OPTOCOM
Optimal tooling system design for large composite parts
| Coordinatore | "FUNDACION PARA LA INVESTIGACION, DESARROLLO Y APLICACION DE MATERIALES COMPUESTOS"
Organization address
address: Avda Rita Levi Montalcini (Tecnogetafe) 29 contact info |
| Nazionalità Coordinatore | Spain [ES] |
| Totale costo | 287˙740 € |
| EC contributo | 215˙805 € |
| Programma | FP7-JTI
Specific Programme "Cooperation": Joint Technology Initiatives |
| Code Call | SP1-JTI-CS-2012-01 |
| Funding Scheme | JTI-CS |
| Anno di inizio | 2012 |
| Periodo (anno-mese-giorno) | 2012-12-01 - 2014-03-31 |
Partecipanti
| # | ||||
|---|---|---|---|---|
| 1 |
"FUNDACION PARA LA INVESTIGACION, DESARROLLO Y APLICACION DE MATERIALES COMPUESTOS"
Organization address
address: Avda Rita Levi Montalcini (Tecnogetafe) 29 contact info |
ES (Getafe) | coordinator | 215˙805.00 |
Mappa
Word cloud
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Obiettivo del progetto (Objective)
'The general objective of the project is to smartly handle the overall process of the composite integrated parts production reducing costs in two ways. First, by adequately simulating the spring back produced after the curing process and providing solutions in order to reduce the costs of reworking or assembly. Secondly, by simulating the thermal model of the set tooling/compositepart/vacuum bag and auxiliary parts under autoclave conditions to optimize the cure cycle temperatures distribution creating more uniformity in the composite part, lower residual stress, lower energy costs and better environmental friendliness. Given the large number of parts produced and their growth, the importance of the target is large. For that general purpose, the first specific objective of the OPTOCOM project is to carry out all the necessary steps to design and manufacture large tool for a composite complex structural part, typically a double curvature fuselage stiffened panel with co-cured stiffeners of about 2x1sqm. The stiffening elements shall be of both “Z” type and “Ω” type cross section. Requirements such as high accuracy and rigidity, typical autoclave conditions, CTE matching, durability, minimal weight, provisions for transport, handling and accessories integration for easy demoulding, shall be imposed Second, is to develop analytical and FEM models which adequately simulate the distortions and spring back occurring in the curing process. This requires to establish the correct hypothesis and to obtain real material performance behavior both along the curing process and when the composite is cured, in order to be introduced into the model. Third, is to set up FEM simulation models to assess the thermal behavior and temperature evolution of the set of elements that get in the autoclave in order to optimize the thermal ramps and maps in the composite part. Finally, an analysis of the design and manufacturing tooling costs to assess benefits and procedures is made'
Introduzione (Teaser)
Production of large, complex composite aircraft structures is a complicated process, much of which takes place in a large autoclave under extreme conditions. Scientists successfully addressed the need for improved efficiency and cost effectiveness.