Transonic aeroelastic stability analysis using a kriging–based schur complement formulation

An efficient approach is presented to search for transonic aeroelastic instability of realistic aircraft structures in multidimensional parameter spaces. Aeroelastic instability is predicted by a small nonlinear eigenvalue problem for the structural equations which is corrected by the aerodynamic influence. The approximation of this computationally expensive interaction term, simulated by nonlinear high fidelity computational fluid dynamics, is formulated to allow both the blind search for aeroelastic instability and the update of lower order predictions with available better information. The approximation is based on a kriging interpolation of exact numerical samples covering the parameter space. The approach is presented for the Goland and MDO wing configurations and the open source fighter.

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