Theaimof this paper is the assessment of the capability of controllers based on the combined actuation of flaps and variable-stiffness\ndevices to alleviate helicopter main rotor vibratory hub loads. Trailing-edge flaps are positioned at the rotor blade tip region,whereas\nvariable-stiffness devices are located at the pitch link and at the blade root. Control laws are derived by an optimal control procedure\nbased on the best trade-off between control effectiveness and control effort, under the constraint of satisfaction of the equations\ngoverning rotor blade aeroelastic response.The numerical investigation concerns the analysis of performance and robustness of the\ncontrol techniques developed, through application to a four-bladed helicopter rotor in level flight. The identification of the most\nefficient control configuration is also attempted
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