Single engine, asymmetrical vertical take-off and landing (VTOL) aircraft

Patent metadata

Field	Value
Publication number	US-10647442-B2
Application number	US-201515543443-A
Country	US
Kind code	B2
Filing date	Nov 16, 2015
Priority date	Jan 16, 2015
Publication date	May 12, 2020
Grant date	May 12, 2020

Abstract

A vertical take-off and landing (VTOL) aircraft is provided and includes wings, first and second nacelles supported on each of the wings, each of the first and second nacelles including a propeller drivable to generate aircraft thrust, and an asymmetrical power generation unit. The asymmetrical power generation unit includes a single engine unit disposed in only one of the first and second nacelles to generate power to drive the propellers of both the first and second nacelles.

First claim

What is claimed is:

1. A vertical take-off and landing (VTOL) aircraft, comprising:
a first wing and a second wing;
a first nacelle supported on the first wing and a second nacelle supported on the second wing,
each of the first and second nacelles including a propeller drivable to generate aircraft thrust; and
an asymmetrical power generation unit including a single engine unit disposed in only one of the first and second nacelles to generate power to drive the propellers of both the first and second nacelles.

2. The aircraft according to claim 1 , further comprising a fuselage from which the first and second wings extend outwardly.

3. The aircraft according to claim 2 , wherein the fuselage and the first nacelle or second nacelle not including the single engine unit encompass at least one or more of aircraft electronic components, payload elements and fuel.

4. The aircraft according to claim 1 , wherein the single engine unit comprises a gas turbine engine.

5. The aircraft according to claim 1 , wherein the single engine unit comprises:
an output shaft;
a compressor-combustor-turbine (CCT) section to compress inlet air, to mix the compressed air with fuel, to combust the mixture to produce high energy fluids and to expand the high energy fluids to generate rotational energy to rotate the output shaft; and
an exhaust duct by which remaining high energy fluids are exhausted.

6. The aircraft according to claim 5 , wherein the first nacelle includes the single engine unit and the aircraft further comprises:
a first gearbox assembly to which the output shaft is coupled and which is configured to drive the propeller of the first nacelle;
a second gearbox assembly configured to drive the propeller of the second nacelle; and
a drive shaft assembly by which rotation of the first gearbox assembly is transmitted to the second gearbox assembly.

7. The aircraft according to claim 6 , wherein the first and second gearbox assemblies are configured to gear up or down rotations of the output shaft.

8. The aircraft according to claim 6 , wherein the drive shaft assembly comprises respective series of shaft sections and bearings.

9. The aircraft according to claim 1 , further comprising alighting elements forming at least a three-point stable support system for the aircraft.

10. A vertical take-off and landing (VTOL) aircraft, comprising:
a fuselage;
a first wing and a second wing extending outwardly from sides of the fuselage;
a first nacelle supported on the first wing and a second nacelle supported on the second wing, each of the first and second nacelles including a propeller drivable to generate aircraft thrust; and
an asymmetrical power generation unit including a single engine unit disposed in only one of the first and second nacelles to generate power to drive the propellers of both the first and second nacelles,
wherein the fuselage and the first nacelle or second nacelle not including the single engine unit encompass at least one or more of aircraft electronic components, payload elements and fuel.

11. The aircraft according to claim 10 , wherein the single engine unit comprises: an output shaft;
a compressor-combustor-turbine (CCT) section to compress inlet air, to mix the compressed air with fuel, to combust the mixture to produce high energy fluids and to expand the high energy fluids to generate rotational energy to rotate the output shaft; and
an exhaust duct by which remaining high energy fluids are exhausted.

12. The aircraft according to claim 11 , wherein the first nacelle includes the single engine unit and the aircraft further comprises:
a first gearbox assembly to which the output shaft is coupled and which is configured to drive the propeller of the first nacelle;
a second gearbox assembly configured to drive the propeller of the second nacelle; and
a drive shaft assembly by which rotation of the first gearbox assembly is transmitted to the second gearbox assembly.

13. The aircraft according to claim 12 , wherein the first and second gearbox assemblies are configured to gear up or down rotations of the output shaft.

14. The aircraft according to claim 12 , wherein the drive shaft assembly comprises respective series of shaft sections and bearings.

15. The aircraft according to claim 10 , further comprising alighting elements forming at least a three-point stable support system for the aircraft.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Alber Mark R

Classifications

• B64C27/82

  characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft · CPC title

• B64C29/02

  having its flight directional axis vertical when grounded · CPC title

• B64D35/04 Primary

  characterised by the transmission driving a plurality of propellers or rotors · CPC title

• B64D27/12

  within, or attached to, wings · CPC title

• B64D27/06

  within, or attached to, wings · CPC title