Aeroelastic tailoring of nonlinear typical section using the method of multiple scales to predict post-flutter stable LCOs

Sanches, Leonardo; Guimarães, Thiago A.; Marques, Flávio D.

doi:10.1016/j.ast.2019.04.031

Cited by 36 publications

(10 citation statements)

References 21 publications

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“…Marsden and Price (2005) and Yang et al (2016) even verified the reliability of the numerical simulation results through the experiment. In Sanches et al (2019), a typical section with hardening nonlinearity in pitching stiffness was investigated to expand the flutter onset boundary and minimum stable LCO amplitudes in post-flutter. In Huang et al (2013); Frampton and Clark (2000), the numerical simulation and results both presented the LCO behavior produced by the structural free-play nonlinearity associated with the control surface.…”

Section: Introductionmentioning

confidence: 99%

Data-driven active flutter control of airfoil with input constraints based on adaptive dynamic programming method

Jia

Tang

Sun

et al. 2021

Journal of Vibration and Control

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The stable flight region can be extended by adding control flap at the wing trailing edge and combined with active control technology. We studied the active flutter control by considering the input constraints. By designing the data-driven optimal controller, the limit cycle oscillations of a typical two-dimensional airfoil wing can be suppressed with single trailing edge control surface. The traditional control methods always need a precise mathematical model of the system, which put high requirements on system modeling. In this study, a novel data-driven optimal controller is proposed by using the input–output data and without depending on the nonlinear system dynamic model. This model-free approach avoids the effects of modeling errors and system uncertainty. When the data-driven controller is applied, the limit cycle oscillation phenomenon of the airfoil wing is eliminated within several seconds. It can be seen from the numerical simulation result that the data-driven adaptive dynamic programming control method possess superiority and feasibility.

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Section: Introductionmentioning

confidence: 99%

Data-driven active flutter control of airfoil with input constraints based on adaptive dynamic programming method

Jia

Tang

Sun

et al. 2021

Journal of Vibration and Control

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“…They discussed the relationship of this bifurcation with the contributions of higher harmonics in the system responses. Recently, Sanches et al (2019) used the method of multiple scales (MMS) to predict the nonlinear flutter boundary of an airfoil with a control surface considering pitch hardening stiffness. They also presented an aeroelastic tailoring procedure to design optimal nonlinear typical sections constrained to slower post-flutter LCO amplitude growth.…”

Section: Introductionmentioning

confidence: 99%

Characterization of typical aeroelastic sections under combined structural concentrated nonlinearities

Silva

Marques

2021

Journal of Vibration and Control

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Structural nonlinearities are usually present in aeroelastic systems. The analysis of this system commonly comprises a study involving only one type of nonlinearity, influencing a particular motion of the airfoil. However, practical applications of aeroelastic systems can be affected by different types of structural nonlinearities. It becomes essential to study the stability of the aeroelastic system under these conditions to assess more real operational flight procedures. In this context, this article presents an investigation of a typical aeroelastic section response with trailing edge control surface subjected to combinations of concentrated structural nonlinearities. Different nonlinear scenarios involving cubic hardening stiffness in pitching and free play, free play with preload, and slip dry friction in the trailing edge control surface motion are analyzed. The mathematical model is based on linear unsteady aerodynamics coupled to a three-dof typical aeroelastic section. Hopf bifurcations diagrams are obtained from direct time integration of the equation of motion. The post-flutter limit cycle oscillations are investigated, revealing supercritical and subcritical bifurcations. A complete parametric study of the nonlinear parameters is carried out, thereby allowing a sensitivity analysis of each nonlinear scenario. The results show that aeroelastic tailoring considering the mild post-flutter behavior can be achieved through an appropriate choice of combined nonlinear effects. Moreover, combined nonlinearities can mitigate the undesired subcritical aeroelastic responses caused by free play.

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“…The piezoelectric patch utilizes these oscillations to harvest electrical energy [27,28]. In designing of piezoelectric aeroelastic energy harvester (PAEH), it is important to consider the phenomenon of flutter [29]. Figure 1 depicts the sub-critical Hopf bifurcation, that occurs when the flow velocity is less than linear flutter velocity.…”

Section: Introductionmentioning

confidence: 99%

Numerical and experimental investigation of piezoelectric energy harvester based on flag-flutter

Eugeni

Elahi

Fune

et al. 2020

Aerospace Science and Technology

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Aeroelastic tailoring of nonlinear typical section using the method of multiple scales to predict post-flutter stable LCOs

Cited by 36 publications

References 21 publications

Data-driven active flutter control of airfoil with input constraints based on adaptive dynamic programming method

Data-driven active flutter control of airfoil with input constraints based on adaptive dynamic programming method

Characterization of typical aeroelastic sections under combined structural concentrated nonlinearities

Numerical and experimental investigation of piezoelectric energy harvester based on flag-flutter

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