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ATLLAS II

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Aero Thermodynamic Loads on Lightweight Advanced Structures II

ATLLAS II is a logical follow-up of a recently finalized FP6 project which has as objectives the identification and assessment of advanced light-weight and high-temperature resistant materials for high-speed vehicles up to Mach 6.... ver más

31/10/2015

MINISTERE DE L'ENS...

7M€

Presupuesto del proyecto: 7M€

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

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Financiación concedida El organismo FP7 notifico la concesión del proyecto el día 2015-10-31 No tenemos la información de la convocatoria

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11 Participantes

MINISTERE DE L'ENSEIGNEMENT...

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INCAS

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USTUTT

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ONERA

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 7M€

Fecha límite de participación Sin fecha límite de participación.

Descripción del proyecto ATLLAS II is a logical follow-up of a recently finalized FP6 project which has as objectives the identification and assessment of advanced light-weight and high-temperature resistant materials for high-speed vehicles up to Mach 6. The material requirements are first defined through an in-depth feasibility study of a Mach 5-6 vehicle. The consortium has now this capability at hand as they can rely on a first set of validated tools, material databases and valuable experience acquired during ATLLAS-I. Starting with a preliminary aero-thermal-structural high-speed vehicle design process, further multi-disciplinary optimization and testing will follow to result into a detailed layout of an independently European defined and assessed high-speed vehicle. Special attention will be given to alleviate sonic boom and emissions at high altitudes. Throughout the design process, the aero-thermal loads will define the requirements for the proposed materials and cooling techniques needed for both the airframe and propulsion components. The former will focus on sharp leading edges, intakes and skin materials each coping with different external aero-thermal loads. The latter will be exposed to internal combustion driven loads. Both metallic (Titanium Matrix Composites and Ni-based Hollow Sphere Stackings) and non-metallic materials (Ceramic Matrix Composites and Ultra High Temperature Composites) will be evaluated. Combined aero-thermal-structural experiments will test various materials as specimens and realistic shapes at extreme conditions representative for high flight Mach numbers. Both static and cyclic tests at low and high temperatures are planned including the evaluation of their durability in terms of long duration exposure to the harsh flight conditions. The materials assigned to dedicated engine components will be exposed to realistic combustion environments. These will be combined with passive or active cooling technologies developed in ATLLAS-I.

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