Flutter control based on ultrasonic motor for a two-dimensional airfoil section

Yu, Min; Hu, Haiyan

doi:10.1016/j.jfluidstructs.2011.08.015

Cited by 14 publications

(7 citation statements)

References 17 publications

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“…This nonlinearity added to the absorbers allows them to increase their equivalent stiffness to cancel the detuning. For the mechanical absorber, the stiffness force is given by 3 with values of k nl,3 ranging from 0 (linear absorber) to 800 × k ltva . Figure 6 depicts bifurcation diagrams of the system with MNLTVAs of nonlinear coefficient between 0 and 800 × k ltva .…”

Section: Bifurcation Analysis Of the System With Nonlinear Tuned Vibrmentioning

confidence: 99%

“…This absorber configuration adds a DOF y that measures the displacement of the absorber's mass. A nonlinear version of this absorber with a cubic stiffness of coefficient k nl,3 is also considered so that the total absorber stiffness force is given by (y − h)k ltva + k nl, 3 (y − h) 3 . Throughout the paper, the mechanical absorber is called MLTVA when the nonlinear coefficient k nl,3 is equal to zero and MNLTVA when it is different from zero.…”

Section: Introductionmentioning

confidence: 99%

“…In both cases, the linear absorber is recovered by setting C nl, 3 or k nl,3 to zero. The equations of motion of the system with a mechanical and an electrical absorber are very similar as the inductance plays the role of the inertia, the resistance of the damping and the capacitance of the stiffness.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Flutter and Limit Cycle Oscillation Suppression Using Linear and Nonlinear Tuned Vibration Absorbers

Verstraelen

Kerschen

Dimitriadis

2017

Shock &Amp; Vibration, Aircraft/Aerospace, Energy Harvesting, Acoustics &Amp; Optics, Volume 9

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Aircraft are more than ever pushed to their limits for performance reasons. Consequently, they become increasingly nonlinear and they are more prone to undergo aeroelastic limit cycle oscillations. Structural nonlinearities affect aircraft such as the F-16, which can undergo store-induced limit cycle oscillations (LCOs). Furthermore, transonic buzz can lead to LCOs because of moving shock waves in transonic flight conditions on many aircraft.This study presents a numerical investigation of passive LCO suppression on a typical aeroelastic system with pitch and plunge degrees of freedom and a hardening stiffness nonlinearity. The absorber used is made of a piezoelectric patch glued to the plunge springs and connected to a resistor and an inductance forming a RLC circuit. A mechanical tuned mass damper absorber of similar configuration is also considered. The piezoelectric absorber features significant advantages in terms of size, weight and tuning convenience.The results show that both types of absorber increase the linear flutter speed of the system in a similar fashion but, when optimal, they lead to a sub-critical bifurcation while a super-critical bifurcation was observed without absorber. Finally, it is shown that the addition of a properly tuned nonlinear spring (mechanical absorber) or capacitor (piezoelectric absorber) can restore the super-criticality of the bifurcation. The tuning of the nonlinearity is carried out using numerical continuation.

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Section: Bifurcation Analysis Of the System With Nonlinear Tuned Vibrmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Flutter and Limit Cycle Oscillation Suppression Using Linear and Nonlinear Tuned Vibration Absorbers

Verstraelen

Kerschen

Dimitriadis

2017

Shock &Amp; Vibration, Aircraft/Aerospace, Energy Harvesting, Acoustics &Amp; Optics, Volume 9

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“…Usage of advanced materials to meet high flutter speed requirements with least weight and no penalty on strength is one of the methods suitably employed in different designs. 27 Aerodynamic surfaces reconfiguration, 28–30 nonlinearity’s reduction study, 31,32 and mass distribution change with balance weights 33 are few other methods employed to address the issue. Effect of local structural alterations during design optimization process 34,35 was studied in the last decade and alterations to control actuators and associated aero-servo elastic analysis resulting from various order state space models 36,37 have already been published.…”

Section: Introductionmentioning

confidence: 99%

Computational and experimental studies of horizontal tail flutter suppression

Khan

Ashraf

Shehzad

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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Flutter is an extremely violent instability that may result in catastrophic failure. Thus, flutter clearance test is one of the critical phases in qualification of an aircraft's airworthiness. During design and development process of an aircraft, flutter problems were experienced on an aerodynamic surface (horizontal tail). In order to tackle the observed problem, a number of approaches to optimize the design for flutter speed were computationally and experimentally studied and evaluated. This paper presents and discusses the outcomes of these studies. A hybrid approach based on evaluations and design change constraints has been proposed to suppress the flutter of the horizontal tail.

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“…When the uncertainty in the structural nonlinearity was taken into account, an adaptive control method would be used to depress the aeroelastic flutter (Li et al, 2011). An ultrasonic motor was also used for the flutter control of the aeroelastic system with a nonlinear stiffness in pitch (Yu and Hu, 2012).…”

Section: Introductionmentioning

confidence: 99%