Aeroelastic Calculations for the Hawk Aircraft Using the Euler Equations

Woodgate, M.; Badcock, K. J.; Rampurawala, Abdul; Richards, B. E.; Nardini, D.; Henshaw, MJdeC

doi:10.2514/1.5608

Cited by 33 publications

(23 citation statements)

References 14 publications

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“…The systems (8) and (10) constitute the original RBF formulation defined to perform CFD-CSM interpolation. In this case, the inclusion of a polynomial term (5), at least of first order, is mandatory to ensure conservation of total force and moment [19].…”

Section: Mathematical Formulationmentioning

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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Section: Mathematical Formulationmentioning

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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“…Non-linear flutter phenomena including limit cycle oscillations (LCO) are known to be related to aerodynamic contributions of the stores and not just their inertia effects (see Woodgate et al [3]). Since the mutual aerodynamic interference of the wing and the stores cannot be neglected, the stores and their surrounding flow must be adequately modeled.…”

Section: Introductionmentioning

confidence: 99%

“…Demonstrations of the potential of such methods for engineering analysis include studies by Melville [1], Pranata et al [2], and Woodgate et al [3] with structured grids method to Farhat and Lesoinne [4] with unstructured grids methods. Farhat et al [5] impressively demonstrated that aeroelastic parameters of a complete F-16 configuration at five different transonic Mach numbers can be computed in a single day with a 128-processor machine.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic simulations using gridless boundary condition and small perturbation techniques

2010

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“…1189 monolithic and partitioned approaches have been proposed to cope with the multi-disciplinary nature of the problem. The monolithic approach uses a tailored aero-structural solver [1, 2], while the partitioned approach favours the coupling of existing structural and fluid solvers [3][4][5][6][7][8][9]. The partitioned approach is used almost as standard, including within the CFD Group at the University of Bristol [6-9], because it allows the use of existing software and grids, but synchronization of the structure and fluid at each time level must be done iteratively [6,7,9].However, the partitioned approach raises a difficult question in terms of information transfer.…”

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confidence: 99%

Improved radial basis function fluid–structure coupling via efficient localized implementation

Rendall

Allen

2009

Numerical Meth Engineering

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SUMMARYPrevious work by the authors has developed a universal interpolation scheme, using radial basis functions (RBFs), which results in a unified formulation for robust fluid-structure interpolation and high-quality mesh motion. The method has several significant advantages. Primarily, all volume mesh, structural mesh, and flow-solver-type dependence is removed entirely, as all operations are performed on totally arbitrary point clouds of any form. Hence, all connectivity requirements are removed from both the coupling and mesh motion problems. Furthermore, only matrix-vector multiplications are required during unsteady simulation because dependence relations are computed once prior to any simulation and then remain constant. This property means that the method is both perfectly parallel and totally independent from the flow-solver. However, the full method is expensive, since the dependence matrix between two sets of points is N points 1 × N points 2 . The fluid-structure coupling behaviour can also be influenced by parameters used in the interpolation. To alleviate these difficulties a more efficient form of the RBF fluid-structure coupling is presented, which also greatly reduces the interpolation parameter influence. A pointwise form of the partition of unity approach is developed that localizes the interpolation, with results presented for static aeroelastic simulations of the Brite-Euram multi-disciplinary optimization wing using a very fine mesh containing 58 000 surface points. It is shown that a 58× reduction in data size is achieved, and equally importantly the interpolation has a much smaller influence on final aeroelastic results.

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Aeroelastic Calculations for the Hawk Aircraft Using the Euler Equations

Cited by 33 publications

References 14 publications

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

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

Aeroelastic simulations using gridless boundary condition and small perturbation techniques

Improved radial basis function fluid–structure coupling via efficient localized implementation

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