This research explores the impact of kinematic structural nonlinearities on thedynamics of a highly deformable cantilevered wing. Two different theoretical formulationsare presented and analysed for nonlinear behavior. The first formulation, whichis more conventional, assumes zero equilibrias and structural nonlinearities occur asterms up to third order in the Taylor series expansion of structural nonlinearities.In the second approach, no prior assumption about equilibria states of the wing ismade. Kinematic nonlinearities due to curvature and inertia were retained in theirexact form. Thus, the former becomes a special case of the latter. This nonlinear formulationpermits the analysis of dynamics about nonzero trims. Nonzero trim statesare computed as a system parameter is varied using a continuation software tool. Thestability characteristics of these trim states are also ascertained. Various bifurcationpoints of the system are determined. Limit-cycle oscillations are also investigated forand are characterized in terms of amplitude of vibration. The research in particularexamines the impact of in-plane degree of freedom on the stability of nonzero trimstates. The effect of variation of system parameters such as stiffness ratio, aspectratio and root angle of attack is also studied. The method of direct eigenanalysis ofnonzero equilibria is novel and new for an aeroelastic system.
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