CLARET

Control and Alleviation of Loads in Advanced Regional Turbo Fan Configurations

Coordinatore	UNIVERSITY OF BRISTOL    more  Organization address address: TYNDALL AVENUE SENATE HOUSE city: BRISTOL postcode: BS8 1TH contact info Titolo: Mrs. Nome: Julie Cognome: Coombs Email: send email Telefono: +44 117 3315535
Nazionalità Coordinatore	United Kingdom [UK]
Totale costo	450˙379 €
EC contributo	337˙783 €
Programma	FP7-JTI Specific Programme "Cooperation": Joint Technology Initiatives
Code Call	SP1-JTI-CS-2010-05
Funding Scheme	JTI-CS
Anno di inizio	2012
Periodo (anno-mese-giorno)	2012-01-28   -   2013-09-27

 Partecipanti

#	participant	country	role	EC contrib. [€]
1	UNIVERSITY OF BRISTOL  Organization address address: TYNDALL AVENUE SENATE HOUSE city: BRISTOL postcode: BS8 1TH contact info Titolo: Mrs. Nome: Julie Cognome: Coombs Email: send email Telefono: +44 117 3315535	UK (BRISTOL)	coordinator	111˙663.00
2	AIRCRAFT RESEARCH ASSOCIATION LIMITED  Organization address address: Manton Lane city: BEDFORD postcode: MK41 7PF contact info Titolo: Mr. Nome: Kieron Cognome: Rentle Email: send email Telefono: 441234000000	UK (BEDFORD)	participant	113˙187.00
3	Stirling Dynamics Ltd  Organization address address: REGENT STREET 26 CLIFTON city: Bristol postcode: BS8 4HG contact info Titolo: Dr. Nome: Simon Cognome: Hancock Email: send email Telefono: +44 117 9152 524 Fax: +44 117 923 8636	UK (Bristol)	participant	112˙933.50
4	THE UNIVERSITY OF LIVERPOOL  Organization address address: Brownlow Hill, Foundation Building 765 city: LIVERPOOL postcode: L69 7ZX contact info Titolo: Ms. Nome: Cherie Cognome: Judge Email: send email Telefono: 441518000000 Fax: 441518000000	UK (LIVERPOOL)	participant	0.00

Mappa

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 Obiettivo del progetto (Objective)

'A novel adaptive winglet concept will be developed to enable controlled cant angle orientation and twist throughout the flight envelope whilst also providing a passive gust loads alleviation capability. A CFD based aerodynamic design of the device applied on a baseline Turbo-Fan Aircraft configuration model will be undertaken, followed by a preliminary lay-out definition of the structure and actuation system required for the device. Detailed parametric studies will then be performed to investigate the performance of the device in terms of both drag and loads alleviation capabilities on its own, and also in combination with conventional control actuators, and both compared to the baseline configuration.'

Introduzione (Teaser)

Despite major advances in engine design, aircraft configurations have remained relatively the same over the last 50 years. Now, a novel morphing wing concept has demonstrated potential to reduce drag and thus fuel consumption and emissions.