| 摘要 |
A rotor system for a rotorcraft having at least one rotor blade pair operably associated with a differential pitch assembly operably for controlling a pitch angle of an upper rotor blade and the lower rotor blade in the rotor blade pair. Operation of the differential pitch assembly changes the pitch of the upper rotor blade more severely than the pitch of the lower rotor blade. As such, the rotor system is configured to provide optimum pitch of the upper and lower rotor blades during a helicopter mode and an airplane mode.
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