft may deteriorate. When the flight velocity is raised to a certain value the vibration amplitude remains unchanged and persisting oscillations appear, which constitute the flutter phenomenon. Flutter can damage the wings and can be the reason for aircraft accidents. Therefore, an effective controller design is needed to suppress the flutter phenomenon and to eliminate the related oscillations.</p> Methods: <p>The article proposes a nonlinear optimal control method for flutter suppression and stabilization of aeroelastic wings. The method is applicable to both the underactuated and to the fully actuated dynamic model of the 2-DOF aeroelastic wing. It is proven that the fully actuated model of the aeroelastic wing is differentially flat, which confirms the controllability of this system. The dynamic model of the wing is subject to Taylor series-based linearization and an H-infinity feedback controller is designed for it.</p> Results: <p>To apply the nonlinear optimal control scheme the dynamic model of the wing undergoes approximate linearization with the use of first-order Taylor-series expansion and through the computation of the associated Jacobian matrices. The linearization takes place at each sampling instance around a time-varying operating point which is defined by the present value of the system’s state vector and by the last sampled value of the control inputs vector. To select the stabilizing feedback control gains an algebraic Riccati equation is repetitively solved at each iteration of the control algorithm.</p> Conclusions: <p>The global stability properties of the nonlinear optimal control scheme are proven through Lyapunov analysis. To perform state-estimation-based control, the H-infinity Kalman Filter can be used as a robust state observer. The nonlinear optimal control method is compared against (i) multi-loop flatness-based control, (ii) sliding-mode control. The nonlinear optimal control scheme achieves fast stabilization of the aeroelastic wing under moderate variations of the control inputs. The nonlinear optimal control method can be used in both the case of underactuation and in the case of full actuation of the 2-DOF aeroelastic wing.</p>

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Nonlinear Optimal Control for Flutter Suppression and Stabilization of an Aeroelastic Wing

  • 期刊论文

  • 发表日期：

    2026年3月23日

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  • G. Rigatos,
  • L. Dala,
  • P. Siano,
  • M. Abbaszadeh,
  • M. Zribi,
  • M. Al-Numay

摘要

Background/Introduction:

Flutter suppression in important for improving the safety and reliability of aircrafts. Due to aeroelasticity in aircraft wings, flutter and limit cycle oscillations may appear. This phenomenon degrades the performance of the aircraft or may even lead to fatigue and failure of the wing’s structure. Flutter is one of the most typical aeroelastic problems.

Purpose:

Flutter should be suppressed, otherwise the performance of an aircraft may deteriorate. When the flight velocity is raised to a certain value the vibration amplitude remains unchanged and persisting oscillations appear, which constitute the flutter phenomenon. Flutter can damage the wings and can be the reason for aircraft accidents. Therefore, an effective controller design is needed to suppress the flutter phenomenon and to eliminate the related oscillations.

Methods:

The article proposes a nonlinear optimal control method for flutter suppression and stabilization of aeroelastic wings. The method is applicable to both the underactuated and to the fully actuated dynamic model of the 2-DOF aeroelastic wing. It is proven that the fully actuated model of the aeroelastic wing is differentially flat, which confirms the controllability of this system. The dynamic model of the wing is subject to Taylor series-based linearization and an H-infinity feedback controller is designed for it.

Results:

To apply the nonlinear optimal control scheme the dynamic model of the wing undergoes approximate linearization with the use of first-order Taylor-series expansion and through the computation of the associated Jacobian matrices. The linearization takes place at each sampling instance around a time-varying operating point which is defined by the present value of the system’s state vector and by the last sampled value of the control inputs vector. To select the stabilizing feedback control gains an algebraic Riccati equation is repetitively solved at each iteration of the control algorithm.

Conclusions:

The global stability properties of the nonlinear optimal control scheme are proven through Lyapunov analysis. To perform state-estimation-based control, the H-infinity Kalman Filter can be used as a robust state observer. The nonlinear optimal control method is compared against (i) multi-loop flatness-based control, (ii) sliding-mode control. The nonlinear optimal control scheme achieves fast stabilization of the aeroelastic wing under moderate variations of the control inputs. The nonlinear optimal control method can be used in both the case of underactuation and in the case of full actuation of the 2-DOF aeroelastic wing.