Abstract
A strain-based geometrically nonlinear finite element beam formulation for structural dynamic and aeroelastic analysis of slender beams and wings has been successfully applied to study the coupled nonlinear aeroelasticity and flight dynamics of different, very flexible aircraft. To improve the ability to use such aeroelastic framework in control design, a modal-based approach is developed in this paper to solve the strain-based nonlinear beam equations with a reduced number of degrees of freedom. The modal approach is applied to study geometrically nonlinear static and transient problems of constrained and free slender beams, subject to external structural or aerodynamic excitations. Accuracy and performance of the new formulation are compared with the direct nonlinear finite element procedure.
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