Geometrically nonlinear effects in wing aeroelastic dynamics at large deflections

Riso, Cristina; Cesnik, Carlos E. S.

doi:10.1016/j.jfluidstructs.2023.103897

Cited by 15 publications

(7 citation statements)

References 19 publications

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“…The linearized system eigenvalues of a coupled statespace solution of unsteady vortex lattice method and structural model in modal domain show the flutter characteristics change considerably with increasing wing deflection [6]. In agreement, model predictions with nonlinear kinematics show the flutter onset is significantly affected by curvature effects as the wing static deflection increases, but it is reported that such effect (related to a reduction in the wing torsional natural frequencies) is not properly captured by linear kinematics [7].…”

Section: Introductionmentioning

confidence: 73%

“…Examples of such oscillatory phenomena are encountered in highly flexible large aspect-ratio wings, rotating wings of wind turbines and helicopter rotors, turbo-machinery blades, and other structures not necessarily related to the aerospace field (cablestayed bridges, buildings, oil risers etc.) [2,3,[6][7][8][9][10][11].…”

Section: Introductionmentioning

confidence: 99%

“…Geometrically nonlinear aeroelastic models subjected to large deformation are also considered [3,25,26]. The Pazy wing is being established as a benchmark model for the investigation of nonlinear aeroelastic effects in wing dynamics [6,7]. The linearized system eigenvalues of a coupled statespace solution of unsteady vortex lattice method and structural model in modal domain show the flutter characteristics change considerably with increasing wing deflection [6].…”

Section: Introductionmentioning

confidence: 99%

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Wind Tunnel Bench Test of a Pitch-and-Plunge Aeroelastic Model Undergoing Nonlinear Post-Flutter Oscillations

Santos,

Adeodato,

Dağlı

et al. 2024

Preprint

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Purpose: The nonlinear post-flutter aeroelastic behavior of a classical pitch-and-plunge airfoil model in low-speed wind tunnel bench tests is reported in this study for a range of airflow speeds where stable oscillations are observed. Methods: An experimental airfoil prototype is designed, characterized and evaluated. Time domain data of the airfoil motion as well as other pertinent frequency and bifurcation characteristics are presented for different values of airflow speed, starting at the critical linear flutter speed of the airfoil model and increasing up to the sudden manifestation of violent unstable oscillations (when the test is interrupted for the safety of the structural apparatus). Results: Stable post-flutter nonlinear oscillations, mainly attributed to the dynamic stall phenomenon and in a lesser degree to hardening structural effects, are observed for a range of airflow speeds starting at the neutral stability boundary of the aeroelastic system. The amplitudes of oscillation increase with increasing airflow speed and settle onto a limit-cycle. The coupled frequency of oscillation is dominated by the plunge degree-of-freedom and also increases with increasing airflow speed. The observed critical airfoil cut-in speed of limit-cycle onset is about 8.1 \mps, and the observed cut-out speed of unstable response is about 9.5 \mps. Conclusion: This work contributes with the literature of Aeroelasticity by presenting the realization, evaluation, and wind tunnel test data of a pitch-and-plunge airfoil model undergoing nonlinear post-flutter oscillations that may be useful to support other studies for verification purposes of eventual numerical simulations of similar aeroelastic systems.

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Section: Introductionmentioning

confidence: 73%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Wind Tunnel Bench Test of a Pitch-and-Plunge Aeroelastic Model Undergoing Nonlinear Post-Flutter Oscillations

Santos,

Adeodato,

Dağlı

et al. 2024

Preprint

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“…A framework is proposed by Gray et al [41] that integrates geometrically nonlinear, subsonic flutter constraints into aerostructural optimization. An effective framework using nonlinear Reduced Order Models (ROM) for flutter and gust responses is introduced by Chao et al [42]. Ensuring accurate calculation of critical constraints for flutter-free designs necessitates a geometrically nonlinear analysis approach involving static equilibrium computation, linearization, eigenvalue determination, and flutter boundary calculation for optimizing highly flexible wings.…”

Section: Introductionmentioning

confidence: 99%

High Aspect Ratio Composite Wings: Geometrically Nonlinear Aeroelasticity, Multi-Disciplinary Design Optimization, Manufacturing, and Experimental Testing

