Aircraft having independently variable incidence channel wings with independently variable incidence channel canards

Abstract

An aircraft includes a fuselage and a pair of channel wings which may vary incidence with respect to the fuselage and a pair of channel canards which can also vary incidence with respect to the fuselage and that can move independently of each other for the purpose of vertical takeoff and landing as well as forward and reverse flight. The wings may have multiple channels and may be powered by single propeller or contra-rotating propellers. The thrust to the propellers may be provided with an internal combustion engine or electric motors or a turbo prop or hybrid system. The channel wing allows the fuselage to maintain a level pitch with respect to the horizon. The aircraft will also have increased maneuverability in hover because it can independently vary the incidence of the wings and canards and be able to tightly turn about a point.

Claims

1. An aircraft comprising: a fuselage; a first channel wing; a second channel wing; a first channel canard; and a second channel canard; wherein the first and second channel wings are coupled to the fuselage and have at least one propeller each, and where the first and second channel wings have controlled independently variable incidences relative to the fuselage; wherein the first and second channel canards are coupled to the fuselage and have at least one propeller each, and where the first and second channel wings have controlled independently variable incidences relative to the fuselage; wherein at least one of a propeller of the channel wings and a propeller of the channel canards can become ducted propellers by enclosing the at least one of the propeller of the channel wings and the propeller of the channel canards with a retractable mechanism for takeoff and landing.

2. The aircraft of claim 1, wherein the independently variable incidence channel wings and the independently variable incidence channel canards are configured to provide control for the aircraft, eliminating the need for standard aircraft control surfaces such as ailerons and rudders.

3. The aircraft of claim 1, configured to supply thrust via either a single propeller, multiple propellers or contra-rotating propellers attached to the first and second channel wings.

4. The aircraft of claim 1, configured to supply thrust via either a single propeller, multiple propellers or contra-rotating propellers attached to the first and second channel canards.

5. The aircraft of claim 1, wherein power for the propellers of the first and second channel wings, and power for the first and second channel canards is providable by at least one of: an internal combustion engine, an electric motor, a turbo prop or a hybrid system.

6. The aircraft of claim 1, wherein power to, and thrust of the propellers of the channel wings and channel canards are variable.

7. The aircraft of claim 1, wherein at least one of the angles of incidence of one or more channel wings and the angle of incidence of one or more channel canards is independently variable.

8. The aircraft of claim 1, wherein the variable incidence of the first and second channel wings, and of the first and second channel canards allows for a smooth transition from vertical takeoff to forward flight.

9. The aircraft of claim 1, wherein the variable incidence of the first and second channel wings, and of the first and second channel canards allows for a smooth transition from forward flight to vertical landing.

10. The aircraft of claim 1, wherein the variable incidence of the first and second channel wings, and of the first and second channel canards allows for hovering and slow flight.

11. The aircraft of claim 1, wherein the variable incidence of the first and second channel wings, and of the first and second channel canards allows for reverse flight.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 is a diagram illustrating the aircraft at rest.

(2) FIG. 2 is a diagram illustrating the aircraft in the vertical takeoff and landing configuration of the present invention.

(3) FIG. 3A is an isometric diagram illustration of the aircraft in the cruise condition of the present invention.

(4) FIG. 3B is side diagram illustration of the aircraft in the cruise condition of the present invention.

(5) FIG. 4 is a diagram of the aircraft illustrating the aircraft in a hover showing the canards and wings in a position for a tight turn.

(6) FIG. 5 is a diagram illustrating the aircraft flying in reverse flight.

(7) FIG. 6 is a close up of a channel of the aircraft of the present invention and showing a possible contra-rotating configuration with high thrust propellers.

DETAILED DESCRIPTION OF THE INVENTION

(8) FIG. 1 is a diagram illustrating the aircraft at rest. In this diagram the aircraft's wing 110 is made up of four channels 120, 130, 140 and 150. The aircraft's canard 160 is made of four channels 170, 180, 190 and 195.

(9) FIG. 2 is a diagram illustrating the aircraft in the vertical takeoff and landing configuration of the present invention. The aircraft of the present invention will be able to independently vary the incidence of the wing 210 as well as the angle of incidence of the canard 220 as required for takeoff, landing, and flight. During liftoff the channel wings and channel canards rotate such that the resultant of the thrust from the propellers and the lift from the wings and canards provide the lift required for vertical takeoff. A portion of the channel wing 230 and the channel canard 240 can become a ducted propeller, by enclosing the propeller(s) with a retractable mechanism, for takeoff and landing allowing for extra thrust, reduction of noise and protection of bystanders.

(10) Referring to FIGS. 3A and 3B, these illustrate the aircraft in the cruise condition. The wing 310 and canard 320 are rotated to a position required to maintain lift for forward flight. FIG. 4 is a diagram of the aircraft of the present invention illustrating the aircraft in a turning hover. This figure shows the right wing 410 and left wing 420 at independent angles of incidence for a hovering left turn. The figure shows the right canard 430 and left canard 440 also positioned independently to provide both lift and thrust for a tight hovering left turn.

(11) FIG. 5 is a diagram illustrating the aircraft flying in reverse flight. Referring to this figure, the wing 510 and 520 is at the angle of incidence for the greatest amount of lift, while the canards 530 and 540 are positioned to provide both lift and reverse thrust.

(12) FIG. 6 is a close up of a channel of the aircraft and shows a possible contra-rotating configuration with high thrust propellers 610 and 620. The contra-rotating propeller system allows for high thrust and lift from the channel. The internal combustion engine(s), electric motor(s), turbo prop or hybrid power system may reside in the nacelle 630.

(13) While the preferred embodiment and various alternative embodiments of the invention have been disclosed and described in detail herein, it may be apparent to those skilled in the art which various changes in form and detail may be made therein without departing from the spirit and scope thereof.