Airbus Operations Gmbh

Airbus UK Limited

Steven Evans

Simon Astwood

Oliver Marks

Christopher David Jones

Chistopher David Jones

A combined composite and metal hybrid component and a method of forming said component, are disclosed, the component comprising a substantially sheet-like or web-like body portion, made of a composite material, at least one stiffening member made of a metal and at least one made of a composite material, and curing the component in a vacuum bag, such that the metal stiffening member is formed against the composite stiffening member and the metal stiffening member remains a part of the hybrid composite component.

Composite structures

The present invention relates to structural component for an aircraft. The structural component comprises a body with a first surface and a lug that extends out of the first surface. The body and lug comprise a composite material and are integrally formed.

Structural component

An aircraft wing torsion box having a front associated with a leading portion of the wing torsion box and a rear associated with a trailing portion of the wing torsion box. The wing torsion box includes a support member having a front spar and a rear spar and a connecting portion between the front and rear spars, the connecting portion includes at least one interposing spar, at least one portion of upper wing skin; and at least one portion of lower wing skin, and at least one portion of the upper wing skin and at least one portion of the lower wing skin being supported by the support member.

Aircraft wing torsion box, aircraft wing, aircraft and supporting member for use therein

A structure having a panel, a stringer, and a rib is disclosed. The stringer includes a stringer flange that is joined to the panel and a stringer web that extends away from the stringer flange. The rib includes a rib web that has first and second faces and a rib foot that has a first rib foot flange that is joined to the stringer web, a second rib foot flange that is joined to the panel and a rib foot web that is joined to the first face of the rib web. The first rib foot flange is connected to the rib foot web by a first corner that includes at least one layer which runs continuously from the first rib foot flange into the rib foot web via the first corner. The second rib foot flange is connected to the rib foot web by a second corner that includes at least one layer which runs continuously from the second rib foot flange into the rib foot web via the second corner.

Aircraft structure

A method of roll forming a plurality of composite components. The method includes the steps: (a) laying a plurality of blanks onto a carrier strip, each blank including a stack of sheets of uncured composite material contacting a respective contact part of the carrier strip; (b) after step (a), forming the blanks and their respective contact parts of the carrier strip with a desired cross-sectional profile by passing the carrier strip carrying the blanks through a series of sets of rollers, each set of rollers performing an incremental part of a bending operation until the desired cross-sectional profile is obtained; (c) after step (b), separating the blanks along with their respective carrier strips from the rest of the carrier strip; and (d) before or after step (c), curing the blanks.

Roll forming composite components

A method of making an aircraft component is provided, wherein the method comprises the steps of:

Method for forming composite components and tool for use therein

A fiber placement tool comprising a plurality of tool segments, each tool segment having an outer surface defining a predetermined profile, each tool segment being removably mounted on at least one elongate shaft.

Fibre placement tool

A method of making an aircraft component is provided, wherein the method comprises the steps of: providing a mould () for the receipt of a material () from which the aircraft component is to be made providing the mould with said material providing an intensification tool () in spaced relationship to the mould and heating the material, tool and mould so that the tool expands and applies pressure to the material and so as to form the component and wherein the linear coefficient of thermal expansion of the tool in a first direction is matched to the coefficient of thermal expansion of the component in the first direction, and the coefficient of thermal expansion of the tool in a second direction is greater than the coefficient of thermal expansion of the component in the second direction, the tool being provided with at least one contacting surface for contacting the material and through which pressure is applied to the material, the expansion of the tool in the second direction causing the at least one contacting surface to contact, and exert pressure on, the material.

Growing community of inventors

Bristol, United Kingdom

Steven Evans