# US 12,006,037 B2 · Vertical take off and landing closed wing aircraft

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- Number: US 12,006,037 B2
- Document ID: US12006037B2
- Status: Granted
- Kind: B2
- Application number: 18/310,198
- Filed: 2023-05-01
- Published: 2024-02-08
- Granted: 2024-06-11
- Earliest claimed: 2016-05-13
- Assignees: Textron Innovations Inc.
- Applicants: Textron Innovations Inc.
- Inventors: Carlos Alexander Fenny; Rohn Lee Olson; Andrew James Zahasky
- Web page: https://patentgrep.com/patent/US12006037B2

## CPC

- B64C 11/28: Collapsible or foldable blades
- B64C 1/068: {Fuselage sections}
- B64C 3/10: Shape of wings
- B64C 3/16: Frontal aspect
- B64C 27/08: with two or more rotors
- B64C 27/12: Rotor drives
- B64C 27/50: Blades foldable to facilitate stowage of aircraft
- B64C 29/0025: {the propellers being fixed relative to the fuselage}
- B64C 29/02: having its flight directional axis vertical when grounded
- B64C 39/024: {of the remote controlled vehicle type, i.e. RPV}
- B64C 39/06: having disc- or ring-shaped wings
- B64C 39/062: {having annular wings}
- B64D 27/24: using steam or spring force (jet aircraft B64D27/16)
- B64D 31/00: Power plant control systems; Arrangement of power plant control systems in aircraft
- B64D 31/18: for hybrid-electric power plants
- B64U 10/20: Vertical take-off and landing [VTOL] aircraft (flying platforms B64U10/13; helicopters B64U10/17)
- B64U 30/293: Foldable or collapsible rotors or rotor supports
- B64C 39/029: {Asymmetrical aircraft}
- B64C 2001/0045: {Fuselages characterised by special shapes}
- B64D 27/026: {comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine (Hybrid electric aircraft B64D27/33)}
- B64U 30/10: Wings
- B64U 50/11: using internal combustion piston engines
- B64U 50/12: using turbine engines, e.g. turbojets or turbofans
- B64U 50/19: using electrically powered motors
- B64U 60/50: with landing legs
- Y02T 50/10: Drag reduction
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- B64C: AEROPLANES; HELICOPTERS
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

An aircraft comprises a fuselage, first and second wing segments each having a leading edge and a trailing edge, a plurality of spokes coupling the fuselage to the first and second wing segments, one or more motors disposed within or attached to the plurality of spokes, and three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight. When the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical. When the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.

## Claims

### Claim 1

An aircraft capable of vertical takeoff and landing, stationary flight and forward flight, the aircraft comprising:
a fuselage;
a first wing segment having a leading edge and a trailing edge;
a second wing segment having a leading edge and a trailing edge;
a plurality of spokes coupling the fuselage to the first wing segment and the second wing segment;
one or more motors disposed within or attached to the plurality of spokes; and
three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the one or more motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight;
wherein, when the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical;
wherein, when the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.

### Claim 2 (depends on 1)

The aircraft of claim 1, wherein the fuselage is configured to carry a payload.

### Claim 3 (depends on 1)

The aircraft of claim 1, wherein the first and second wing segments, the fuselage and the plurality of spokes are not substantially reconfigured for transition between vertical takeoff and landing, stationary flight and forward flight.

### Claim 4 (depends on 1)

The aircraft of claim 1, wherein the fuselage comprises two or more modules.

### Claim 5 (depends on 1)

The aircraft of claim 1, wherein the aircraft is unmanned.

### Claim 6 (depends on 1)

The aircraft of claim 1, wherein the each of the three or more propellers comprise a variable speed constant pitch propeller.

### Claim 7 (depends on 1)

The aircraft of claim 1, wherein the plurality of spokes are operable to change a position of the first or second wing segments with respect to the fuselage or vice versa.

### Claim 8

An aircraft capable of vertical takeoff and landing, stationary flight and forward flight, the aircraft comprising:
a fuselage;
a plurality of spokes coupled to the fuselage;
a first wing segment coupled to at least two of the plurality of spokes and having a leading edge and a trailing edge;
a second wing segment coupled to at least two of the plurality of spokes and having a leading edge and a trailing edge;
one or more motors disposed within or attached to the plurality of spokes; and
a propeller proximate to a leading edge of each of the plurality of spokes, and operably connected to the one or more motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight;
wherein, when the aircraft is in vertical takeoff and landing and stationary flight, a longitudinal axis of the fuselage is approximately vertical;
wherein, when the aircraft is in forward flight, the longitudinal axis of the fuselage is approximately in the direction of the forward flight and the fuselage extends forward beyond the leading edges of the first wing segment and the second wing segment.

### Claim 9 (depends on 8)

The aircraft of claim 8, wherein the fuselage is configured to carry a payload.

### Claim 10 (depends on 8)

The aircraft of claim 8, wherein the first and second wing segments, the fuselage and the plurality of spokes are not substantially reconfigured for transition between vertical takeoff and landing, stationary flight and forward flight.

### Claim 11 (depends on 8)

The aircraft of claim 8, wherein the fuselage comprises two or more modules.

### Claim 12 (depends on 8)

The aircraft of claim 8, wherein the aircraft is unmanned.

### Claim 13 (depends on 8)

The aircraft of claim 8, wherein each propeller is a variable speed constant pitch propeller.

### Claim 14

An aircraft capable of vertical takeoff and landing, stationary flight and forward flight, the aircraft comprising:
a fuselage;
six spokes coupled to the fuselage;
a first wing segment coupled to at least two of the spokes and having a leading edge and a trailing edge;
a second wing segment coupled to at least two of the spokes and having a leading edge and a trailing edge;
one or more motors disposed within or attached to the six spokes; and
a propeller proximate to a leading edge of each of the six spokes, and operably connected to the one or more motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight;
wherein, when the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical;
wherein, when the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.

### Claim 15 (depends on 14)

The aircraft of claim 14, wherein the fuselage is configured to carry a payload.

### Claim 16 (depends on 14)

The aircraft of claim 14, wherein the first and second wing segments, the fuselage and the plurality of spokes are not substantially reconfigured for transition between vertical takeoff and landing, stationary flight and forward flight.

### Claim 17 (depends on 14)

The aircraft of claim 14, wherein the fuselage comprises two or more modules.

### Claim 18 (depends on 14)

The aircraft of claim 14, wherein the aircraft is unmanned.

### Claim 19 (depends on 14)

The aircraft of claim 14, wherein each propeller is a variable speed constant pitch propeller.