US 2015/0144736 A1 · PRESSURE BULKHEAD FOR AN AIRCRAFT AND DEVICE AS WELL AS METHOD FOR MANUFACTURING AN AIRCRAFT STRUCTURAL COMPONENT

Abstract

A pressure bulkhead made of fiber composite material for an aircraft fuselage for the pressure-tight axial closure of a fuselage region configured to be put under internal pressure. The bulkhead comprises a first area element, at least one second area element and a plurality of core elements. The first area element has a plurality of receptacles. Each receptacle is configured to receive a core element. The core elements are received in the receptacles between surfaces facing one another of the first area element and of the at least one second area element. The surfaces facing one another of the first area element and of the at least one second area element are connected to one another in regions without core elements.

Claims17

Dependent claims

a first area element;
at least one second area element;
and
a plurality of core elements, wherein the first area element has a plurality of receptacles, which are configured to receive a core element, wherein the core elements are received in the receptacles between surfaces facing one another of the first area element and of the at least one second area element and wherein the surfaces facing one another of the first area element and of the at least one second area element are connected to one another in regions without core elements.

1 more element

A device for manufacturing a pressure bulkhead for an aircraft fuselage made from fiber composite material for the pressure-tight axial closure of a fuselage region configured to be put under internal pressure, the device comprising:

a closable tool with a receiving device for receiving a semifinished arrangement provided for the manufacture of the aircraft structural component and a cover device for the pressure-tight covering of the receiving device, wherein the receiving device and the cover device, in the closed state, enclose a tool cavity;
a pressurization device for applying pressure upon the tool cavity;
and a matrix material supply device for supplying matrix material to the tool cavity and for introducing the matrix material into the semifinished arrangement;
wherein the receiving device of the tool has a surface structure with a plurality of receptacles, the receiving device being configured to act upon the semifinished arrangement upon pressurization of the tool cavity in such a way that the semifinished arrangement is provided with a surface structure corresponding to the surface structure of the receiving device, the surface structure having a plurality of receptacles, which are configured to receive a core element.

1 more element

A method for manufacturing a pressure bulkhead made of fiber composite material for an aircraft fuselage for the pressure-tight axial closure of a fuselage region configured to be put under internal pressure, the method comprising the steps:

a) inserting a semifinished arrangement provided for the manufacture of the aircraft structural component and comprising at least one fiber layer into an open tool, the open tool having a receiving device for receiving the semifinished arrangement and a cover device for a pressure-tight covering of the receiving device, wherein the receiving device and the cover device, in the closed state, enclose a tool cavity;
b) closing the tool;
c) pressurizing the tool cavity, so that a surface structure of the receiving device of the tool, which has a plurality of receptacles, acts upon the semifinished arrangement in such a way that the semifinished arrangement is provided with a surface structure corresponding to the surface structure of the receiving device, with a plurality of receptacles that are configured to receive a core element;
d) producing an over- or under pressure in the tool cavity suitable for an introduction of matrix material into the semifinished arrangement;
e) supplying matrix material into the tool cavity and introducing the matrix material into the semifinished arrangement;
f) curing the matrix material;
and
g) removing the fiber composite component.

5 more elements

Dependencies are inferred from the claim text.

Pressure bulkhead for an aircraft and device as well as method for manufacturing an aircraft structural component

Life of this patent

Pressure bulkhead for an aircraft and device as well as method for manufacturing an aircraft structural component

Life of this patent

Abstract

Claims17