The prediction of aeroelastic effects is one of the key problems during the design process of an aircraft. One challenging aspect of this goal is to compute space and time-accurate fluid and structural interactions. In the partitioned coupling approach, well-established CFD and CSD (Computational Structural Dynamics) codes are used and integrated in a flexible software environment. One main focus of the present work is on the state and load transfer over nonconforming grids on the coupling interface. To fulfill conservation in the overall solution process, a weak formulation of the continuity conditions on the common interface based on a variational formulation of the scalar energy functional is used and Lagrange multipliers are introduced. Using Galerkin's method leads to a transfer scheme, which minimizes the L2 error norm. An extended transfer approach, which minimizes the more general Sobolev norm will be discussed and applied to aeroelastic problems and further the use of dual-Lagrange multipliers will be presented. To solve the coupled system in a partitioned way, iterative staggered as well as simple staggered time integration schemes will be introduced. Numerical results obtained from simulation of an oscillating one-dimensional plate in transonic flow and a three-dimensional wing example will be presented to demonstrate the applicability and performance of the concepts and to compare the properties of the different coupling techniques and transfer methods.
Coupling techniques for computational nonlinear transient aeroelasticity
Verfahrenskopplung für die numerische, nichtlineare, transiente Aeroelastizität
2006
11 Seiten, 9 Bilder, 20 Quellen
Aufsatz (Konferenz)
Englisch
Coupling techniques for computational non-linear transient aeroelasticity
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