Reliability-based aeroelastic optimization of a composite aircraft wing via fluid-structure interaction of high fidelity solvers

We consider reliability based aeroelastic optimization of a AGARD 445.6 composite aircraft wing with stochastic parameters. Both commercial engineering software and an in-house reliability analysis code are employed in this high-fidelity computational framework. Finite volume based flow solver Fluen...

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Bibliographic Details
Published in:IOP conference series. Materials Science and Engineering 2010-06, Vol.10 (1), p.012037-012037
Main Authors: Nikbay, M, Fakkusoglu, N, Kuru, M N
Format: Article
Language:English
Subjects:
Accuracy
Aeroelasticity
Aircraft
Algorithms
Commercial aircraft
Euler-Lagrange equation
Finite element method
Fluid-structure interaction
Mathematical models
Matlab
Mesh generation
Optimization
Quadratic programming
Reliability analysis
Reliability engineering
Software engineering
Software reliability
Solvers
Statistical analysis
Structural response
Three dimensional models
Wings (aircraft)
Workflow
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Summary:We consider reliability based aeroelastic optimization of a AGARD 445.6 composite aircraft wing with stochastic parameters. Both commercial engineering software and an in-house reliability analysis code are employed in this high-fidelity computational framework. Finite volume based flow solver Fluent is used to solve 3D Euler equations, while Gambit is the fluid domain mesh generator and Catia-V5-R16 is used as a parametric 3D solid modeler. Abaqus, a structural finite element solver, is used to compute the structural response of the aeroelastic system. Mesh based parallel code coupling interface MPCCI-3.0.6 is used to exchange the pressure and displacement information between Fluent and Abaqus to perform a loosely coupled fluid-structure interaction by employing a staggered algorithm. To compute the probability of failure for the probabilistic constraints, one of the well known MPP (Most Probable Point) based reliability analysis methods, FORM (First Order Reliability Method) is implemented in Matlab. This in-house developed Matlab code is embedded in the multidisciplinary optimization workflow which is driven by Modefrontier. Modefrontier 4.1, is used for its gradient based optimization algorithm called NBI-NLPQLP which is based on sequential quadratic programming method. A pareto optimal solution for the stochastic aeroelastic optimization is obtained for a specified reliability index and results are compared with the results of deterministic aeroelastic optimization.
ISSN:1757-899X
1757-8981
1757-899X
DOI:10.1088/1757-899X/10/1/012037