Active control method on flutter suppression of a high-aspect-ratio two-dimensional airfoil with a control surface

Yang, Pu; Li, Q. D.; Zhang, Ren; Tan, Qingke; Fan, Yu

doi:10.1109/cgncc.2014.7007599

Cited by 8 publications

(5 citation statements)

References 4 publications

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“…Lee and Singh (2018) designed a scriptL1 adaptive control for AFS in presence of different gust loads shapes and parameters uncertainties including the flap dynamics as a second-order oscillator. Yang et al (2014) applied H∞ loop shaping optimal control theory in order to take into account the presence of uncertainties and disturbances in the control scheme. Jia et al (2019, 2021) proposed a data-driven optimal controller which eliminates the effects of non-modeled dynamics and uncertainties.…”

Section: Introductionmentioning

confidence: 99%

Simple adaptive V-stack piezoelectric based airfoil flutter suppression system

Vindigni

Orlando

2022

Journal of Vibration and Control

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The suppression of aeroelastic vibrations due to flutter using a trailing edge flap is analyzed to increase the speed operability range of wings. The aeroelastic model of a 3DOF airfoil in incompressible flow is presented and an augmented state-space representation is used for the time domain analysis. A finite element model of a V-stack piezoelectric actuator, used to move the trailing edge flap, is introduced to model the actuator dynamics. The use of the simple adaptive controller is investigated to realize an adaptive flutter suppression system. A parallel feedforward compensator is tuned to make the plant almost strictly passive and a metaheuristic algorithm is used to determine the invariant parameters. Numerical simulations are carried out to verify the performance of the simple adaptive flutter suppression system in presence of speed variations and disturbances. Numerical results proved that the SAC flutter suppression system improves the closed loop system flutter boundary with respect to a gain scheduled PID controller.

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Section: Introductionmentioning

confidence: 99%

Simple adaptive V-stack piezoelectric based airfoil flutter suppression system

Vindigni

Orlando

2022

Journal of Vibration and Control

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“…In this way, a continuous input is provided to the controller [12]. In the studies of Na et al [13] and Yang et al [14], the model of a three-degrees-of-freedom airfoil was taken into account. Thus, the dynamic of the aerodynamic surface was considered.…”

Section: Introductionmentioning

confidence: 99%

“…The authors introduced the presence of measure noises and output disturbances, and thus a linear quadratic Gaussian (LQG) controller associated with a sliding mode observer has been implemented, since this architecture is capable of noise decoupling and shows robustness properties to disturbances. Yang et al [14] instead specified that the LQR and LQG controllers are based on mathematical knowledge of the disturbances. Thus, when there are some uncertainties, these strategies lose robustness.…”

Section: Introductionmentioning

confidence: 99%

“…Thus, when there are some uncertainties, these strategies lose robustness. In order to take into account the uncertainties in the design of the controller, Yang et al [14] proposed H ∞ loop shaping, which is implemented by defining a generalized plant that encloses all the dynamic features to be controlled, such as sensors and actuator dynamics and so on, and introducing two different input vectors, namely the control input vector and the exogenous input vector. Then, the disturbance-output transfer function is defined, and the minimization problem of its infinity norm is solved.…”

Section: Introductionmentioning

confidence: 99%

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Computational Analysis of the Active Control of Incompressible Airfoil Flutter Vibration Using a Piezoelectric V-Stack Actuator

Vindigni¹,

Orlando

Milazzo

2021

Vibration

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The flutter phenomenon is a potentially destructive aeroelastic vibration studied for the design of aircraft structures as it limits the flight envelope of the aircraft. The aim of this work is to propose a heuristic design of a piezoelectric actuator-based controller for flutter vibration suppression in order to extend the allowable speed range of the structure. Based on the numerical model of a three degrees of freedom (3DOF) airfoil and taking into account the FEM model of a V-stack piezoelectric actuator, a filtered PID controller is tuned using the population decline swarm optimizer PDSO algorithm, and gain scheduling (GS) of the controller parameters is used to make the control adaptive in velocity. Numerical simulations are discussed to study the performance of the controller in the presence of external disturbances.

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“…The design of limit cycle oscillation suppression systems is extremely important in aircraft applications, since limit cycle oscillations can cause dynamic instability that could result in catastrophic damage [1], [2]. To ease readability in this paper, the following four acronyms will be defined: limit cycle oscillations (LCO); synthetic jet actuators (SJA); small unmanned aerial vehicle (SUAV); and angle of attack (AoA).…”

Section: Introductionmentioning

confidence: 99%

A robust nonlinear output feedback control method for limit cycle oscillation suppression using synthetic jet actuators

Ramos-Pedroza

MacKunis

Golubev

2017

Aerospace Science and Technology

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A synthetic jet actuator-based output feedback control method is presented, which achieves asymptotic limit cycle oscillation regulation in small unmanned aerial vehicle wings, where the dynamic model contains uncertainty and unmodeled external disturbances. In addition, the proposed control method compensates for the parametric uncertainty and nonlinearity inherent in the synthetic jet actuator dynamics. Motivated by the limitations characteristic of small unmanned aerial vehicles, the control method is designed to be computationally inexpensive, eliminating the need for time-varying parameter update laws, function approximators, or other computationally heavy techniques. To this end, a computationally minimal robust-inverse control method is utilized, which is proven to compensate for the uncertainties in both the aerial vehicle dynamics and the synthetic jet actuator dynamics. By endowing the robust-inverse control law with a bank of dynamic filters, asymptotic limit cycle oscillation regulation is achieved using only pitching and plunging displacement measurements in the feedback loop. The result is an asymptotic synthetic jet actuator-based limit cycle oscillation regulation control method, which does not require velocity measurements, adaptive laws, or function approximators in the feedback loop. To achieve the result, a detailed mathematical model of the limit cycle oscillation dynamics is utilized, which includes nonlinear stiffness effects, unmodeled external disturbances, and dynamic model uncertainty, in addition to the parametric uncertainty in the synthetic jet actuator dynamic model. A rigorous Lyapunov-based stability analysis is utilized to prove asymptotic regulation of limit cycle oscillations, and numerical simulation results are provided to demonstrate the performance of the proposed control law.

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Active control method on flutter suppression of a high-aspect-ratio two-dimensional airfoil with a control surface

Cited by 8 publications

References 4 publications

Simple adaptive V-stack piezoelectric based airfoil flutter suppression system

Simple adaptive V-stack piezoelectric based airfoil flutter suppression system

Computational Analysis of the Active Control of Incompressible Airfoil Flutter Vibration Using a Piezoelectric V-Stack Actuator

A robust nonlinear output feedback control method for limit cycle oscillation suppression using synthetic jet actuators

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