VTOL aircraft using rotors to simulate rigid wing aero dynamics
A vertical take-off and landing aircraft which uses fixed rotors for both VTOL and forward flight operations. The rotors form a synthetic wing and are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the synthetic wing. The synthetic wing may also have narrow front and rear airfoils which may provide structural support as well as providing lift during forward flight. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight.
1. An aerial vehicle adapted for vertical takeoff and horizontal flight using rotors to simulate traditional wing aerodynamics, said aerial vehicle comprising:
a main vehicle body;
a right side wing assembly, said right side wing assembly comprising:
a plurality of right side wing rotors in a forward swept configuration along a single forward swept linear or curvilinear first span direction, wherein the spin axis of each of said right side wing rotors is tilted forward;
a forward swept right side leading edge wing, said right side leading edge wing having a first end at said main vehicle body and moving outboard along the first span direction directly forward of the plurality of right side wing rotors;
a forward swept right side trailing edge wing, said right side trailing edge wing having a first end at said main vehicle body and moving outboard along the first span direction directly rearward of the plurality of right side wing rotors;
a plurality of right side span supports, said right side span supports coupled to said forward swept right side leading edge wing on a first end, and coupled to said forward swept right side trailing edge wing on a second end, wherein each of said plurality of right side wing rotors are mounted on one of said plurality of right side span supports; and
a right side wing tip section, said right side wing tip section joining said right side leading edge wing to said right side trailing edge wing outboard of said plurality of said right side wing rotors; and
a left side wing assembly, said left side simulated wing comprising:
a plurality of left side wing rotors in a forward swept configuration along a single forward swept linear or curvilinear second span direction, wherein the spin axis of each of said left side wing rotors is tilted forward:
a forward swept left side leading edge wing, said left side leading edge wing having a first end at said main vehicle body and moving outboard along the first span direction directly forward of the plurality of left side wing rotors;
a forward swept left side trailing edge wing, said left side trailing edge wing having a first end at said main vehicle body and moving outboard along the second span direction directly rearward of the plurality of left side wing rotors;
a plurality of left side span supports, said left side span supports coupled to said forward swept left side leading edge wing on a first end, and coupled to said forward swept left side trailing edge wing on a second end, wherein each of said plurality of left side wing rotors are mounted on one of said plurality of left side span supports; and
a left side wing tip section, said left side wing tip section joining said left side leading edge wing to said left side trailing edge wing outboard of said plurality of said left side wing rotors.
2. The aerial vehicle of claim 1 wherein the spin axis of said right side wing rotors is tilted forward at an angle in the range of 8-12 degrees, and wherein the spin axis of said left side wing rotors is tilted forward at an angle in the range of 8-12 degrees.
3. The aerial vehicle of claim 2 wherein the tilt angle of said right side wing rotors and the tilt angle of said left side wing rotors are not adjustable.
4. The aerial vehicle of claim 3 wherein said aerial vehicle does not have controllable control surfaces.
5. The aerial vehicle of claim 4 wherein a most inboard rotor of said plurality of right side wing rotors in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle and wherein a most outboard rotor of said plurality of right side wing rotors in a forward swept configuration is forward of the longitudinal center of said aerial vehicle.
6. The aerial vehicle of claim 3 wherein a most inboard rotor of said plurality of right side wing rotors in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle and wherein a most outboard rotor of said plurality of right side wing rotors in a forward swept configuration is forward of the longitudinal center of said aerial vehicle.
7. The aerial vehicle of claim 2 wherein said aerial vehicle does not have controllable control surfaces.
8. The aerial vehicle of claim 2 wherein each wing rotor has a plurality of blades and an electric motor, said electric motor mounted central to the spin axis of the rotor, and wherein an inboard end of said blade relative to the spin axis is outboard of the motor.
9. The aerial vehicle of claim 2 wherein a most inboard rotor of said plurality of right side wing rotors in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle and wherein a most outboard rotor of said plurality of right side wing rotors in a forward swept configuration is forward of the longitudinal center of said aerial vehicle.
10. The aerial vehicle of claim 1 wherein the spin axis of said right side wing rotors is tilted forward at an angle in the range of 5-15 degrees, and wherein the spin axis of said left side wing rotors is tilted forward at an angle in the range of 5-15 degrees.
11. The aerial vehicle of claim 10 wherein the tilt angle of said right side wing rotors and the tilt angle of said left side wing rotors are not adjustable.
12. The aerial vehicle of claim 11 wherein said aerial vehicle does not have controllable control surfaces.
13. The aerial vehicle of claim 12 wherein a most inboard rotor of said plurality of right side wing rotors in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle and wherein a most outboard rotor of said plurality of right side wing rotors in a forward swept configuration is forward of the longitudinal center of said aerial vehicle.
14. The aerial vehicle of claim 11 wherein a most inboard rotor of said plurality of right side wing rotors in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle and wherein a most outboard rotor of said plurality of right side wing rotors in a forward swept configuration is forward of the longitudinal center of said aerial vehicle.
15. The aerial vehicle of claim 10 wherein said aerial vehicle does not have controllable control surfaces.
16. The aerial vehicle of claim 10 wherein a most inboard rotor of said plurality of right side wing rotors in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle and wherein a most outboard rotor of said plurality of right side wing rotors in a forward swept configuration is forward of the longitudinal center of said aerial vehicle.
17. The aerial vehicle of claim 1 wherein the spin axis of said right side wing rotors is tilted forward at an angle in the range of 5-20 degrees, and wherein the spin axis of said left side wing rotors is tilted forward at an angle in the range of 5-20 degrees.
18. The aerial vehicle of claim 17 wherein a most inboard rotor of said plurality of right side wing rotors in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle and wherein a most outboard rotor of said plurality of right side wing rotors in a forward swept configuration is forward of the longitudinal center of said aerial vehicle.
19. The aerial vehicle of claim 1 wherein each wing rotor has a plurality of blades and an electric motor, said electric motor mounted central to the spin axis of the rotor, and wherein an inboard end of said blade relative to the spin axis is outboard of the motor.
20. The aerial vehicle of claim 1 wherein a most inboard rotor of said plurality of right side wing rotors in a forward swept configuration is rearward of the longitudinal center of said aerial vehicle and wherein a most outboard rotor of said plurality of right side wing rotors in a forward swept configuration is forward of the longitudinal center of said aerial vehicle.