Tilt wing VTOL aircraft

Details Tilt wing VTOL aircraft Tilt wing VTOL aircraft

1993-05-28

1995-04-11

Huppert, Michael S.

Aeronautics and astronautics

Aircraft, heavier-than-air

Airplane and helicopter sustained

244 56, 244 124, 244 66, B64C 2728

Patent

active

054051053

ABSTRACT:
A tilt wing VTOL aircraft has a fuselage with sides and an upper surface, an upper wing having a leading edge, a trailing edge, a chord, a lower surface and an upper surface. The wing is pivotally mounted on the fuselage for rotation from a cruise flight position in which the upper surface of the wing is flush with the upper surface of the fuselage to a hover position in which the wing is perpendicular to the upper surface of the fuselage. Aircraft engines are mounted on the wing. The aircraft has a pair of flaps at the trailing edge of the wing, each located between the fuselage and an engine and each spaced the same distance from the fuselage and each of the engines. The flaps are mounted for selective movement from colinearity with the chord of the wing to a first angle of about +30.degree. with the chord and about 30.degree. with the upper surface of the wing and to a second angle of about -30.degree. with the chord and about 30.degree. with the lower surface of the wing. When the flaps are between a small angle with the chord and the first angle with the chord, the aircraft moves in a forward horizontal direction while in hover and when the flaps are between a small angle with the chord and at the second angle with the chord, the aircraft moves in a reverse horizontal direction while in hover. The horizontal motion forces are produced by the propeller slipstream acting on the wing flaps and because the flap aerodynmnic center of gravity is at essentially the same height as the aircraft center of gravity.

REFERENCES:
patent: 3107882 (1963-10-01), Matteson et al.
patent: 3136499 (1964-06-01), Kessler
patent: 3179352 (1965-04-01), Nelson
patent: 3197157 (1965-07-01), King
patent: 3666209 (1972-05-01), Taylor
patent: 5096140 (1992-03-01), Dornier, Jr. et al.

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