Reduced Order Modeling for the Nonlinear Geometric Response of Some Joined Wings

Phlipot, Greg; Wang, Xiaoquan; Mignolet, Marc P.; Demasi, Luciano; Cavallaro, Rauno

doi:10.2514/6.2014-0151

Cited by 15 publications

(12 citation statements)

References 10 publications

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“…A detailed investigation of the eigenvalues and eigvenvectors of the Nastran tangent stiffness matrix, its projection on the 38-mode basis, and of the 38-mode ROM tangent stiffness matrix, see [16] for a similar discussion, demonstrated that the 38-mode basis was not sufficiently rich to properly capture the changes in the dominant transverse modes shortly before, during, and after the mode switching transition. This issue was resolved (as in [16]) by enriching the basis with 3 POD eigenvectors of the residuals of the projection of the first and second eigenvectors of the Nastran tangent stiffness matrix on the 38-mode basis.…”

Section: Coupled Thermal-structural Rom Resultsmentioning

confidence: 98%

“…This issue was resolved (as in [16]) by enriching the basis with 3 POD eigenvectors of the residuals of the projection of the first and second eigenvectors of the Nastran tangent stiffness matrix on the 38-mode basis. These latter eigenvectors were obtained in conditions close and after the mode switching transition.…”

Section: Coupled Thermal-structural Rom Resultsmentioning

confidence: 99%

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Panel Response Prediction Through Reduced Order Models with Application to Hypersonic Aircraft

Matney

Mignolet

Culler

et al. 2015

56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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The present work is the culmination of a series of investigations by the authors on the construction and validation of structural, thermal, and coupled structural-thermal reduced order models (ROMs) for the prediction of the displacements and temperature fields on a representative panel of a hypersonic aircraft during a particular trajectory. The focus of the present paper is first on the development and validation of an efficient strategy for enriching the thermal ROM basis to reflect the temperature distribution induced by the structural deformations through changes of the aerodynamics. Next, the assembly of the thermal and structural ROM bases and the identification of their coefficients is revisited for both cases of constant and temperature dependent coefficient of thermal expansion. The coupled ROM predictions are finally compared to those obtained from full structural and thermal finite element models and it is seen that the ROMs perform overall very well over the large temperature change during the trajectory, from room temperature to 2300F. The only exception to the accuracy of the ROMs is a mode switching event occurring for one of the finite element models but not for the ROMs. This issue is under continued investigation.

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Section: Coupled Thermal-structural Rom Resultsmentioning

confidence: 98%

Section: Coupled Thermal-structural Rom Resultsmentioning

confidence: 99%

Panel Response Prediction Through Reduced Order Models with Application to Hypersonic Aircraft

Matney

Mignolet

Culler

et al. 2015

56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

Self Cite

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“…However, results in this direction have not been quite encouraging. Some recent results are shown in references [9,10].…”

Section: Introductionmentioning

confidence: 91%

Phenomenology of Nonlinear Aeroelastic Responses of Highly Deformable Joined-wings Configurations

Cavallaro

Iannelli

Demasi

et al. 2014

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

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Dynamic aeroelastic behaviour of structurally nonlinear Joined Wings is presented.Three configurations, two characterized by a different location of the joint and one presenting a direct connection between the two wings (Sensorcraft-like layout) are investigated.As a first step, the snap-divergence is studied from a dynamic perspective in order to assess the real response of the configuration. Later on, the investigations focus on the flutter occurrence (critical state) and go further in analyzing postcritical phenomena: Limit Cycle Oscillations (LCOs) are observed followed by a lost of periodicity of the solution as speed is further increased. In some cases, it is also possible to ascertain the presence of period doubling (flip-) bifurcation.Differences between flutter (Hopf 's bifurcation) speed evaluated with linear and nonlinear analyses are discussed in depth, in order to understand if a less computationally intense approach may be used with confidence.Both frequency and time-domain approaches are compared. Moreover, aerodynamic solvers based on the potential flow are critically examined and discussed. In particular, it is assessed in what measure the use of more sophisticated (and computationally more intensive) aerodynamic and interface models impacts the aeroelastic predictions. These differences range from the methods adopted for load transferring to the models employed to describe the wake.When the use of the tools gives different results, a physical interpretation of the leading mechanism generating the mismatch is provided. In particular, for PrandtlPlane-like configurations the aeroelastic response is very sensitive to the wake's shape. As a consequence, it is suggested that a more sophisticated modelling of the wake positively impacts the reliability of aerodynamic and aeroelastic analysis.For Sensorcraft-like configurations some LCOs are characterized by a non-synchronous motion of the inner and outer portion of the lower wing: the wings' tip exhibits a small oscillation during the descending or ascending phase, whereas the mid-span station describes a sinusoidal-like trajectory in the time domain.

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“…In the future, dynamic and aeroelastic analysis will be considered with the use on reduced models (comparison with the approach presented in Reference [48] will also be pursued). Further investigation needs to be performed for the best strategy for basis update.…”

Section: Recommendations and Further Researchmentioning

confidence: 99%

A Computational Method for Structurally Nonlinear Joined Wings Based on Modal Derivatives

Teunisse

Demasi

Tiso

et al. 2014

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

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Past studies showed that the overconstrained nature of Joined Wings and the strong structural geometric nonlinearities make difficult the use of standard packages of aeroelastic solvers (usually modally reduced and frequency domain based) which have been effectively adopted by the industry for decades. We present here a study on the reduction of the computational cost in presence structural nonlinear effects that cannot be neglected in Joined Wings, even at small angles of attack and attached flow. In particular, a reduced order model is achieved with a basis constituted by vibration modes augmented with the corresponding modal derivatives. The results can be considered excellent when compared to the full order reference solution. However, a convergence test showed that the required number of vectors is relatively high and the basis needs to be often updated to achieve the best performance. More investigations will be necessary for an effective use in the industry and complicate dynamic problems involving the unsteadiness of the aerodynamics.

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Reduced Order Modeling for the Nonlinear Geometric Response of Some Joined Wings

Cited by 15 publications

References 10 publications

Panel Response Prediction Through Reduced Order Models with Application to Hypersonic Aircraft

Panel Response Prediction Through Reduced Order Models with Application to Hypersonic Aircraft

Phenomenology of Nonlinear Aeroelastic Responses of Highly Deformable Joined-wings Configurations

A Computational Method for Structurally Nonlinear Joined Wings Based on Modal Derivatives

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