Aircraft

Patent metadata

Field	Value
Publication number	US-10358229-B2
Application number	US-201615135040-A
Country	US
Kind code	B2
Filing date	Apr 21, 2016
Priority date	May 13, 2015
Publication date	Jul 23, 2019
Grant date	Jul 23, 2019

Abstract

An aircraft including trailing edge flaps, a wing mounted propulsor positioned such that the flaps are located in a slipstream of the first propulsor in use when deployed. The aircraft further including a thrust vectorable propulsor configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane. The thrust vectorable propulsor includes a ducted fan configurable between a first mode, in which the fan provides net forward thrust to the aircraft, and a second mode in which the fan provides net drag to the aircraft. The fan is positioned to ingest a boundary layer airflow in use when operating in the first mode.

First claim

The invention claimed is:

1. An aircraft comprising:
a thrust vectorable propulsor provided at a tail of the aircraft and configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane and configurable between a first mode, in which the thrust vectorable propulsor provides net forward thrust to the aircraft, and a second mode in which the thrust vectorable propulsor provides net drag to the aircraft, the thrust vectorable propulsor being positioned to ingest a boundary layer airflow of a fuselage of the aircraft in use when operating in the first mode;
a deployable high lift device comprising at least one of one or more flaps located at a trailing edge of a wing of the aircraft, and one or more slats located at a leading edge of the wing, the deployable high lift device being deployable to increase the lift generated by the wing in flight;
a plurality of further propulsors located on the wing, which are not a thrust vectorable propulsors, located such that the high lift device is located in a slipstream of the plurality of further propulsors in use when deployed; and
an internal combustion engine for providing power to the plurality of propulsors, the internal combustion engine being positioned on the wing outboard of the plurality of further propulsors relative to the fuselage.

2. An aircraft according to claim 1 , wherein the deployable high lift device comprises at least one flap located at the trailing edge of the wing, and at least one slat located at the leading edge of the wing and corresponding to the flap, the at least one flap and the at least one slat being located in the slipstream of the plurality of further propulsors in use when deployed.

3. An aircraft according to claim 1 , wherein at least one of the thrust vectorable propulsor and the plurality of further propulsors comprises an electrically or mechanically driven propeller or ducted fan.

4. An aircraft according to claim 1 , wherein the plurality of further propulsors each comprise an intake located ahead of a leading edge of the wing.

5. An aircraft according to claim 1 , wherein the aircraft comprises at least one of an internal combustion engine arranged to provide power to at least the thrust vectorable propulsor, and an electrical power source arranged to provide power to at least the thrust vectorable propulsor.

6. An aircraft according to claim 5 , wherein the aircraft comprises at least one of an internal combustion engine driven electrical generator, the electrical generator being electrically coupled to one or more propulsor driving electrical motors to thereby power one or more of the plurality of further propulsors, and an internal combustion engine driven gearbox configured to drive at least one of the plurality of further propulsors.

7. An aircraft according to claim 1 , wherein the thrust vectorable propulsor comprises an intake positioned at an aft end of the fuselage.

8. An aircraft according to claim 1 , wherein the thrust vectorable propulsor comprises a variable pitch fan located within a duct.

9. An aircraft according to claim 8 , wherein the thrust vectorable propulsor comprises at least one of an inlet guide vane positioned upstream of the fan, and an outlet guide vane positioned downstream of the fan.

10. An aircraft according to claim 9 , wherein one or both of the inlet and outlet guide vanes are variable pitch.

11. An aircraft according to claim 3 , wherein the thrust vectorable propulsor comprises at least one of a variable area inlet arrangement, and a variable area outlet arrangement.

12. An aircraft according to claim 11 , wherein the thrust vectorable propulsor comprises a duct wall having a translatable section configured to open an annular gap in the duct wall when in an open position, and close the annular gap when in a closed position.

13. An aircraft according to claim 11 , wherein the thrust vectorable propulsor comprises a translatable plug nozzle configured to increase the outlet area when in a first position and decrease the outlet area when in a second position.

14. An aircraft comprising:
a thrust vectorable propulsor configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane and configurable between a first mode, in which the thrust vectorable propulsor provides net forward thrust to the aircraft, and a second mode in which the thrust vectorable propulsor provides net drag to the aircraft, the thrust vectorable propulsor being positioned to ingest a boundary layer airflow in use when operating in the first mode;
a motor for driving the thrust vectorable propulsor;
an electric power source arranged to provide power to the motor; and
of an internal combustion engine arranged to provide power to the electrical power source, the internal combustion engine being positioned on a wing outboard of a plurality of further propulsors relative to the fuselage.

15. An aircraft comprising:
a thrust vectorable propulsor provided at a tail of the aircraft and configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane and configurable between a first mode, in which the thrust vectorable propulsor provides net forward thrust to the aircraft, and a second mode in which the thrust vectorable propulsor provides net drag to the aircraft, the thrust vectorable propulsor being positioned to ingest a boundary layer airflow of a fuselage of the aircraft in use when operating in the first mode;
a deployable high lift device comprising one or more slats located at a leading edge of the wing, the one or more slats being deployable to increase the lift generated by the wing in flight; and
a plurality of further propulsors located such that the one or more slats is located in a slipstream of the plurality of further propulsors in use when deployed; and
an internal combustion engine for providing power to the plurality of propulsors, the internal combustion engine being positioned on the wing outboard of the plurality of further propulsors relative to the fuselage.

Assignees

• Rolls Royce Plc

Inventors

• Moxon Matthew

Classifications

• B64C3/50

  by leading or trailing edge flaps · CPC title

• Y02T50/166

  Cross-Sectional Technologies · mapped topic

• B64D29/04

  associated with fuselages · CPC title

• B64D2027/026

  Operations & Transport · mapped topic

• B64D27/02

  Aircraft characterised by the type or position of power plants · CPC title