This research explores the impact of kinematic structural nonlinearities on the
dynamics of a highly deformable cantilevered wing. Two different theoretical formulations
are presented and analysed for nonlinear behavior. The first formulation, which
is more conventional, assumes zero equilibrias and structural nonlinearities occur as
terms 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 is
made. Kinematic nonlinearities due to curvature and inertia were retained in their
exact form. Thus, the former becomes a special case of the latter. This nonlinear formulation
permits the analysis of dynamics about nonzero trims. Nonzero trim states
are computed as a system parameter is varied using a continuation software tool. The
stability characteristics of these trim states are also ascertained. Various bifurcation
points of the system are determined. Limit-cycle oscillations are also investigated for
and are characterized in terms of amplitude of vibration. The research in particular
examines the impact of in-plane degree of freedom on the stability of nonzero trim
states. The effect of variation of system parameters such as stiffness ratio, aspect
ratio and root angle of attack is also studied. The method of direct eigenanalysis of
nonzero equilibria is novel and new for an aeroelastic system
