A multi-disiplinary code coupling approach for analysis and optimization of aeroelastic systems

We consider the static aeroelastic analysis and optimization of aircraft wings for steady-state conditions while both aerodynamic and structural parameters can be used as optimization variables. The core effort of this work lies on developing a robust methodology to couple commercial codes for a full aeroelastic optimization purpose to yield a convenient adaptation to engineering applications in industry. A commercial finite volume based flow solver Fluent-6.3.26 is used to solve inviscid 3D Euler equations, Gambit as the fluid do-main mesh generator and Catia-V5-R16 as a parametric 3D solid modeler. Abaqus-6.7.1, a structural finite element method 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 aeroelastic analysis by employing a staggered algorithm. Modefrontier-4.0 is used as a multi-objective and multidisiplinary optimization software with both gradient-based and gradient-free optimization algorithms. Aeroelastic optimization is performed for a basic experimental wing model based on AGARD 445.6 elastic wing configuration with multi-objectives of maximum lift over drag ratio and minimum weight of the wing. Static aeroelastic criteria on maximum tip deflection are given as design constraints. Optimization variables are chosen as sweep angle at the quarter chord and the taper ratio of the wing. A genetic algorithm NSGA-II is used to control the optimization process. The aeroelastic analysis results produced a good agreement with the experimental data given in literature and the the aeroelastic optimization study resulted with a set of pareto optimal values.