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LAPCAT-II

Financiado

Cerrado

Long Term Advanced Propulsion Concepts and Technologies II

Lacpat II is a logical follow-up of the previous EC-project which has as objective to reduce antipodal flights to less than 2 to 4 hours. Among the several studied vehicles, only two novel aircraft for a Mach 5 and 8 flight are r... ver más

31/12/2013

MINISTERE DE L'ENS...

10M€

Presupuesto del proyecto: 10M€

Líder del proyecto

MINISTERE DE L'ENSEIGNEMENT SUPERIEUR ET DE... No se ha especificado una descripción o un objeto social para esta compañía.

Fecha límite participación Sin fecha límite de participación.

Ver 13 Participantes

Financiación concedida El organismo FP7 notifico la concesión del proyecto el día 2013-12-31 No tenemos la información de la convocatoria

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Información adicional privada

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13 Participantes

MINISTERE DE L'ENSEIGNEMENT...

0.00€ | Lider

UOXF

N.D. | Participante

USTUTT

N.D. | Participante

UNIROMA1

N.D. | Participante

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Líder del proyecto

MINISTERE DE L'ENSEIGNEMENT SUPERIEUR ET DE... No se ha especificado una descripción o un objeto social para esta compañía.

Presupuesto del proyecto 10M€

Fecha límite de participación Sin fecha límite de participación.

Descripción del proyecto Lacpat II is a logical follow-up of the previous EC-project which has as objective to reduce antipodal flights to less than 2 to 4 hours. Among the several studied vehicles, only two novel aircraft for a Mach 5 and 8 flight are retained in the present proposal. Starting from the available Mach 5 vehicle and its related precooled turboramjet, assumed performance figures of different components will now be assessed in more detail, i.e.: Intake design and performance Environment friendly design of combustor Nozzle design and performance Structural analysis Once available, the vehicle performance will be re-assessed. The outcome will allow the definition of a detailed development roadmap. Though the cruise flight of the Mach 8 vehicle based on a scramjet seemed feasible, the acceleration based on an ejector rocket was not. Integrated design of airframe and engine throughout the whole trajectory is the prime focus now to guarantee a successful design. A turbo-based engine will replace the former ejector rocket to assure better performance and fuel consumption during acceleration. Important points to be addressed to realize these goals are: - proper development and validation of engine-airframe integration tools and methodology - high-speed airbreathing cycle analysis - off- and on-design behaviour of engine and airframe - dedicated experiments to evaluate the design in various operation points Validated tool development should give solid confidence to propose a fully integrated vehicle to comply with the mission goals. Once defined, a roadmap will be defined with a step-wise approach to future development. Finally, for vehicles flying at high speeds and high altitudes, limited know-how is available on the environmental impact. The influence of NOx and H2O onto the ozone layer and the formation of contrails with its direct and indirect effects will be investigated for both vehicles.

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