Abstract
A comprehensive analytical formulation has been developed to predict the vibratory hub loads of a helicopter rotor system in forward flight. The analysis is used to calculate the optimal higher harmonic control inputs and associated actuator power required to minimize these hub loads. The formulation is based on a finite element method in space and time. A nonlinear time domain unsteady aerodynamic model is used to obtain the airloads, and the rotor induced inflow is calculated using a free wake model. Predicted vibratory hub loads are correlated with experimental data obtained from a scaled model rotor. Results of a parametric study on a hingeless rotor show that blade flap, lag and torsion vibration characteristics, offset of blade center of mass from elastic axis, offset of elastic axis from quarter-chord, and rotor thrust all have large effects on the HHC actuator power requirement.
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