Compound helicopter with no tail rotor

Details Compound helicopter with no tail rotor Compound helicopter with no tail rotor

1990-01-17

1991-11-26

Barefoot, Galen

Aeronautics and astronautics

Aircraft, heavier-than-air

Airplane and helicopter sustained

244 1719, B64C 2722

Patent

active

050676687

ABSTRACT:
This helicopter invention uniquely has no anti-torque tail rotor. The tail propeller is used only for forward thrust during the airplane mode of flight and during the transition from vertical helicopter flight to forward airplane mode of flight, when the helicopter rotor may be feathered in a no-lift attitude. The anti-torque balancing forces during the hovering mode are developed by the differentially controlled aileron forces when the wings are aligned vertically with the vertically downward airflow from the helicopter rotor. There is also a vertically moveable horizontal airfoil on the tail cone, or tail boom, with controllable means which can provide anti-torque reaction forces during the helicopter hovering mode from the lifting rotor down flow air. An angular moveable tail fin assembly and rudder are provided to improve transition from VTOL hovering flight to horizontal airplane flight. Means are provided to electronically schedule transition from the VTOL to horizontal cruise flight sensed by the wing attitude which can control the angular attitude of the fin and rudder in a completely computerized automatic transition to and from VTOL and airplane flight mode.

REFERENCES:
patent: 2338935 (1944-01-01), Hafner
patent: 2680579 (1954-06-01), Hohenemser
patent: 3055618 (1962-09-01), Brislawn, Jr.
patent: 3075727 (1963-01-01), Ellis, III et al.
patent: 3563496 (1971-02-01), Zuck
patent: 4462559 (1984-07-01), Garza
patent: 4730795 (1988-03-01), David

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