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This paper describes the development of a simplified nonlinear aeroelastic model for the Lockheed Martin X-56A Multi-Utility Demonstrator. Equivalent beam stiffnesses and inertias are calculated from a NASTRAN FEM model. Sectional aerodynamic coefficients are also calculated from wind-tunnel verified CFD data and additional X-FOIL results. The information is used within the University of Michigan Nonlinear Aeroelastic Simulation Toolbox (UM/NAST) to create a simplified coupled nonlinear aeroelastic/flight dynamics representation of the X-56A. With this model, various aeroelastic phenomena can be studied including trim, flutter onset, and elastic-rigid body coupling.

Nonlinear Aeroelastic Analysis of the X-56 Multi-Utility Aeroelastic Demonstrator