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1.发明申请公开(公告)号：US20200072161A1
公开(公告)日：2020-03-05
申请号：US16552079
申请日：2019-08-27
发明人： Eric BOUCHET , Laurent CAZEAUX , Thierry GACHES , Morad KASSEM , Claire MAFFRE
摘要： A structure which absorbs low-frequency sound comprising a perforated skin, a box having two lateral walls in the shape of a strip, that delimit between them an opening, and a bottom opposite the opening connecting the two lateral walls, the lateral walls becoming closer together with increasing distance from the opening to the bottom. The box is attached to the skin at the opening. Each lateral wall extends width-wise between the opening and the bottom. Each box has two tongues, each tongue being strip shaped, extending lengthwise over an entire box length, and width-wise between the opening and the bottom of the box. Each tongue has a first end attached along an edge of the opening and a second, free end which extends towards the bottom, becoming closer to the second end of the other tongue, where each tongue has an arcuate shape along its length.
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公开(公告)号：US20190144125A1
公开(公告)日：2019-05-16
申请号：US16173190
申请日：2018-10-29
发明人： Eric BOUCHET , Jérôme COLMAGRO , Michel GARCIA
摘要： An aircraft which comprises a fuselage and at least one propulsion assembly linked to the fuselage by at least two connecting rods positioned at least partially in an inner zone of the air inlet of the nacelle of the propulsion assembly. Thus, the connecting rods do not interfere with the secondary flow flowing inside the nacelle and do not affect the aerodynamic performance levels of the propulsion assembly.
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公开(公告)号：US20180148186A1
公开(公告)日：2018-05-31
申请号：US15823890
申请日：2017-11-28
CPC分类号： B64D27/26 , B64D27/20 , B64D2027/268
摘要： To allow the attachment of an engine of the “Open Rotor Puller” type to the rigid structure of an attachment pylon, an attachment structure comprises a first attachment structure shifted forwards with respect to the center of gravity of the engine and connected to the rigid structure through a pyramid, a second attachment structure laid out at the rear with respect to the first attachment structure and extending in a plane of a first stringer of the rigid structure, and a third attachment structure laid out at the rear with respect to the second attachment structure. The second attachment structure comprises two engine attachments for recovering the moment along the axis of the engine, laid out on either side of a horizontal symmetry plane of the engine.
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4.发明申请公开(公告)号：US20180009543A1
公开(公告)日：2018-01-11
申请号：US15641771
申请日：2017-07-05
IPC分类号： B64D27/26
CPC分类号： B64D27/26 , B64D2027/266 , F16B37/047
摘要： An aircraft engine mount which comprises first and second parts connected by connecting elements and wherein one of the two connected parts comprises at least one transverse hole opening onto an access face of the part and into which there open at least two passage holes each intended to house a threaded shank of one of the connecting elements. The engine mount comprises a transverse nut which comprises at least two bodies joined together each having a tapped hole configured to engage with one of the threaded shanks.
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公开(公告)号：US20190152616A1
公开(公告)日：2019-05-23
申请号：US16197726
申请日：2018-11-21
发明人： Olivier PAUTIS , Eric BOUCHET , Olivier BARBARA
IPC分类号： B64D27/26
摘要： To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.
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公开(公告)号：US20190100324A1
公开(公告)日：2019-04-04
申请号：US16150991
申请日：2018-10-03
发明人： Frederic JOURNADE , Eric BOUCHET , Olivier BARBARA , Pascal POME
摘要： An aircraft engine assembly has a front engine mount connecting an engine and a primary structure of a pylon comprising at least one front rod having at least three front link points. A first front link point is configured to connect the front rod and the front end of the primary structure. A second front link point is configured to connect the front rod and the core of the engine. A third front link point is configured to connect the front rod and the engine core and is offset relative to the second front link point in a horizontal transverse direction. The first front link point of the front engine mount is separated from the rotation axis of the engine by a distance greater than an exterior radius of the rear casing of the core of the engine at the rear link point of the rear engine mount.
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7.发明申请公开(公告)号：US20180170563A1
公开(公告)日：2018-06-21
申请号：US15845330
申请日：2017-12-18
发明人： Eric BOUCHET , Esteban MARTINO-GONZALEZ , Jerome COLMAGRO , Fernando INIESTA LOZANO , Julien MOULIS , Antoine ABELE
CPC分类号： B64D27/20 , B64C1/061 , B64C1/16 , B64D27/14 , B64D27/26 , B64D2027/268 , B64D2033/0286 , Y02T50/44
摘要： In order to reduce the congestion of the attachment means for aircraft engines in a secondary vein, a first fuselage frame has two side portions for supporting the engine, each associated with one of the two partly buried side engines, these portions being curved inwards so as to surround and follow the profile of the outer shroud of an intermediate case. The side portion is attached on this shroud through first and second attachment arrangements spaced apart from each other circumferentially, these arrangements being configured in order to allow absorption of the forces related to the torque along a longitudinal direction of the engine.
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公开(公告)号：US20160152315A1
公开(公告)日：2016-06-02
申请号：US14952376
申请日：2015-11-25
发明人： Esteban MARTINO GONZALEZ , Diego FOLCH CORTES , Pablo GOYA ABAURREA , Angel PASCUAL FUERTES , Sandra LINARES MENDOZA , Julien GUILLEMAUT , Eric BOUCHET , Jerome COLMAGRO , Jonathan BLANC
摘要： An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece.
摘要翻译： 一种包括适于位于机身周边内的中心元件的飞行器机身框架，以及从作为提升表面的纵向结构的一部分的中心元件的两侧突出到机身的周边外侧的两个侧向延伸部。 中心元件和两个横向延伸部被配置为一体的部件。
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