Optimized method of controlling yaw for rotary-wing...

Details Optimized method of controlling yaw for rotary-wing... Optimized method of controlling yaw for rotary-wing...

2005-06-15

2008-09-23

Swiatek, Rob (Department: 3643)

Aeronautics and astronautics

Aircraft, heavier-than-air

Helicopter or auto-rotating wing sustained, i.e., gyroplanes

Reexamination Certificate

active

07427046

ABSTRACT:
A method of the invention for controlling the pitch of the blades of a tail rotor of a rotary-wing aircraft includes the following operations:a) generating a main control for the pitch of the blades of the tail rotor as a function of a control member for controlling the pitch of the blades of the tail rotor that is actuated by a pilot of the aircraft;b) generating a collective pitch and yaw decoupling control as a function of the collective pitch of the rotary wing;c) generating a bias control that is variable as a function of the flying speed of the aircraft and of the position of the control member; andd) adding the bias control to the decoupling control and to the main control in order to obtain an overall control, thereby controlling the pitch of the blades of the tail rotor.

REFERENCES:
patent: 4493465 (1985-01-01), Howlett et al.
patent: 5188511 (1993-02-01), Ebert
patent: 6142413 (2000-11-01), Dequin et al.
patent: 6290171 (2001-09-01), Dequin et al.

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