Airbus Operations Sl

Airbus Espana, S.l.

Jose Sanchez Gomez

Rafael Avila Dominguez

Enrique Redondo Vara

Angel Postigo Rodriguez

Cesar Bautista De La Llave

Bernardo Lopez Romano

Enric Vila Papell

Ana Rodriguez Bellido

Rebeca Anguiano Zarranz

Enrique Garate Fel

Rafael Ruiseco Salgado

Juan Ignacio Forcen Carvalho

César Serrano Velaz

Hector Alonso Pintado

Rafael ÁVila Dominguez

Héctor Alonso Pintado

A system for out of autoclave bonded repairs which including a fixing structure () to the composite area to be repaired, including a frame () and fixing parts () attached to the frame (), a movable structure () able to be attached either to the fixing structure () or to the patch manufacturing table (), which includes three shafts () and three engines () configured to be able to move the tooling support in the three axes X, Y and Z, and a tooling support of either scanning tool (), milling tool (), patch cutting tool () or composite patch handle tool (), and a patch manufacturing structure ().

System for out of autoclave bonded repairs

A method for obtaining a composite piece of n plies, at least one ply having a fiber volume greater than 58% in weight, the method comprising the steps of laying uncured prepreg plies and performing ultrasound compaction over each laid uncured laminate ply, wherein at least one of the uncured laminate plies has a fiber volume greater than 58% in weight. Finally, the composite laminate is cured. The step of performing ultrasound compaction comprises applying an ultrasonic compactor over each laid laminate ply.

Method for obtaining a composite laminate

The invention relates to an aircraft with a protection shield for the rear composite material, fuselage) for conducting tail impact tests, in addition to a tail absorber, the shield () being formed by a plurality of pieces () joined to supports () fixed to the rear fuselage () behind the tail absorber (), said pieces () having a laminar structure with an outer steel sheet (), an inner composite sheet () and an intermediate high resistance silicon sheet ().

Aircraft with a rear fuselage protection shield

The present invention relates to a process for manufacturing composite structures formed by two subcomponents of the same material, characterized in that it comprises the following steps: providing a first subcomponent (), particularly a skin; providing a tool () made of a composite and precured for the manufacture of the second subcomponent (), particularly a stiffener; positioning said tool () on said first subcomponent (); applying preimpregnated composite () on said tool () so as to form the second subcomponent (); consolidating the composite structure by means of a process of curing the assembly resulting from the previous steps under suitable pressure and/or temperature conditions.

Process of manufacturing composite structures with embedded precured tools

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Madrid, Spain

Jose Sanchez Gomez