Aircraft with an airframe and at least one electrically powered thrust producing unit

Patent metadata

Field	Value
Publication number	US-11117674-B2
Application number	US-201715832031-A
Country	US
Kind code	B2
Filing date	Dec 5, 2017
Priority date	Dec 7, 2016
Publication date	Sep 14, 2021
Grant date	Sep 14, 2021

Abstract

An aircraft with an airframe and at least one thrust producing unit the at least one thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to an electrical energy source via an electrical energy distribution system, wherein the airframe comprises at least one load carrying section and at least one propulsion system carrying section, wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other, wherein the at least one load carrying section is provided for transportation of passengers and/or cargo, and wherein the at least one propulsion system carrying section is provided for carrying at least essentially the electrical energy source and the electrical energy distribution system.

First claim

What is claimed is:

1. An aircraft comprising:
an airframe and at least one thrust producing unit, the at least one thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to an electrical energy source via an electrical energy distribution system, wherein the airframe comprises at least one load carrying section and at least one propulsion system carrying section,
wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other, wherein the at least one load carrying section is provided for transportation of passengers and/or cargo, and wherein the at least one propulsion system carrying section carries the electrical energy source and the electrical energy distribution system,
the at least one propulsion system carrying section comprising at least a first zone and a second zone that are segregated from each other, the electrical energy distribution system being only carried by the first zone and the electrical energy source being only carried by the second zone; and
the airframe comprising at least one segregating frame that segregates the at least one load carrying section from the at least one propulsion system carrying section,
wherein the first zone is segregated from the second zone of the at least one propulsion system carrying section by the at least one segregating frame or by a longeron or by a structural shell.

2. The aircraft of claim 1 ,
wherein the airframe comprises at least one longeron that segregates the first zone from the second zone.

3. The aircraft of claim 1 ,
wherein the at least one propulsion system carrying section comprises at least one third zone that is segregated from the first zone and spaced apart from the second zone, the at least one third zone being provided for carrying at least a portion of the electrical energy source.

4. The aircraft of claim 3 ,
wherein the airframe comprises at least one longeron that segregates the first zone from the at least one third zone.

5. The aircraft of claim 3 ,
wherein the airframe comprises a load carrying framework and at least one covering item, wherein the third zone is at least partly arranged between the load carrying framework and the at least one covering item.

6. The aircraft of claim 5 ,
wherein the at least one covering item is shaped to allow inflow of a cooling air stream at least into the second zone for cooling at least the electrical energy source.

7. The aircraft of claim 1 ,
wherein the electrical energy source is a high-voltage energy source.

8. The aircraft of claim 1 ,
wherein the electrical energy source is exchangeable and comprises at least two exchangeable energy source units.

9. The aircraft of claim 8 ,
wherein quick releases are provided that allow at least a quick release of the at least two exchangeable energy source units for removal of the at least two exchangeable energy source units from the aircraft.

10. The aircraft of claim 1 ,
wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other in longitudinal direction of the aircraft.

11. The aircraft of claim 1 ,
wherein at least three additional thrust producing units are provided, each additional thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to the electrical energy source via the electrical energy distribution system, the aircraft being implemented as a multicopter.

12. The aircraft of claim 1 ,
wherein the aircraft is configured as a vertically taking off and landing air vehicle.

13. An aircraft comprising:
an airframe and at least one thrust producing unit, the at least one thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to an electrical energy source via an electrical energy distribution system, wherein the airframe comprises at least one load carrying section and at least one propulsion system carrying section,
wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other, wherein the at least one load carrying section is provided for transportation of passengers and/or cargo, and wherein the at least one propulsion system carrying section carries the electrical energy source and the electrical energy distribution system,
the at least one propulsion system carrying section comprising at least a first zone, a second zone, and a third zone that are segregated from each other, the electrical energy distribution system being only carried by the first zone and the electrical energy source being only carried by the second zone, wherein the first zone is positioned in between the second zone and the third zone; and
the airframe comprising at least one frame that segregates the at least one load carrying section from the at least one propulsion system carrying section,
wherein the first zone is segregated from the second zone of the at least one propulsion system carrying section by the at least one frame or by a longeron or by a structural shell.

14. The aircraft of claim 13 further comprising a first longeron segregating the first zone from the second zone and a second longeron segregating the first zone from the third zone.

15. The aircraft of claim 13 , wherein the aircraft is configured as a vertically taking off and landing air vehicle.

16. The aircraft of claim 13 , wherein the electrical energy source is a high-voltage energy source.

17. An aircraft comprising:
an airframe and at least one thrust producing unit, the at least one thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to an electrical energy source via an electrical energy distribution system, wherein the airframe comprises at least one load carrying section and at least one propulsion system carrying section,
wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other, wherein the at least one load carrying section is provided for transportation of passengers and/or cargo, and wherein the at least one propulsion system carrying section carries the electrical energy source and the electrical energy distribution system,
the at least one propulsion system carrying section comprising at least a first zone and a second zone that are segregated from each other by a first longeron, the electrical energy distribution system being only carried by the first zone and the electrical energy source being only carried by the second zone; and
the airframe comprising at least one frame that segregates the at least one load carrying section from the at least one propulsion system carrying section.

18. The aircraft of claim 17 ,
wherein the at least one propulsion system carrying section comprises at least one third zone that is segregated from the first zone and spaced apart from the second zone, the at least one third zone being provided for carrying at least a portion of the electrical energy source.

19. The aircraft of claim 18 , wherein the airframe comprises second longeron that segregates the first zone from the at least one third zone.

20. The aircraft of claim 17 , wherein the electrical energy source is a high-voltage energy source.

Assignees

• Airbus Helicopters Deutschland GmbH

Inventors

• Mores Sebastian
• Blacha Martin
• Reichensperger Christian
• Rittel Klaus
• Schneeberger Marco
• Geiss Michael
• Paschek Markus
• Bebesel Marius

Classifications

• B64D27/35

  Arrangements for on-board electric energy production, distribution, recovery or storage · CPC title

• B64D27/34

  All-electric aircraft · CPC title

• B64C1/06 Primary

  Frames; Stringers; Longerons {; Fuselage sections} · CPC title

• B64U10/17

  Helicopters (flying platforms B64U10/13) · CPC title

• B64U50/13

  using external fans or propellers · CPC title