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SWING SIGNED

Sonaca WING flap process Development

Total Cost €

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EC-Contrib. €

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Partnership

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Project "SWING" data sheet

The following table provides information about the project.

Coordinator
CENTRE TECHNIQUE DES INDUSTRIES MECANIQUES 

Organization address
address: AVENUE FELIX LOUAT 52
city: SENLIS CEDEX
postcode: 60304
website: http://www.cetim.fr

contact info
title: n.a.
name: n.a.
surname: n.a.
function: n.a.
email: n.a.
telephone: n.a.
fax: n.a.

 Coordinator Country France [FR]
 Total cost 1˙170˙467 €
 EC max contribution 941˙535 € (80%)
 Programme 1. H2020-EU.3.4.5.1. (IADP Large Passenger Aircraft)
 Code Call H2020-CS2-CFP09-2018-02
 Funding Scheme CS2-IA
 Starting year 2019
 Duration (year-month-day) from 2019-10-01   to  2022-09-30

 Partnership

Take a look of project's partnership.

# participants  country  role  EC contrib. [€] 
1    CENTRE TECHNIQUE DES INDUSTRIES MECANIQUES FR (SENLIS CEDEX) coordinator 441˙688.00
2    LOIRETECH HOLDING SAS FR (MAUVES SUR LOIRE) participant 271˙367.00
3    AFPT GMBH DE (DORTH) participant 228˙480.00

Map

 Project objective

SWING project aims to develop a material/process/design solution for a shielding flap for hybrid laminar flow control on wings of large passenger aircraft. The project target is to develop an In Situ Consolidation thermoplastic process to outperform existing process in terms of structural and economic performance. Indeed, Hybrid Laminar Flow Concept will lead to more complexity in the structure of the wings and their accessories, and therefore an efficient process to manufacture flaps are needed to enable implementation of such system with an acceptable cost.

From a technical point of view, several challenges stay on the development road : • Selection of a thermoplastic composite pre-impregnated tape that fulfil both the design, the process and the economic requirement. • Process parameter control strategy to guarantee in situ consolidation of composite with the nominal performance of the material for the targeted complex geometry • Efficiency of tape laying to match with the economic equation. Efficiency includes the maximum laying speed and the gestion of start and stop (loss of time, scraps…) • Assembly solution to create a closed wing section that include the ribs and possibly other reinforcement (for mechanical fastening, at trailing edge….).

SWING aims at overcoming these challenges with significative achievement to allow the integration of the thermoplastic flap in demonstrator wings of hybrid laminar flow control. The Krueger flap develop inside the project will impact the CO2 emissions of the Large Passenger Aircraft demonstrator through two ways : by reducing the weight of the flap thus the fuel consumption and by allowing aerodynamics optimization.

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The information about "SWING" are provided by the European Opendata Portal: CORDIS opendata.

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