Airbus Operations Sl

Airbus Espana, S.l.

Antonio De Julián Aguado

Vicente Martínez Valdegrama

Pedro Nogueroles Viñes

Raúl Burgos Gallego

José Luis Lozano García

Loreto Martinez Fernández

Oscar De La Cruz Garcia

José Luis Lozano Garcia

Loreto Martínez Fernández

José Luis Lozano GARCÍA

Oscar De La Cruz GARCÍA

Method of manufacture of one or more pairs of components in composite material (') intended to form part of aerofoils located on both sides of the axis of symmetry of an aircraft whose shape has a conical tendency in the longitudinal direction, the angle of conicity being less than 10&#xb0;, that comprises the following stages: a) Lay-up of layers on a flat tape lay-up table forming the laminate of a hypothetical component formed by all of the components of said pairs (), the components of each pair being arranged adjacently and the first components () and the second components () of each pair being arranged alternately, and the whole being arranged symmetrically relative to a hypothetical horizontal axis X-X of the tape lay-up jig; b) Cutting of the flat laminates corresponding to each of said components); c) Forming and curing said components.

Method for the manufacture of one or more pairs of components in composite material

Joining arrangement for the lateral boxes (') of a horizontal tail stabilizer with a central tubular box and manufacturing method for said box. The boxes (&#x2032;) are joined using an intermediate joining part () that comprises a central box (), upper (&#x2032;) and lower (&#x2032;) lateral flaps, fitting plates (A) for the trimming device and fitting plates (B) for the pivoting device, the join being made with rivets between the skins (&#x2032;) of the lateral boxes (&#x2032;) and said flaps (&#x2032;). The method for manufacturing the intermediate joining part () comprises steps to: a) Provide preforms suitable for forming said part (); b) Form and cure the part () made from said preforms using an RTM method.

Joining arrangement for the lateral boxes of a horizontal tail stabiliser with a tubular central box and manufacturing method for said box

Computer assisted method for the advanced design of bent parts of composite material using a computer assisted CAD system comprising the following stages: a) Supplying the 2D mesh model () of the part; b) Generating the 3D outer surface () of the part; c) Obtaining the 3D mesh model () by adapting the 2D mesh model () to the geometry of the 3D outer surface () by bending the contour lines () of the patterns () of the 2D model () with respect to some bending lines () set up in relation to a bending surface () similar to that of the tool provided for bending the part; d) Generating the solid model () of the bent part. The invention also relates to a computer program that when it is executed on a computer together with a CAD system it causes the execution of the method.

Computer assisted method for the advanced design of bent parts of composite material

The invention relates to a piece made of composite material with areas of different thickness manufactured from a stack of composite material fabrics comprising at least two adjacent areas () of different thickness and a transition area () between both configured with a single slope (), in which the stack is structured by: a first and a fourth section formed by at least two continuous fabrics () extending along the three mentioned areas (); a second section formed by one or more symmetrical and balanced fabric packets () ending in the transition area () placed among one or more continuous fabrics (); a third section formed by a symmetrical and balanced fabric packet () extending along the three mentioned areas () placed among one or more continuous fabrics ().

Piece made of composite material with areas of different thickness

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Madrid, Spain

Antonio De Julián Aguado