Pressure bulkhead for an aircraft fuselage

Patent metadata

Field	Value
Publication number	US-10384759-B2
Application number	US-201615361292-A
Country	US
Kind code	B2
Filing date	Nov 25, 2016
Priority date	May 26, 2014
Publication date	Aug 20, 2019
Grant date	Aug 20, 2019

Abstract

A pressure bulkhead for an aircraft fuselage having a skin element, with a first surface and a second surface, a circumferential edge and a center axis, and a reinforcement assembly, which has radially disposed reinforcement elements extending along the first surface radially between an outer end at the edge of the skin element and an inner end, which faces the center axis, wherein, in a cross section, which extends radially along the center axis, each of the radially disposed reinforcement elements defines first and second contour lines, each extending from the outer end of the radially disposed reinforcement elements to the inner end thereof, and the reinforcement assembly resting with the first contour lines thereof on the first surface of the skin element. A pressure bulkhead for an aircraft fuselage can efficiently absorb occurring pressure loads.

First claim

The invention claimed is:

1. A pressure bulkhead for an aircraft fuselage, comprising:
a skin element comprising a first surface and a second surface that is located opposite the first surface, and a circumferential edge and a center axis; and
a reinforcement assembly comprising a plurality of radially disposed reinforcement elements that extend along the first surface of the skin element in a radial direction between an outer end at the edge of the skin element and an inner end, which faces the center axis;
wherein, as viewed in a cross section, which extends radially along the center axis, each of the radially disposed reinforcement elements defines a first contour line and a second contour line, which is located opposite the first contour line, wherein each contour line extends from the outer end of the radially disposed reinforcement elements to the inner end thereof,
wherein the reinforcement assembly rests with the first contour lines thereof on the first surface of the skin element, and
wherein one of the first or second contour lines has a convex course extending from the outer end in a direction towards the inner end and all the way to the center axis, in which course a distance between the first contour line and the second contour line increases continuously.

2. The pressure bulkhead according to claim 1 , wherein, as viewed from the outer end to the inner end, the first or the second contour lines have a form of a catenary curve.

3. The pressure bulkhead according to claim 1 , wherein, as viewed from the outer end to the inner end, the first or the second contour lines have a form of a parabola.

4. The pressure bulkhead according to claim 1 , wherein, as viewed from the outer end to the inner end, the first or the second contour lines have form a segment of a circle.

5. The pressure bulkhead according to claim 1 , wherein the first contour lines have the convex course extending from the outer end in a direction towards the inner end, in which course the distance between the first contour lines and the second contour lines increases continuously, and wherein the second contour lines have a straight course.

6. The pressure bulkhead according to claim 5 , wherein the first surface of the skin element is oriented towards a pressure side of the aircraft fuselage.

7. The pressure bulkhead according to claim 1 , wherein both the first contour lines and the second contour lines have the convex course extending from the outer end in a direction towards the inner end, in which course the distance between the first contour lines and the second contour lines increases continuously.

8. The pressure bulkhead according to claim 7 , wherein the first surface of the skin element is oriented towards the pressure side of the aircraft fuselage.

9. The pressure bulkhead according to claim 1 , wherein the second contour lines have the convex course extending from the outer end in a direction towards the inner end, in which course the distance between the first contour lines and the second contour lines increases continuously, and wherein the first contour lines have a straight course.

10. The pressure bulkhead according to claim 9 , wherein an additional reinforcement assembly is provided, which rests against the second surface of the skin element, and which is designed in a manner that is analogous to the reinforcement assembly.

11. The pressure bulkhead according to claim 9 , wherein the second surface of the skin element is oriented towards the pressure side of the aircraft fuselage.

12. The pressure bulkhead according to claim 1 , wherein the reinforcement assembly has one or a plurality of tangentially disposed reinforcement elements, which extend in a tangential direction about the center axis along the first surface of the skin element, and from the first contour line to the second contour line, and which thereby form points of intersection with the radially disposed reinforcement elements.

13. The pressure bulkhead according to claim 12 , wherein two or more points of intersection, at which the radially disposed reinforcement elements and the tangentially disposed reinforcement elements intersect, are interconnected with one another by diagonally disposed reinforcement elements, which extend along the first surface of the skin element from the first contour line to the second contour line, and extend between the radially disposed reinforcement elements and the tangentially disposed reinforcement elements.

14. The pressure bulkhead according to claim 1 , wherein the pressure bulkhead is formed at least partially of a fiber reinforced composite material or at least partially of a metallic material.

15. The pressure bulkhead according to claim 1 , wherein the radially disposed reinforcement elements or the tangentially disposed reinforcement elements or the diagonally disposed reinforcement elements are designed in a form of T-profiles or in a form of TT-profiles or in a form of TY-profiles.

16. The pressure bulkhead according to claim 1 , wherein a plurality of connection elements is provided at the outer ends of the radially disposed reinforcement elements, wherein the connection elements form a part of the outer ends of the radially disposed reinforcement elements or are connected to the outer ends of the radially disposed reinforcement elements.

Assignees

• Airbus Operations Gmbh

Inventors

• Zuardy Ichwan
• Hoffmeister Thomas
• Herrmann Axel Siegfried
• Müller Markus

Classifications

• B64C1/10 Primary

  Bulkheads · CPC title

• B64C1/064

  Stringers; Longerons · CPC title