Airbus Operations Sl

Airbus Espana, S.l.

Jose Cuenca Rincon

Gabriel Cruzado Parla

Augusto Perez Pastor

Aquilino Garcia Garcia

Jorge Juan Galiana Blanco

Alberto Martinez Cerezo

Maria Mora Medias

Francisco De Paula Escobar Benavides

Daniel Claret Viros

Fernando Munoz Ajenjo

Juan Salamero Laorden

Ana Teresa Rodriguez-Bellido

María Mora Medias

The present disclosure refers to a method for manufacturing carbon fiber panels stiffened with omega stringers for the construction of aircraft structures, such as fuselage sections, wing panels, etc. One tubular pressure member is provided for each omega stringer of the structure to be manufactured, wherein the tubular pressure member is configured with the shape of the omega stringer. Each tubular pressure member is enclosed between the omega stringer and part of the laminate, and autoclave pressure is applied to the interior of the tubular pressure member, so that the tubular pressure member is used to consolidate the omega stringers and/or part of the laminate from the interior of these two elements, while these two elements are being co-cured or co-bonded in an autoclave. Imperfections on those internal surfaces such as resin wrinkles of the structure are reduced.

Method for manufacturing carbon fiber panels stiffened with omega stringers

A system for curing polymer matrix composite parts out of autoclave in manufacturing and repairing processes including: (i) an inner vacuum bag () placed over the lay-up to be cured located over a working area () with the edges of the inner vacuum bag () joined to the working area by first sealing elements (); (ii) a Perforated bulkhead () located over the inner vacuum bag (), (iii) an Outer vacuum bag () over a perforated bulkhead () and over the edges of the inner vacuum bag with the edges of the outer vacuum bag () joined to the working area () by second sealing elements (), (iv) a vacuum device () and (v) a heating source ().

System and method for curing polymer matrix composite parts in manufacturing and repairing processes

An apparatus for manufacturing composite stringers from a composite laminate comprising a male mold, a main caul plate, two fixed female mold halves, two secondary movable caul plates and a retention device. The main caul plate is located below the male mold, the female mold halves are located at both sides of the main caul plate and the secondary movable caul plates, each of them located respectively over each one of the two female mold halves. The male mold, the main caul plate, the two female mold halves and the two secondary caul plates are non-developable surfaces. The retention device keeps each secondary movable caul plate at a predetermined distance of its respective female mold half.

Device and method of manufacturing omega stringers

A composite skin () with swept angle and dihedral for an aircraft mid-box lifting surface having a left side (), a right side () and a central transition area () where both sides meet, that is designed and manufactured as a single part from left tip to right tip following a common ply structure for the whole part defined in relation to a single orientation rosette (). The invention also refers to a composite aircraft mid-box lifting surface including an upper and lower panel with said composite skin ().

Integrated composite skin for aircraft mid-box lifting surfaces

Growing community of inventors

Madrid, Spain

Jose Cuenca Rincon