HERRB

Helicopter Electric Regenerative Rotor Brake

Coordinatore	UNIVERSITY OF BRISTOL    more  Organization address address: TYNDALL AVENUE SENATE HOUSE city: BRISTOL postcode: BS8 1TH contact info Titolo: Dr. Nome: David Cognome: Drury Email: send email Telefono: +44 117 9545390
Nazionalità Coordinatore	United Kingdom [UK]
Totale costo	698˙331 €
EC contributo	523˙745 €
Programma	FP7-JTI Specific Programme "Cooperation": Joint Technology Initiatives
Code Call	SP1-JTI-CS-2011-01
Funding Scheme	JTI-CS
Anno di inizio	2011
Periodo (anno-mese-giorno)	2011-10-01   -   2015-03-31

 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: Dr. Nome: David Cognome: Drury Email: send email Telefono: +44 117 9545390	UK (BRISTOL)	coordinator	382˙990.00
2	Motor Design Ltd  Organization address address: Scotland Street 4 city: Ellesmere postcode: SY12 OEG contact info Titolo: Dr. Nome: David Cognome: Staton Email: send email Telefono: +44 1691 623305	UK (Ellesmere)	participant	72˙093.00
3	ADAPTED SOLUTIONS GmbH  Organization address address: Annaberger Strasse 240 city: CHEMNITZ postcode: D-09125 contact info Titolo: Dr. Nome: Thomas Cognome: Barucki Email: send email Telefono: 493715000000 Fax: 493715000000	DE (CHEMNITZ)	participant	68˙662.00

Mappa

 Word cloud

Esplora la "nuvola delle parole (Word Cloud) per avere un'idea di massima del progetto.

 Obiettivo del progetto (Objective)

'The proposal outlines a design process coupled with a full evaluation and testing phase for a fully electric replacement for the current mechanical-hydraulic rotor brake system that exists on most large rotorcraft in production currently allow regenerative capture of the inertial energy stored in the aircraft drivetrain during deceleration.

The concept offers further potential alongside other similar projects to downsize and in the long term even remove the hydraulic circuit that exists on aircraft resulting such that the benefits of electrical systems becomes significant. Furthermore, once on the aircraft, installation of the equipment provides potential for several performance and system benefits as there would exist coupled to the rotor a bi-directional power flow controller within an independent energy store. Possible systems would include fast rotor start, auto-gyro assist for safe landing in the event of primary power failure and extra power on-board electrical power generation for redundancy during flight.'