Abstract
ABSTRACT A mixed variational approach is used to investigate the coupled flap-lag-torsional aeroelastic stability of a nonuniform helicopter blade. This approach is particularly suited to treating rotating blades with sharp variations or discontinuous changes in their properties or cross-sectional dimensions. Numerical results by this approach are presented in hovering conditions, for both uniform and nonuniform blades with low torsional stiffness, and compared with the results by the usual Rayleigh-Ritz method. It is shown that the present approach has good convergence properties for both static equilibrium position and critical collective pitch angles.
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