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2.发明授权AILE D'AÉRONEF AVEC UN DISPOSITIF DE PROTECTION D'UNE STRUCTURE DE LONGERON AVANT D'UN CAISSON CENTRAL DE LADITE AILE ET D'AU MOINS UN ÉQUIPEMENT SITUÉ DANS LADITE AILE 有权飞机翼带有一个装置，用于保护一个中央的所述侧翼以及至少一个设备位于同一个设备之前的长结构
公开(公告)号：EP2877396B1
公开(公告)日：2018-05-09
申请号：EP13739755.0
申请日：2013-06-20
发明人： DAZET, Francis
CPC分类号： B64C3/28 , B64D45/00 , B64D2045/0095
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3.发明公开DISPOSITIF DE PROTECTION D'UNE STRUCTURE DE LONGERON AVANT D'UN CAISSON CENTRAL D'AILE D'AÉRONEF ET D'AU MOINS UN ÉQUIPEMENT SITUÉ DANS LADITE AILE 有权设备技术的平面翼中央外壳前HOLM结构在这WING保护和至少一部分设备的
公开(公告)号：EP2877396A1
公开(公告)日：2015-06-03
申请号：EP13739755.0
申请日：2013-06-20
发明人： DAZET, Francis
CPC分类号： B64C3/28 , B64D45/00 , B64D2045/0095
摘要： A device for protecting a front spar structure (12) of a central casing (13) of an aircraft wing and equipment (14) located in said wing. The device comprises a shielding surface (222) extending along the front of a front spar of a central casing (13), from the intersection surface (3) between the wing and the fuselage delimited by the wing root, transversally to this intersection surface (3), up to a first rib of the central casing (13) partially surrounding the equipment (14). The device thus protects the equipment (14) located in the zone between the wing root and the first rib of the central casing (13) of the wing.
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公开(公告)号：EP2476162A1
公开(公告)日：2012-07-18
申请号：EP10770551.9
申请日：2010-09-10
发明人： DAZET, Francis
摘要： The invention relates to a radome (1) for an aircraft and, specifically, to a device for connecting said radome to the structure of said aircraft. The radome that is the subject matter of the invention includes a plurality of locking units suitable for engaging the opposing surfaces of the fuselage (10) of the aircraft and the radome (1), each unit comprising: a locking means (20) suitable for exerting a tractive force on the surface of the fuselage, substantially normal to the latter, by means of the attachment means; a centring means suitable for passing on the shearing forces substantially tangential to the opposing surfaces of the fuselage and the radome; the locking means (20) being placed so as to be located inside the resulting stress cone on the centring means in order to minimise the bending strain generated by assembly in the radome (1).
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