On the dynamic response of a hingeless helicopter rotor blade

The intense nature of the aerodynamic environment surrounding a helicopter can cause excessive deflection rotor blades. Therefore, proper prediction loading and blade are necessary for monitoring health. Compared to rigid blade, dynamics hingeless is particular interest its inherent flexing tendency strong coupling between different degrees-of-freedom motion. With small-angle assumption, deformed resembles straight shape with constant flapping angle. However, in reality, deforms variable angle dynamic twist. In this paper, coupled, steady-state response Bo 105 investigated at forward flight advance ratios without assumption. velocity distributions generalized torsional deformation introduced modify total twist deriving corresponding attack. solution resulting nonlinear equations obtained by formulating method lines flap-lag-torsion terms time-varying deflections other parameters. parameters from analysis differ significantly than that model validated comparing solutions finite element published results.