| 摘要 |
<p>The method involves controlling pitch of a set of blades (12) of a tail rotor (10) of an aircraft (1) using a control unit (31) in an anti-torque mode of operation, and controlling a salient angle (theta) of a rotation axis (AX) using the control unit. The pitch of set of blades of the tail rotor of the aircraft is controlled using another control unit (32) in a propulsion mode of operation. The tail rotor is swiveled to move reversibly from the anti-torque mode of operation to the propulsion mode of operation. An independent claim is also included for an aircraft comprising an airframe carrying a rotary wing including a set of blades.</p> |
