THREE WING, SIX-TILT PROPULSION UNIT, VTOL AIRCRAFT

• US 20110315809A1
• Filed: 09/12/2011
• Published: 12/29/2011
• Est. Priority Date: 10/09/2009
• Status: Active Grant

• Current Assignee: Oliver VTOL LLC
• Original Assignee: Oliver VTOL LLC
• Inventors: OLIVER, Richard David
• Granted Patent: US 8,800,912 B2
• Time in Patent Office: Days
• US Class Current: 244/12.4
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 29/0075 the motors being tiltable relative to the fuselage
• CPC Class Codes: B64C 39/08 having multiple wings
• CPC Class Codes: B64D 27/06 within, or attached to, wings
• CPC Class Codes: B64D 27/12 within, or attached to, wings
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A vertical takeoff and landing aircraft having at least three wings and at least six propulsion units, each of which are located radially from two adjacent propulsion units, by equal or substantially equal angles. The at least six propulsion units together being located symmetrically, or at substantially symmetric positions, about the approximate center of gravity of the aircraft, when viewed from above. A vertical stabilizer may or may not be employed. If no vertical stabilizer is employed, yaw control during horizontal flight may be achieved through differential thrust using the at least six propulsion units. Yaw control during vertical flight may be provided by a plurality of yaw control panels. Absent yaw control panels, yaw control during vertical flight may be provided using differential propulsion unit tilt angles.

Claims

1. A vertical takeoff and landing aircraft comprising:

a fuselage;

three wings fixed to the fuselage, including a front wing, a middle wing and a rear wing; and

six rotatable propulsion units, wherein first and second propulsion units are fixed to the front wing, third and fourth propulsion units are fixed to the middle wing and fifth and sixth propulsion units are fixed to the rear wing, and wherein each of the six propulsion units is located radially from each of two adjacent propulsion units by equal or substantially equal angles.

2. The vertical takeoff and landing aircraft of claim 1, wherein the six propulsion units are symmetrically positioned, or at substantially symmetric positions, about the approximate center of gravity of the aircraft.

3. The vertical takeoff and landing aircraft of claim 1, wherein each of the rotatable propulsion units are rotatable to first orientation during forward flight and to a second orientation during vertical flight.

4. The vertical takeoff and landing aircraft of claim 3, wherein the first and second propulsion units are fixed to a first and second outboard end of the front wing, respectively;

the third and fourth propulsion units are fixed to a first and second outboard end of the middle wing, respectively; and

the fifth and sixth propulsion units are fixed to a first and second end of the rear wing, respectively.

5. The vertical takeoff and landing aircraft of claim 4 further comprising:

a plurality of yaw control panels.

6. The vertical takeoff and landing aircraft of claim 5, wherein the plurality of yaw control panels comprises a first, second, third and fourth yaw control panel located outboard of, fixed to and rotatable with the first, second, fifth and sixth propulsion unit, respectively.

7. The vertical takeoff and landing aircraft of claim 4 further comprising:

differential propulsion unit tilt angle yaw control during vertical flight.

8. The vertical takeoff and landing aircraft of claim 1, wherein the front, middle and rear wings are vertically displaced relative to each other.

9. The vertical takeoff and landing aircraft of claim 8, wherein the middle wing is vertically displaced higher than the front wing, and the rear wing is vertically displaced higher than the middle wing.

10. The vertical takeoff and landing aircraft of claim 9, wherein the front wing exhibits a negative dihedral, the middle wing exhibits a neutral dihedral and the rear wing exhibits a positive dihedral.

11. The vertical takeoff and landing aircraft of claim 1 further comprising:

differential thrust yaw control during horizontal flight.

12. The vertical takeoff and landing aircraft of claim 1 further comprising:

a vertical stabilizer fixed to the fuselage.

13. A vertical takeoff and landing aircraft comprising:

a fuselage;

three wings fixed to the fuselage, including a front wing, a middle wing and a rear wing; and

six propulsion units, wherein first and second propulsion units are rotatably fixed to the front wing, third and fourth propulsion units are rotatably fixed to the middle wing and fifth and sixth propulsion units are rotatably fixed to the rear wing, wherein each of the six propulsion units is located radially from each of two adjacent propulsion units by equal or substantially equal angles, and wherein each of the six propulsion units are rotatable to a first orientation during horizontal flight and rotatable to a second orientation during vertical flight.

14. The vertical takeoff and landing aircraft of claim 13, wherein the six propulsion units are symmetrically positioned, or at substantially symmetric positions, about the approximate center of gravity of the aircraft.

15. The vertical takeoff and landing aircraft of claim 13, wherein the first and second propulsion units are rotatably fixed to a first and second outboard end of the front wing, respectively;

the third and fourth propulsion units are rotatably fixed to a first and second outboard end of the middle wing, respectively; and

the fifth and sixth propulsion units are rotatably fixed to a first and second end of the rear wing, respectively.

16. The vertical takeoff and landing aircraft of claim 15 further comprising:

a plurality of yaw control panels.

17. The vertical takeoff and landing aircraft of claim 16, wherein the plurality of yaw control panels comprises:

a first yaw control panel and a second yaw control panel fixed to and rotatable with the first propulsion unit and the second propulsion unit, respectively; and

a third yaw control panel and a fourth yaw control panel fixed to and rotatable with the fifth propulsion unit and the sixth propulsion unit, respectively.

18. The vertical takeoff and landing aircraft of claim 15 further comprising:

differential propulsion unit tilt angle yaw control during vertical flight.

19. The vertical takeoff and landing aircraft of claim 13, wherein the front, middle and rear wings are vertically displaced relative to each other.

20. The vertical takeoff and landing aircraft of claim 19, wherein the middle wing is vertically displaced higher than the front wing, and the rear wing is vertically displaced higher than the middle wing.

21. The vertical takeoff and landing aircraft of claim 19, wherein the front wing exhibits a negative dihedral, the middle wing exhibits a neutral dihedral and the rear wing exhibits a positive dihedral.

22. The vertical takeoff and landing aircraft of claim 13 further comprising:

differential thrust yaw control during horizontal flight.

23. The vertical takeoff and landing aircraft of claim 13 further comprising:

a vertical stabilizer fixed to the fuselage.