Helicopter low-speed yaw control

Details Helicopter low-speed yaw control Helicopter low-speed yaw control

1991-11-07

1993-05-11

Basinger, Sherman

Aeronautics and astronautics

Aircraft, heavier-than-air

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

244 1711, 244 75R, B64C 2700

Patent

active

052094308

ABSTRACT:
A system for improving yaw control at low speeds consists of one strake placed on the upper portion of the fuselage facing the retreating rotor blade and another strake placed on the lower portion of the fuselage facing the advancing rotor blade. These strakes spoil the airflow on the helicopter tail boom during hover, low speed flight and right or left sidewards flight so that less side thrust is required from the tail rotor.

REFERENCES:
patent: 2383038 (1945-08-01), Bossi
patent: 3059877 (1962-10-01), Lee
patent: 3807662 (1974-04-01), Velazquez
patent: 4200252 (1980-04-01), Logan et al.
patent: 4227665 (1980-10-01), Carlson et al.
patent: 4708305 (1987-11-01), Kelley et al.
patent: 4786009 (1988-11-01), Rao et al.
patent: 4809930 (1989-03-01), Ballero
patent: 4948068 (1990-08-01), Van Horn

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