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Optimised yaw control method for rotorcraft and corresonding system
Optimised yaw control method for rotorcraft and corresonding system
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机译:旋翼机及相应系统的优化偏航控制方法
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摘要
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.
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