| 摘要 |
<p>The method involves elaborating a main control of a pitch of a rear rotor blade by a pitch control unit (4b) activated by a pilot. A yaw uncoupling control is elaborated by an attitude control system of a rotary wing. A variable control bias (17) is elaborated according to a flying speed of a rotocraft, the main control and/or a position of the unit. The bias is added with the uncoupling control and main control to control the pitch. An independent claim is also included for a system of controlling a yaw of a rotocraft.</p> |
