Electric Vertical Takeoff and Landing Aircraft

• US 20190322368A1
• Filed: 04/24/2019
• Published: 10/24/2019
• Est. Priority Date: 04/24/2018
• Status: Active Grant

• Current Assignee: Thomas W. Melcher
• Original Assignee: Thomas W. Melcher
• Inventors: Melcher, Thomas W.
• Granted Patent: US 11,548,637 B2
• Time in Patent Office: Days
• CPC Class Codes: B64C 29/02 having its flight directional axis vertical when grounded
• CPC Class Codes: B64C 3/38 Adjustment of complete wings or parts thereof
• CPC Class Codes: B64C 3/385 Variable incidence wings
• CPC Class Codes: B64C 37/00 Convertible aircraft
• CPC Class Codes: B64C 9/02 Mounting or supporting thereof
• CPC Class Codes: B64D 1/22 Taking-up articles from earth's surface
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: B64F 1/362 Installations for supplying conditioned air to parked aircraft
• CPC Class Codes: B64G 1/002 Launch systems
• CPC Class Codes: B64G 1/401 Liquid propellant rocket engines Ion or plasma engines B64G1/413; Arcjets and other resistojets B64G1/415
• CPC Class Codes: B64G 1/402 Propellant tanks; Feeding propellants
• CPC Class Codes: B64G 5/00 Ground equipment for vehicles, e.g. starting towers, fuelling arrangements B64G3/00 takes precedence
• CPC Class Codes: B64U 10/20 Vertical take-off and landing [VTOL] aircraft flying platforms B64U10/13; helicopters B64U10/17
• CPC Class Codes: B64U 2101/60 for transporting passengers; for transporting goods other than weapons
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: B64U 30/26 Ducted or shrouded rotors
• CPC Class Codes: B64U 50/12 using turbine engines, e.g. turbojets or turbofans
• CPC Class Codes: B64U 50/15 using combustion exhausts other than turbojets or turbofans, e.g. using rockets, ramjets, scramjets or pulse-reactors
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 80/70 in containers B64U80/60 takes precedence
• CPC Class Codes: Y02T 50/10 : Drag reduction

Abstract

An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The propulsion assembly is coupled to the boom by a rotating joint. A second wing is optionally coupled to the rotating joint. The first wing is coupled to the boom by a rotating joint. The first wing is coupled to the rotating joint by a hinge. A vehicle with roll, pitch, and yaw maneuverability able to mirror the aircraft movements may be coupled to the second end of the boom. The vehicle body may be picked up with a vehicle chassis disconnected from the vehicle body. The boom houses an energy source to power the propulsion assembly. A rudder is coupled to the second end of the boom. A paddle is disposed between the propulsion assembly and the boom.

Claims

1. An aircraft, comprising:

a boom;

a propulsion assembly coupled to a first end of the boom; and

a first wing coupled to a second end of the boom.

2. The aircraft of claim 1, wherein the propulsion assembly is coupled to the boom by a rotating joint.

3. The aircraft of claim 2, further including a second wing coupled to the rotating joint.

4. The aircraft of claim 1, wherein the first wing is coupled to the boom by a rotating joint.

5. The aircraft of claim 4, wherein the first wing is coupled to the rotating joint by a hinge.

6. The aircraft of claim 5, further including a wing tip retention mechanism disposed on the boom and configured to facilitate warping of the first wing.

7. The aircraft of claim 1, further including a vehicle body coupled to the second end of the boom.

8. The aircraft of claim 1, wherein the boom houses an energy source to power the propulsion assembly.

9. The aircraft of claim 1, further including a rudder coupled to the second end of the boom.

10. The aircraft of claim 1, wherein the propulsion assembly comprises a rocket dome with an integral air breathing engine capable of propelling the aircraft beyond Earth'"'"'s atmosphere.

11. A method of transportation, comprising:

providing a vertical takeoff and landing (VTOL) aircraft including,

a boom

a propulsion assembly coupled to a first end of the boom,

a first wing coupled to a second end of the boom, and

a payload connector coupled to the second end of the boom; and

providing a ground vehicle comprising a vehicle body and a dock disposed on the vehicle body; and

picking up the vehicle body with the VTOL aircraft by attaching the payload connector to the dock.

12. The method of claim 11, further including picking up the ground vehicle while the ground vehicle is driving.

13. The method of claim 11, further including picking up the vehicle body with the VTOL while a chassis of the ground vehicle is disconnected from the vehicle body.

14. The method of claim 11, further including parking the VTOL aircraft in a storage silo, wherein the VTOL aircraft is recharged or refueled.

15. The method of claim 11, further including:

flying the VTOL aircraft vertically to pick up the vehicle body; and

transitioning to horizontal flight after picking up the vehicle body.

16. The method of claim 15, wherein transitioning to horizontal flight includes rotating the propulsion assembly relative to the boom.

17. The method of claim 15, further including:

orienting the first wing parallel to the boom while flying the VTOL aircraft vertically; and

orienting the first wing perpendicular to the boom during horizontal flight.

18. The method of claim 11, further including picking up the vehicle body with the VTOL aircraft and a second VTOL aircraft in tandem.

19. The method of claim 11, wherein the ground vehicle includes an active long-travel leaning suspension.

20. The method of claim 19, further including overfilling a liquid side of a shock actuator of the active long-travel leaning suspension to impart a desired control attribute.

21. The method of claim 19, further including using the active long-travel leaning suspension to actively position the vehicle to protect a vehicle occupant and a surrounding pedestrian.

22. The method of claim 19, further including using a precessional wheel torque of the ground vehicle to control an attitude of the ground vehicle during flight, wherein the ground vehicle includes all-wheel steering and all-wheel drive to individually control the precessional wheel torque of each wheel.

23. The method of claim 11, further including a second wing coupled to the first end of the boom, wherein the second wing is mounted to the boom in a reverse orientation of the first wing.