Abstract
An investigation is made of the nonlinear, large amplitude aeroelastic behavior of hingeless composite rotor blades during hover. The aeroelastic model is capable of dealing with large vibration amplitudes as well as large static deflections including transverse shear and warping deformation and is based on an Euler angle formulation of the basic large deflection equations together with a harmonic balance, finite difference, and NewtonRaphson technique. Nonlinear stall aerodynamics is included by use of the ONERA airforces model. Analysis of large amplitude limit cycles that evolve from linear flutter solutions is performed on a [0/90]35 graphite/ epoxy composite blade model. Numerical results indicate that the nonlinear stall is dominant at moderate amplitudes, but that nonlinear static-dynamic couplings in the structure, which bring a softening effect into the general aeroelastic behavior, could be equally important at large amplitudes.
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