Airbus Operations Gmbh

Klaus Rode

Hauke Seegel

Georg Lonsdorfer

Andreas Pau

Hartmut Herter

Kevin Danke

A method for stiffening a skin field of an aircraft fuselage includes providing a skin field for an aircraft fuselage, manufacturing an integral lattice-shaped stiffening structure including a plurality of longitudinal stiffeners and connecting the stiffening structure to the skin field. The manufacturing can include the use of a tool mold having a plurality of longitudinal recesses configured to form longitudinal stiffeners and a plurality of sunken areas disposed between the longitudinal recess. The sunken areas are configured for forming respective mounts that are configured for connection to circumferential stiffeners.

Method and a device for the manufacture of a stiffening structure for an aircraft fuselage segment, and also a stiffening structure

A method for manufacturing a fiber composite component having an integral structural design includes positioning a sheet-like fibrous semi-finished product in a mold that defines an outer contour of the fiber composite component. Dimensionally stable fibrous semi-finished products, each having dimensions corresponding to a respective portion of the manufactured fiber composite component, are arranged on the sheet-like fibrous semi-finished product. The dimensionally stable fibrous semi-finished products are stabilized and fixed in place using mold cores. The semi-finished products are resin infiltrated using one of a first or a second gating process so as to form a construct. The first gating process includes gating via the mold cores at a head of each dimensionally stable fibrous semi-finished product and performing extraction in an area of the mold. The second gating process including gating in an area of the mold and performing extraction via the mold cores at the head of each dimensionally stable fibrous semi-finished product. The construct is hardened and demolded by removing the mold cores.

Method and device for manufacturing a fiber composite component with an integral structural design

A method of manufacturing a component from a composite-fiber-material semifinished product includes providing a forming support having a contour including at least one section corresponding to a surface of the manufactured component. The semifinished product is placed onto the forming support and the semifinished product is formed such that the semifinished product contacts the forming support. Further, a device form manufacturing component includes the forming support having the contour including at least one section corresponding to the surface of the manufacture component.

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Oberhaching, Germany

Klaus Rode