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European Aeronautic Defence and Square Company Eads France

Composite Atlantic Limited

Carbone Forge

European Aeronautic Defence and Space Company Eads France

Airbus Group Sas

Composites Atlantic Limited

Claude Baril

Maurice Guitton

Frédérick Cavaliere

Fredérick Cavallere

Olivier Blanc

Kevin P Steck

Scott Saunders

Michael Davison

Mike Myra

Troy Brake

Vincent Duqueine

Paul Bruhm

Severine Guitton

A connecting rod is composed of two or more assembled shells made of a composite, open over the entire length of the connecting rod. The shells incorporate clevis joints for introducing stress at each of their ends. The shells are produced separately then assembled together to form a sealed section. Each shell is made from a material preimpregnated with long fibres. The production of each shell is simplified due to the overall shape of the shell as a simple curve, thus a shell may be produced industrially, for example, by thermoforming a flat composite preform. The two shells are assembled by simultaneous polymerization of the shells, by bonding, by welding, by riveting or any other assembly process or combination of assembly processes that are compatible with one another. The structural composite connecting rod obtained has very good mechanical properties, especially in compression, with a simple and economic production process.

Structural connecting rod made of a composite and process for producing such a connecting rod

A wrinkle control process for manufacturing a closed cross-sectional, composite laminate structure on a male tool cured under temperature and pressure. The process includes the step of creating a plurality of filled or unfilled depressions at strategic locations in the laminate prior to curing. The depressions are created by depression forming elements that have a predetermined size designed to create a depression in under plies, alone or combined with intensification techniques. The depressions may be left unfilled or be partially or completely filled. Depression forming elements are removed after cure or remain part of the structure. The number of elements being determined by the following equation: N=(OPL&#x2212;OPC)&#xf7;(Li&#x2212;Lj), where OPL is the outside perimeter of the composite structure after lay-up and prior to curing, OPC is the outside perimeter of the composite structure after lay-up and after curing, Li is the linear length of the composite segment formed by a depression forming element and Lj is the theoretical linear length of the corresponding composite segment without a depression.

Process for reducing wrinkles in composite laminated structures

The invention relates to a method for making a thermoplastic composite part by molding. The method includes making several portions of the part according to a molding method, the molding method including placing, in a mold, a composite material containing fibers embedded in a thermoplastic matrix, while arranging the material so that the fibers contained therein are oriented along one or more preferred directions; submitting the mold to particular pressure and temperature conditions, knowing that for each of the different portions the fibers may be of different natures and dimensions, and may be oriented in different directions, while the thermoplastic matrix and that of the material used for making the first portion are identical or compatible; and assembling the different portions obtained, placing them in a mold, and submitting the latter to particular pressure and temperature conditions.

Method for making a thermoplastic composite part by molding

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Laval, Canada

Claude Baril