A method for manufacturing an aircraft leading edge panel, includes a step of overmoulding a coating onto a sheet positioned in a cavity of a mould, which cavity is delimited by a shaping surface which exhibits an optimized surface finish. The coating includes, after the overmoulding step, an exterior face which corresponds to the exterior face of the panel that is to be obtained and which exhibits an optimized surface finish conferred by the shaping surface of the mould. A panel may be obtained using this method and a leading edge includes at least one such panel. Because of the optimized surface finish of the exterior surface thereof, the panel contributes to extending the regions of laminar flow.
PROCEDE DE FABRICATION D'UN PANNEAU D'UN BORD D'ATTAQUE D'AERONEF PERMETTANT D'OBTENIR UN ECOULEMENT LAMINAIRE ETENDU, BORD D'ATTAQUE COMPRENANT AU MOINS UN PANNEAU OBTENU A PARTIR DUDIT PROCEDE
METHOD FOR MANUFACTURING A PANEL OF AN AIRCRAFT LEADING EDGE FOR PROVIDING AN EXTENDED LAMINAR FLOW, LEADING EDGE COMPRISING AT LEAST ONE PANEL OBTAINED BY THE METHOD
HERSTELLUNGSVERFAHREN EINES PANEELS EINER FLUGZEUGVORDERKANTE, DAS EINE AUSGEDEHNTE LAMINARE STRÖMUNG ERMÖGLICHT, FLUGZEUGVORDERKANTE, DIE MINDESTENS EIN NACH DIESEM VERFAHREN HERGESTELLTES PANEEL UMFASST
2020-04-08
Patent
Electronic Resource
French
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