Suppression of Limit Cycle Oscillations with a Nonlinear Energy Sink: Experimental Results

Hill, Wallace; Strganac, Thomas W.; Lee, Young S.; Kerschen, Gaëtan; Vakakis, Alexander F.; Bergman, Lawrence A.

doi:10.2514/6.2006-1848

Cited by 6 publications

(6 citation statements)

References 26 publications

(24 reference statements)

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“…However, for nonlinear connections, the restoring force is a nonlinear function of the relative displacement δ, i.e., f Je,W = k non ðδÞ • δ . Substituting the restoring force expression to Equation (13) and therefore the entire structure is reduced under generalized coordinates q.…”

Section: Extended Free-interface Component Mode Synthesismentioning

confidence: 99%

“…And an aeroelastic test was carried out on a foam-aluminum-fiberglass rigid wing in an open-circuit blower-like wind tunnel, as well as nonlinear time series analysis served to investigate the behavior and bifurcations of freeplay. A series of studies on flutter suppression technique was also evaluated by wind tunnel tests on a 3-DOF airfoil model [11][12][13].…”

Section: Introductionmentioning

confidence: 99%

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An Integrated Test-Based Nonlinear Aeroelastic Analysis Method to Freeplay-Induced Limit-Cycle Oscillations

Sun

Yang

et al. 2022

International Journal of Aerospace Engineering

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The nonlinear limit-cycle oscillations induced by aileron rotational freeplay are investigated by numerical simulation and flutter wind tunnel tests. An integrated nonlinear aeroelastic analysis method and procedure based on the nonlinear system identification technology is proposed. Based on the characteristics of the structure, a low-speed nonlinear flutter wing-aileron model that considers both the linear flutter test and the nonlinear limit-cycle oscillation test with aileron rotational freeplay is designed. The wind tunnel tests are conducted with the model, and the stable limit-cycle oscillation is observed by accelerometers under the linear flutter boundary with a 0° angle of attack. Higher-order harmonic vibration is also observed with a low proportion compared to the fundamental oscillation, and the limit-cycle oscillation grows gradually with the increase of airspeed until flutter occurs. The comparison of numerical and experimental investigation shows high consistency.

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Section: Extended Free-interface Component Mode Synthesismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

An Integrated Test-Based Nonlinear Aeroelastic Analysis Method to Freeplay-Induced Limit-Cycle Oscillations

Sun

Yang

et al. 2022

International Journal of Aerospace Engineering

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“…Block et al [3] used a full-state feedback controller that demonstrated the ability to stabilize the nonlinear aeroelastic testing apparatus system at twice the open loop flutter velocity. Also, passive control techniques were explored by Hill et al [4] that demonstrated a nonlinear energy sink device to be effective in increasing the overall stability threshold of the aeroelastic system. In recent years, several active linear and nonlinear control capabilities have been implemented.…”

Section: Introductionmentioning

confidence: 99%

“…Due to the physical constraints of the wing it is considered to be rigid, with all the elastic properties concentrated in the springs and cam system. The constructed test apparatus is based on existing test beds developed at Texas A&M University and NASA Langley Research Center [4,15]. The apparatus features independent pitch and plunge movement that will allow the wing to exhibit plunging pitching flutter and LCO at a certain frequency and dynamic pressure.…”

Section: Introductionmentioning

confidence: 99%

Design of a Wind Tunnel Apparatus to Assist Flow and Aeroelastic Conrtol via Zero Net Mass Flow Actuators

O'Donnell

Marzocca

Milanese

et al. 2007

48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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A plunging-pitching aeroelastic apparatus has been developed to experimentally test new devices for flow and aeroelastic control. The purpose of the experiment is twofold: i) the first phase investigates the aeroelastic behavior of a two-dimensional wing section in postflutter region, structurally and aerodynamically characterizing the aeroelastic model; ii) the subsequent experiment will be instrumental to test active flow control devices in both the pre-and post-flutter regimes. The design of the testing apparatus utilizes a linear and nonlinear cam spring system that allows testing at selected aeroelastic and flowfield conditions. The wing section is mounted to the aeroelastic test apparatus and tests have been conducted in the low speed Clarkson University Wind Tunnel Facility. Plunging and pitching accelerations of the wing during aeroelastic response have been recorded to study and compare the experimental results with the proposed mathematical models. Active flow control devices are bench tested and will be installed in a composite NACA 0018 airfoil at specified locations along the wing span. Zero net mass flow actuators (ZNMF) are considered in this research: ZNMF control devices, such as synthetic jets actuators (SJA) and frequency driven voice coils, are under investigation to demonstrate their ability to actively change the flowfield for improved aeroelastic wing performances. Numerical simulations have already demonstrated improved performance regarding flow and aeroelastic characteristics due to active flow control. Experimental investigation, numerical studies, and corresponding analytical models are provided and pertinent conclusions are discussed.

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“…5 In Ref., 6 the stability threshold for a two degrees of freedom aeroelastic system was increased by a nonlinear energy sink, based on the principle of nonlinear energy pumping. In Ref.…”

Section: Introductionmentioning

confidence: 99%

A Nonlinear Controller for Flutter Suppression: from Simulation to Wind Tunnel Testing

Ronch

Tantaroudas

Jiffri

et al. 2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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Active control for flutter suppression and limit cycle oscillation of a wind tunnel wing section is presented. Unsteady aerodynamics is modelled with strip theory and the incompressible two-dimensional classical theory of Theodorsen. A good correlation of the stability behaviour between simulation and experimental data is achieved. The paper focuses on the introduction of a nonlinearity in the plunge degree of freedom of an experimental wind tunnel test rig and the design of a nonlinear controller based on partial feedback linearization. To demonstrate the advantages of the nonlinear synthesis on linear conventional methods, a linear controller is implemented for the nonlinear system that exhibits limit cycle oscillations above the linear flutter speed. The controller based on partial feedback linearization outperforms the linear control strategy based on pole placement. Whereas feedback linearization allows to suppress fully the limit cycle oscillations, the pole placement fails to achieve any significant reduction in amplitudes.

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Suppression of Limit Cycle Oscillations with a Nonlinear Energy Sink: Experimental Results

Cited by 6 publications

References 26 publications

An Integrated Test-Based Nonlinear Aeroelastic Analysis Method to Freeplay-Induced Limit-Cycle Oscillations

An Integrated Test-Based Nonlinear Aeroelastic Analysis Method to Freeplay-Induced Limit-Cycle Oscillations

Design of a Wind Tunnel Apparatus to Assist Flow and Aeroelastic Conrtol via Zero Net Mass Flow Actuators

A Nonlinear Controller for Flutter Suppression: from Simulation to Wind Tunnel Testing

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