VTOL aircraft

Patent metadata

Field	Value
Publication number	US-11524778-B2
Application number	US-202017080145-A
Country	US
Kind code	B2
Filing date	Oct 26, 2020
Priority date	Oct 24, 2019
Publication date	Dec 13, 2022
Grant date	Dec 13, 2022

Abstract

A VTOL aircraft has fixed wings and a rotor blade system for providing lift in active and passive modes thereof. Operation of the rotor blade system may be switched between the active mode in which the rotor blade system is driven by a power system of the aircraft and the passive mode in which the rotor blade system is not driven by the power system, the rotor blade system being configurable to provide lift in the passive mode during forward flight of the aircraft. The rotor blade system provides lift in the passive mode, allowing the fixed wings to be shorter than in the case where the rotor system provides lift during vertical take-off and landing but otherwise has no function, thus providing aircraft which is lighter, more compact and more efficient than similar aircraft of the prior art.

First claim

The invention claimed is:

1. A VTOL aircraft comprising:
a pair of fixed wings each wing being located on a respective lateral side of a fuselage of the aircraft, and
a propeller for providing forward thrust when driven by a power system of the aircraft and rotor blade system for providing lift in active and passive modes thereof, the rotor blade system comprising first and second sets of rotor blades, each of which is mounted on a respective one of opposite lateral sides with respect to the fuselage and by a respective fixed wing, wherein
operation of the rotor blade system may be switched between the active mode in which the rotor blade system is driven by a power system of the aircraft and the passive mode in which the rotor blade system is not driven by the power system of the aircraft, the rotor blade system being configurable to provide lift in the passive mode during forward flight of the aircraft,
the first and second sets of rotor blades are comprised in first and second rotor units respectively, each rotor unit being rotatably mounted to a respective fixed wing of the aircraft such that the rotation axis of any given set of the first and second sets of rotor blades may be rotated in a plane which is orthogonal to the horizontal plane of the aircraft and parallel to the central longitudinal axis of the aircraft between a first orientation in which the rotation axis of the set is substantially normal to the horizontal plane of the aircraft and the rotor blade system is in the active mode thereof and a second orientation in which the rotation axis of the set is inclined to the horizontal plane of the aircraft and the rotor blade system is in the passive mode thereof, and
the first and second rotor units each comprise a respective rudder for influencing yaw of the aircraft.

2. A VTOL aircraft according to claim 1 wherein each of the first and second sets of rotor blades comprises respective first and second sub-sets of rotor blades, the sub-sets of a given set being arranged for rotation about a common rotation axis and mutually displaced along said axis.

3. A VTOL aircraft according to claim 1 further comprising a second pair of fixed wings each of which is located on a respective lateral side of the aircraft, the second pair of fixed wings being located forward of the pair of fixed wings.

4. A VTOL aircraft according to claim 3 wherein the rotor blade system further comprises third and fourth sets of rotor blades, each of which is mounted by a respective fixed wing of the second pair of fixed wings.

5. A VTOL aircraft according to claim 4 wherein the third and fourth sets of rotor blades are comprised in third and fourth rotor units respectively, each of the third and fourth rotor units being mounted to a respective fixed wing of the second pair of fixed wings such that the rotation axis of any given set of the third and fourth sets of rotor blades may be rotated in a plane which is orthogonal to the horizontal plane of the aircraft and parallel to the central longitudinal axis of the aircraft between a first orientation in which the rotation axis of the set is substantially normal to the horizontal plane of the aircraft and the rotor blade system is in the active mode thereof and a second orientation in which the rotation axis of the set is inclined to the horizontal plane of the aircraft and the rotor blade system is in the passive mode thereof.

6. A VTOL aircraft according to claim 5 wherein the third and fourth rotor units each comprise a respective rudder for influencing the yaw of the aircraft.

7. A VTOL aircraft according to claim 1 wherein at least part of the rotor blade system may be arranged to drive an electrical generator or an electrical machine configured as an electrical generator during the passive mode of operation of the rotor blade system.

8. A VTOL aircraft according to claim 1 wherein the power system comprises an electric motor or an electrical machine configurable as an electric motor and an electrical power source and wherein in the active mode the electric motor or the electrical machine configured an electric motor is arranged to receive electrical power from the electrical power source and to drive at least part of the rotor blade system.

9. A VTOL aircraft according to claim 8 wherein the electrical power source is an electrical power generator.

10. A VTOL aircraft according to claim 8 wherein the electrical power source is an electrical energy store.

11. A VTOL aircraft according to claim 8 wherein the electrical power source comprises an electrical power generator and an electrical energy store and wherein the power system is configurable such that (i) the electric motor or the electrical machine configured as an electric motor may receive electrical power from the electrical power generator or the electrical energy store or both the electrical power generator and the electrical energy store, and (ii) the electrical energy store receives electrical power from the electrical power generator.

12. A VTOL aircraft according to claim 11 wherein the power system comprises an electric motor arranged to receive electrical power from the electrical power generator, the electrical energy store or both the electrical power generator and the electrical energy store and to provide mechanical power to the propeller.

13. A VTOL aircraft according to claim 12 wherein the electrical power source comprises an electrical generator and a gas turbine engine arranged to drive the electrical generator.

14. A VTOL aircraft according to claim 13 wherein a shaft of the gas turbine engine is mechanically coupled to or integral with a shaft of the electric motor which is arranged to provide mechanical power to the propeller.

15. A VTOL aircraft according to claim 10 wherein the electric motor or the electrical machine configured as an electric motor is an electrical machine and is configurable in the passive mode as an electrical generator which is arranged to provide electrical power to the electrical energy store.

16. A VTOL aircraft comprising:
a first pair of fixed wings each wing being located on a respective lateral side of the aircraft;
a propeller for providing forward thrust when driven by a power system of the aircraft and rotor blade system for providing lift in active and passive modes thereof, the rotor blade system comprising first and second sets of rotor blades, each of which is mounted by a respective fixed wing, wherein operation of the rotor blade system may be switched between the active mode in which the rotor blade system is driven by a power system of the aircraft and the passive mode in which the rotor blade system is not driven by the power system of the aircraft, the rotor blade system being configurable to provide lift in the passive mode during forward flight of the aircraft; and
a second pair of fixed wings each of which is located on a respective lateral side of the aircraft, the second pair of fixed wings being located forward of the first pair of fixed wings; wherein
the rotor blade system further comprises third and fourth sets of rotor blades, each of which is mounted by a respective fixed wing of the second pair of fixed wings,
the third and fourth sets of rotor blades are in third and fourth rotor units respectively, each of the third and fourth rotor units being mounted to a respective fixed wing of the second pair of fixed wings such that the rotation axis of any given set of the third and fourth sets of rotor blades may be rotated in a plane which is orthogonal to the horizontal plane of the aircraft and parallel to the central longitudinal axi

Assignees

• Rolls Royce Plc

Inventors

• Saias Chana A
• Pachidis Vasileios

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• B64C27/52

  Tilting of rotor bodily relative to fuselage (of see-saw type construction B64C27/43) · CPC title

• B64C27/26

  characterised by provision of fixed wings · CPC title

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title

• B64C27/02

  Gyroplanes · CPC title