Aircraft including a passenger cabin extending around a space defined outside the cabin and inside the aircraft

Patent metadata

Field	Value
Publication number	US-9611039-B2
Application number	US-201414263376-A
Country	US
Kind code	B2
Filing date	Apr 28, 2014
Priority date	Apr 29, 2013
Publication date	Apr 4, 2017
Grant date	Apr 4, 2017

Abstract

The sealed bottoms of aircraft passenger cabin have to be fastened with heavily sized fasteners so as to withstand loads induced by the cabin pressurization. Besides, the increase in aircrafts seating capacity makes an increase in passenger cabin widths of interest. Such a width increase however makes the structure delimiting passenger cabin less resistant to efforts induced by the cabin pressurization. The present invention proposes an aircraft wherein the structure delimiting passenger cabin extends over 360 degrees around a space defined outside structure. The invention allows structure to be more resistant to loads induced by the cabin pressurization, while allowing to reduce or even to avoid the need for a sealed bottom, and while allowing to increase the space available for passengers.

First claim

The invention claimed is:

1. An aircraft comprising a structure having a substantially continuous passenger cabin, wherein, when the structure is seen from above, the structure comprises:
at least two lateral portions respectively comprising two lateral regions of the substantially continuous passenger cabin and separated from each other by a space defined outside the structure and extending between substantially solid lower and upper parts of an aerodynamic envelope externally delimiting the aircraft;
a forward portion connecting two forward ends of the lateral portions of the structure to each other; and
an aft portion connecting two aft ends of the lateral portions of the structure to each other,
wherein the at least two lateral portions, the forward portion, and the aft portion comprise the substantially continuous passenger cabin, and
wherein the aircraft comprises a propulsion system located external to the aerodynamic envelope of the aircraft.

2. The aircraft according to claim 1 , wherein, when the structure is seen from above, the forward portion of the structure has an outside edge that is concave from a first end of the forward portion as far as a second end of the forward portion opposite the first end, with a concave face of the outside edge facing an aft side of the aircraft.

3. The aircraft according to claim 1 , wherein the aft portion comprises one median section and two lateral sections arranged on respective sides of the median section to define second and third spaces outside the structure, these second and third spaces extending between the median section and the lateral sections of the aft portion, each being delimited by the lower and upper parts of the aerodynamic envelope.

4. The aircraft according to claim 1 , wherein the aerodynamic envelope comprises at least one access hatch for accessing the space.

5. The aircraft according to claim 4 , further comprising a removable container housed inside the space.

6. The aircraft according to claim 4 , further comprising a landing gear housed in the space.

7. The aircraft according to claim 4 , wherein the structure comprises at least one internal door for accessing the space.

8. A method for embarking or disembarking passengers onto or off of the aircraft according to claim 7 , the method comprising extending a passenger passage through the access hatch of the aerodynamic envelope, through the space, and through the at least one internal door of the structure.

9. The aircraft according to claim 1 , wherein each of the at least two lateral portions of the structure comprises a plurality of circumferential stiffening frames.

10. The aircraft according to claim 9 , wherein each of the forward and aft portions comprises a plurality of circumferential stiffening frames.

11. The aircraft according to claim 10 , wherein the circumferential stiffening frames of the at least two lateral portions and of the forward and aft portions are disposed in corresponding planes and arranged such that when the structure is seen from above with respect to an anticlockwise direction, a plane of each circumferential stiffening frame defines a positive or zero anticlockwise angle with respect to a plane of an immediately preceding circumferential stiffening frame in a clockwise direction.

Assignees

• Airbus Operations Sas

Inventors

• Lieven Patrick
• Delahaye Romain
• Perju Catalin

Classifications

• B64D9/00

  Equipment for handling freight; Equipment for facilitating passenger embarkation or the like · CPC title

• B64C1/00

  Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like · CPC title

• B64C2039/105

  of blended wing body type · CPC title

• B64D11/00 Primary

  Passenger or crew accommodation; Flight-deck installations not otherwise provided for · CPC title

• B64C2001/0045

  Fuselages characterised by special shapes · CPC title