Farsadi,

Ahmadi,

Sahin

et al. 2024

Aerospace

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In the field of aerospace engineering, the design and manufacturing of high aspect ratio composite wings has become a focal point of innovation and efficiency. These long, slender wings, constructed with advanced materials such as carbon fiber and employing efficient manufacturing methods such as vacuum bagging, hold the promise of significantly lighter aircraft, reduced fuel consumption, and enhanced overall performance. However, to fully realize these benefits, it is imperative to address a multitude of structural and aeroelastic constraints. This research presents a novel aeroelastically tailored Multi-objective, Multi-disciplinary Design Optimization (MMDO) approach that seamlessly integrates numerical optimization techniques to minimize weight and ensure structural integrity. The optimized wing configuration is then manufactured, and a Ground Vibration Test (GVT) and static deflection analysis using the Digital Image Correlation (DIC) system are used to validate and correlate with the numerical model. Within the fully automated in-house Nonlinear Aeroelastic Simulation Software (NAS2) package (version v1.0), the integration of analytical tools offers a robust numerical approach for enhancing aeroelastic and structural performance in the design of composite wings. Nonlinear aeroelastic analyses and tailoring are included, and a population-based stochastic optimization is used to determine the optimum design within NAS2. These analytical tools contribute to a comprehensive and efficient methodology for designing composite wings with improved aeroelastic and structural characteristics. This comprehensive methodology aims to produce composite wings that not only meet rigorous safety and performance standards but also drive cost-efficiency in the aerospace industry. Through this multidisciplinary approach, the authors seek to underscore the pivotal role of tailoring aeroelastic solutions in the advanced design and manufacturing of high aspect ratio composite wings, thereby contributing to the continued evolution of aerospace technology.

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“…Geometric nonlinearities of complex mechanical systems consisting of slender structural members can be modelled with appropriate nonlinear MBS. Such structures include for example slender and elastic aircraft wings, in which the occurring geometrical nonlinearity significantly affects the dynamic behaviour of the wing and thus the aircraft itself [1]. Another example is provided by energy converter turbines, in which turbine blades are being developed to be ever more slender due to increasing rotor sizes.…”

Section: Introductionmentioning

confidence: 99%

On an objective, geometrically exact coupling element for a director-based multi-body finite element framework

Märtins,

Schuster,

Hente

et al. 2024

Multibody Syst Dyn

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In multi-body systems, flexible components and couplings between them can be subject to large displacements and rotations. This contribution presents a general objective and geometrically exact node-to-node coupling element that pursues two innovations. Firstly, the coupling element represents a consistent extension to an existing nonlinear mechanical framework. The coupling element is intended to preserve its attributes of objectivity, path independence and adherence to the energy-conserving or energy-dissipative time integration method. Secondly, beside elasticity, inertia and damping properties are also considered. For this purpose, a director-based formulation is employed within a total Lagrangian description. The avoidance of an angle-based representation, along with the additive updating of state variables, results not only in path independence but also in the avoidance of cumulative errors during extended simulations. An objective deformation measure is chosen based on the Green–Lagrange strain tensor. The inertia forces are considered by an arbitrarily shaped continuum located at the centre of the coupled nodes. Damping is considered by using two different objective first-order dissipation functions, which further ensure energy conservation or dissipation. We successfully demonstrate the coupling element within the mechanical framework on using example applications. Firstly, the geometrically exact behaviour is shown compared to a linear deformation measure. Secondly, we numerically show the path independence of the formulation. The dynamic behaviour is demonstrated in a transient analysis of a damped structure. Finally, the modal analysis of a wind turbine shows the application of the coupling element to model the soil–structure interaction.

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Geometrically nonlinear effects in wing aeroelastic dynamics at large deflections

Cited by 15 publications

References 19 publications

Wind Tunnel Bench Test of a Pitch-and-Plunge Aeroelastic Model Undergoing Nonlinear Post-Flutter Oscillations

Wind Tunnel Bench Test of a Pitch-and-Plunge Aeroelastic Model Undergoing Nonlinear Post-Flutter Oscillations

High Aspect Ratio Composite Wings: Geometrically Nonlinear Aeroelasticity, Multi-Disciplinary Design Optimization, Manufacturing, and Experimental Testing

On an objective, geometrically exact coupling element for a director-based multi-body finite element framework

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