Vertical/short takeoff or landing aircraft having a rotatable wi

Aeronautics and astronautics – Aircraft sustentation – Sustaining airfoils

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244 45R, 244217, 244 125, 244 60, B64C 2700

Patent

active

050980343

ABSTRACT:
An improved vertical/short takeoff or landing aircraft (10). The aircraft has a canard wing (14), attached to the forward section of the aircraft body, that has an engine (26) on each side. Each engine drives a pusher propeller (42). Located aft of the canard wing (14) is a primary wing (16) that includes a number of control surfaces and that is rotatably attached to the fuselage (12). The primary wing (16) is rotated downwardly about its chordwise axis when the aircraft takes off or lands vertically. When short takeoffs and landings are required the wing is partially rotated and during conventional flight, the wing is rotated to a position that is approximately parallel to the longitudinal axis of the aircraft (12). The aircraft also has a tail control group that consists of a horizontal stabilizer (22) and elevator (34) to where on each side is attached a vertical stabilizer (22) and rudder (36).

REFERENCES:
patent: D203283 (1965-12-01), Woods
patent: 1890059 (1932-12-01), Lake
patent: 3506220 (1970-04-01), Sbrilli
patent: 3540681 (1970-11-01), Orazi
patent: 3954231 (1976-05-01), Fraser
patent: 3995794 (1976-12-01), Lanier
patent: 4238094 (1980-12-01), McGann
patent: 4553721 (1985-11-01), Jorgensen
patent: 4598888 (1986-07-01), Beteille
patent: 4605185 (1986-08-01), Reyes

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