Structural assembly for an aircraft fuselage with double curvature including frames with an optimized orientation

Patent metadata

Field	Value
Publication number	US-10427773-B2
Application number	US-201615353319-A
Country	US
Kind code	B2
Filing date	Nov 16, 2016
Priority date	Nov 17, 2015
Publication date	Oct 1, 2019
Grant date	Oct 1, 2019

Abstract

In order to allow an aircraft fuselage structure to provide optimum resistance to pressurization loads in a fuselage region with a double curvature, the fuselage structure includes a circumferential frame oriented so that the web of the circumferential frame has an orientation close to the local normal to the skin of the fuselage.

First claim

The invention claimed is:

1. A structural assembly for forming a part of an aircraft fuselage, comprising:
a fuselage skin having a double curvature; and
circumferential frames that comprise a web and a flange substantially orthogonal to the web and to which the fuselage skin is fixed,
wherein the circumferential frames comprise at least one first circumferential frame having a lower extremity and an upper extremity and conformed so that a first virtual straight line half-segment, which passes through the web and originates from a middle of a first virtual straight line segment connecting the lower extremity to the upper extremity, extending orthogonally to the first virtual straight line segment, intersects the fuselage skin at a point at which the first virtual straight line half-segment is substantially normal to the fuselage skin.

2. The structural assembly according to claim 1 , wherein the web of the first circumferential frame is inscribed in a plane at an angle strictly between 0 and 45 degrees to a transverse plane.

3. The structural assembly according to claim 1 , wherein the lower extremity and the upper extremity of the first circumferential frame are situated on a same lateral side of the structural assembly.

4. The structural assembly according to claim 1 , wherein the web of the first circumferential frame has a portion centered relative to a point of intersection of the first virtual straight line half-segment and the fuselage skin, wherein the portion extends at an angle less than 20 degrees to a local normal to the fuselage skin and has a circumferential extent exceeding 10% of a circumferential extent of the first circumferential frame.

5. The structural assembly according to claim 1 , wherein the circumferential frames further include at least one second circumferential frame extending symmetrically with respect to the first circumferential frame relative to a vertical median plane of the structural assembly.

6. The structural assembly according to claim 1 , wherein the lower extremity of the first circumferential frame is connected to a landing gear well structure.

7. The structural assembly according to claim 1 , further comprising a lower windshield frame section to support an aircraft cockpit windshield and in which the upper extremity of the first circumferential frame is connected to the lower windshield frame section.

8. The structural assembly according to claim 7 , comprising a one-piece upper portion integrating a part of the fuselage skin and a structure comprising the lower windshield frame section and an upper windshield frame section, uprights, stringers, and an upper extremity portion of the first circumferential frame, and in which the lower windshield frame section, the upper windshield frame section and the uprights delimit the aircraft cockpit windshield.

9. The structural assembly according to claim 8 , wherein all the stringers of the upper portion and the lower windshield frame section, the upper windshield frame section and the uprights each comprising a second web having a third extremity and an opposite fourth extremity and are each conformed so that a corresponding second virtual straight line half-segment, which passes thorough the web and through a middle of a corresponding second virtual straight line segment connecting the third extremity to the fourth extremity and extends orthogonally to the second virtual straight line segment, intersects the fuselage skin at a second point at which the second virtual straight line half-segment is substantially normal to the fuselage skin.

10. An aircraft comprising a structural assembly forming a part of a fuselage of the aircraft, the structural assembly comprising:
a fuselage skin having a double curvature, and
circumferential frames that comprise a web and a flange substantially orthogonal to the web and to which the fuselage skin is fixed,
wherein the circumferential frames comprise at least one first circumferential frame having a lower extremity and an upper extremity and conformed so that a first virtual straight line half-segment, which passes through the web and originates from a middle of a first virtual straight line segment connecting the lower extremity to the upper extremity, extending orthogonally to the first virtual straight line segment, intersects the fuselage skin at a point at which the first virtual straight line half-segment is substantially normal to the fuselage skin.

11. The aircraft according to claim 10 , including a nose section that comprises the structural assembly.

Assignees

• Airbus Operations Sas

Inventors

• Bellet Daniel
• Bernadet Philippe

Classifications

• B64C1/10

  Bulkheads · CPC title

• B64C1/36

  adapted to receive antennas or radomes · CPC title

• B64C25/14

  fore-and-aft · CPC title

• B64C1/1492

  Structure and mounting of the transparent elements in the window or windscreen · CPC title

• B64C1/12

  Construction or attachment of skin panels · CPC title