Recovering rotations in aeroelasticity

Ahrem, Regina; Beckert, Armin; Wendland, Holger

doi:10.1016/j.jfluidstructs.2007.02.003

Cited by 10 publications

(8 citation statements)

References 14 publications

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“…Define that us and ua are the deformation shift vector of the structure points and deformation shift vector of CFD grid points respectively, then as  u Hu (3) According to the virtual work principle, the interpolation matrix between the aerodynamic loads and the displacement …”

Section: Interpolation Methods Between Flow Field and Structurementioning

confidence: 99%

“…Although these measures can improve the aerodynamic performance and structure efficiency of large aircraft, static aeroelastic deformation of wing and other components will become more serious. Therefore, a huge number of studies have been conducted in order to predict the influence of aeroelasticity on aerodynamic performances and the structure safety of the aircraft more precisely [1][2][3][4][5].…”

Section: Introductionmentioning

confidence: 99%

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Numerical Simulation Research on the Transonic Aeroelasticity of a High-Aspect-Ratio Wing

Guo¹,

Li²,

Chen³

et al. 2015

IJHT

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A numerical simulation based on CDF/CSD methods is conducted to investigate the transonic static aeroelastic issues of large aircraft. The RANS equation and structural statics equations are utilized as governing equations to do coupling iterative calculation. In order to improve the accuracy and efficiency of CFD, multi-block structured grids are employed for parallel computation and the multi-grid method is used to accelerate convergence. Additionally, a dynamic mesh generation technique, based on a radial basis function (RBF) and the transfinite interpolation (TFI) method is adopted to enhance the efficiency and robustness of grid deformation. Moreover, a thin plate spline interpolation technique of three dimensions is utilized to improve the efficiency of data interpolation, coupled with the calculation of structural deformation based on the virtual work principle. The effectiveness of methods used in this paper is validated by a calculation example employing a static aeroelastic model of a wing-body configuration and independently developed software. Based on static aeroelastic analysis of this model in a typical region of transonic Mach number, several suggestions on static aeroelastic correction of large aircraft's aerodynamic coefficients or derivatives can be given.

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Section: Interpolation Methods Between Flow Field and Structurementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Numerical Simulation Research on the Transonic Aeroelasticity of a High-Aspect-Ratio Wing

Guo¹,

Li²,

Chen³

et al. 2015

IJHT

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“…This approach, though very good for the elastomechanical study of the structure, leads to non‐negligible complications in the procedure of transferring the computed structural displacements to the aerodynamic grid. This problem has been studied in detail by Ahrem et al , whose interpolation method is based on vector‐valued interpolants for the reconstruction of rotations.…”

Section: Beam Structural Modelmentioning

confidence: 99%

“…It is well known that in the beam structural model that not only displacements are given at nodes but also rotations. Ahrem et al derived a novel interpolation method that incorporates the recovery of rotations into the reconstruction process to obtain a more accurate solution. In their interpolation method, they use vector‐valued interpolants for the reconstruction of rotations; that is, the three components of the displacement field are not modelled independently.…”

Section: Introductionmentioning

confidence: 99%

A radial basis function algorithm for simplified fluid‐structure data transfer

Cordero-Gracia

Gómez

Valero

2014

Numerical Meth Engineering

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SUMMARYIn loosely‐coupled aeroelastic computation, the aerodynamic and elastomechanical models are based on different grids and eventually a simplified structural model, like a shell or stick, is considered. CFD tools are applied over the aerodynamic grid, whereas CSM tools are over the structural one. The meshes are usually non‐conforming; thus, three‐dimensional and non‐intrusive interpolation procedures are necessary to transfer structural deformations to the aerodynamic surface grid and aerodynamic loads to the structure. For that purpose, an interpolator based on radial basis functions has been developed. This tool does not require grid connectivities and can be applied to any three‐dimensional data.We have developed two strategies to deal with two special cases of interest. The first is when the structure is represented by a beam model and there is not a proper structural mesh close to the aerodynamic surface. The second is when managing a full configuration aircraft and the problem has been split into some small blocks in such a way that there are aerodynamic nodes belonging to more than one block. Copyright © 2014 John Wiley & Sons, Ltd.

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“…Data exchange approach. Radial basis functions (RBF) [8,9,10] interpolation method has become a well-established tool to interpolate scattered data, which has many advantages, such as easy to realize, high accuracy of the interpolation data, less time-consuming and so on. At the same time, the interpolation method does not depend on the model.…”

Section: Foundation Of Theorymentioning

confidence: 99%

Static Aeroelasticity Analysis of High Aspect Ratio Wing and the Jig-Shape Design Based on Multi-Block Structural Grid

Liu¹,

Bai²,

Hua

2013

AMM

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The influence of structural elastic deformation on the aerodynamic characterisitcs of large transport aircraft has been researched. A method of static aeroelasticity based on multi-block structural grid of high aspect ratio wing has been established, and then a design method of jig-shape is developed. The technology of RBF interpolation is used to exchange the data of CFD/CSD. Based on RBF&Delaunay technology, a mesh motion method is developed to make the design process less time-consuming, which can be applied to large deformation of multi-block structural grid. The static aeroelastic deformation of a wing-body of large transport aircraft is analyzed. Then the wing-body's jig-shape is designed. Compared the aerodynamic characteristics between design cruise shape and target cruise shape, it shows that the aerodynamic characteristics of design cruise shape is almost equal to target cruise shape and the design process of jig-shape is feasible.

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Recovering rotations in aeroelasticity

Cited by 10 publications

References 14 publications

Numerical Simulation Research on the Transonic Aeroelasticity of a High-Aspect-Ratio Wing

Numerical Simulation Research on the Transonic Aeroelasticity of a High-Aspect-Ratio Wing

A radial basis function algorithm for simplified fluid‐structure data transfer

Static Aeroelasticity Analysis of High Aspect Ratio Wing and the Jig-Shape Design Based on Multi-Block Structural Grid

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