Multi wing aircraft
OwnerStephen H. Funckinventor
Life of this patent
Estimating the term…
Abstract
A multi-wing, airfoil fuselage aircraft that is capable of flying in a ground-effect mode includes a main airfoil fuselage wing, a fin that extends vertically from this wing, a pivot mount that is affixed to the fin, an auxiliary wing that connects to the pivot mount so as to allow its angle of attack to be adjusted and changed during different flight conditions, a main landing gear, an adjustable-length, stabilizing landing gear, assorted control surfaces that are movably affixed to the auxiliary wing and fin, and a ground-effect control system that is adapted to control the operation and movement of these control surfaces when the aircraft is flying in a ground-effect mode of flight.
Claims20
A multi-wing, airfoil fuselage aircraft capable of flying in a ground-effect mode, said aircraft comprising:
- a main, airfoil fuselage wing having a centerline and top, bottom, front, rear and wing tip surfaces and a specified span length between said wing tips and a specified chord length between said front and rear surfaces, and said top and bottom surfaces configured so as to yield a camber for said main airfoil fuselage wing, that is selected from the group consisting of symmetrical and reverse chamber,
- a fin that connects and extends vertically from said main airfoil fuselage wing top surface,
- a pivot mounting means affixed to said fin,
- an angle-of-attack adjustable, auxiliary wing that connects to said pivot mounting means, wherein said pivot mounting means adapted to allow the entire auxiliary wing to be moved so as to adjust and change the angle-of-attack of said auxiliary wing with respect to said main airfoil fuselage wing centerline,
- a main landing gear that connects to the bottom surface of said main airfoil fuselage wing,
- a stabilizing landing gear having telescoping pieces that are configured to connect to the bottom surface of said main airfoil fuselage wing and allow said stabilizing landing gear to extend to accommodate the initial touch-down of said aircraft and to raise said main, airfoil fuselage wing into a desired angle of attack for take-off,
- a plurality of control surfaces movably affixed to said auxiliary wing and fin, said control surfaces adapted to control the stability and maneuverability of said aircraft, and
- a ground-effect control system that is adapted to control the operation and movement of said control surfaces when said aircraft is flying at relatively low speeds in a ground-effect mode for extended periods of time.
A multi-wing aircraft capable of flying in a ground-effect mode, said aircraft comprising:
- a main wing having a centerline and top, bottom, front, rear and wing tip surfaces and a specified span length between said wing tips and a specified chord length between said front and rear surfaces, and said top and bottom surfaces configured so as to yield a camber for said main wing, that is selected from the group consisting of symmetrical and reverse camber,
- a fin that connects and extends vertically from said main wing top surface,
- a pivot mounting means affixed to said fin,
- an angle-of-attack adjustable, auxiliary wing that connects to said pivot mounting means, wherein said pivot mounting means adapted to allow the entire auxiliary wing to be moved so as to adjust and change the angle-of-attack of said auxiliary wing with respect to said main airfoil fuselage wing centerline,
- a main landing gear that connects to the bottom surface of said main wing,
- a stabilizing landing gear having telescoping pieces that are configured to connect to the bottom surface of said main wing and allow said stabilizing landing gear to extend to accommodate the initial touch-down of said aircraft and to raise said main wing into a desired angle of attack for take-off,
- a plurality of control surfaces movably affixed to said auxiliary wing and fin, said control surfaces adapted to control the stability and maneuverability of said aircraft, and
- a ground-effect control system that is adapted to control the operation and movement of said control surfaces when said aircraft is flying at a relatively low speeds in a ground-effect mode for extended periods of time.
Dependencies are inferred from the claim text.