公开(公告)号：US20060060697A1

公开(公告)日：2006-03-23

申请号：US10954192

申请日：2004-10-01

申请人： Jacques Beaufort

发明人： Jacques Beaufort

IPC分类号： B64D33/02

CPC分类号： B64D29/06

摘要： The invention relates to a device (131) for assembly of a shroud (26) arranged between an air intake (22) and a pylon (2) fixed to the engine (4), the device comprising: stressed flexible means (130) provided with a first end (130a) and a second end (130b); first connection means connected to the air intake and to the end (130a); and second connection means connected to the shroud and to the end (130b). According to the invention, the second connection means comprise a primary assembly (140) fixed to the shroud and a secondary assembly (142) fixed to the second end (130b), and the primary and secondary assemblies (140,142) are connected to each other through a pivot connection (144).

摘要翻译： 本发明涉及一种用于组装布置在固定到发动机（4）的进气口（22）和塔架（2）之间的护罩（26）的装置（131），该装置包括

公开(公告)号：US20090200419A1

公开(公告)日：2009-08-13

申请号：US12304772

申请日：2007-07-09

申请人： Stéphane Levert ,  Jacques Beaufort

发明人： Stéphane Levert ,  Jacques Beaufort

IPC分类号： B64D27/26

CPC分类号： B64D27/26 ,  B64C27/26 ,  B64D2027/268

摘要： A mounting structure for an aircraft engine including a rigid structure and a mechanism to mount the engine on the rigid structure. The mounting mechanism includes a thrust load device including two side thrust links each including an aft end mounted on an evener bar of the device, via a mechanical connection. Each connection is formed by a lug provided on the evener bar and passing through an orifice made in the aft end, the lug being arranged so as to extend substantially laterally relative to the mounting structure.

摘要翻译： 一种用于飞机发动机的安装结构，包括刚性结构和将发动机安装在刚性结构上的机构。 安装机构包括推力负载装置，该推力负载装置包括两个侧向推力连接件，每个侧推力连接件通过机械连接件包括安装在装置的再生杆上的后端。 每个连接由设置在延长杆上并通过在后端制成的孔的凸耳形成，凸耳布置成相对于安装结构基本上横向延伸。

公开(公告)号：US20090200418A1

公开(公告)日：2009-08-13

申请号：US12298328

申请日：2007-05-14

申请人： Jacques Beaufort

发明人： Jacques Beaufort

IPC分类号： B64D27/00

CPC分类号： B64D27/26 ,  B64D2027/264 ,  B64D2027/268

摘要： A device for attaching an aircraft engine including a rigid structure forming a structure box, and a device for absorbing thrust loads including a main fitting fixedly mounted on one of the spars forming the structure box, by a fixing mechanism. The fixing mechanism includes a fixing peg mounted on the spar and including a main portion located on the outside relatively to the box, the fitting being crossed by the portion of the peg and pressed against the spar by a bell-shaped supporting washer surrounding the main portion and stressed by a screw crossing it, the latter being screwed into a barrel nut housed in a bore made within the main portion.

摘要翻译： 一种用于安装包括形成结构箱的刚性结构的飞行器发动机的装置，以及用于吸收推力载荷的装置，包括通过固定机构固定地安装在形成结构箱的一个翼梁上的主配件。 固定机构包括安装在翼梁上的固定栓，并且包括位于相对于箱体的外侧的主要部分，该配件由该钉的一部分穿过，并通过围绕主体的钟形支撑垫圈抵靠翼梁 部分并且被穿过螺钉的螺钉应力，后者被拧入容纳在主要部分内的孔中的桶形螺母中。

公开(公告)号：US20080169378A1

公开(公告)日：2008-07-17

申请号：US11817837

申请日：2006-03-15

申请人： Jacques Beaufort ,  Jean-Francois Dumont

发明人： Jacques Beaufort ,  Jean-Francois Dumont

IPC分类号： B64D27/12 ,  B64D27/18

CPC分类号： B64D27/26 ,  B64D2027/268 ,  Y02T50/44

摘要： An engine attachment for an assembly system configured to be mounted between a rigid structure of an attachment strut of an aircraft engine and an engine. The attachment includes a main body, a rudder bar on an articulated mounting on the main body by a hinge pin, and two thrust absorption rods each with one end connected to the rudder bar. The main body includes a first main brace and a second main brace superimposed on the first brace. The hinge pin is formed by a first portion and a second portion, wherein the first portion is made in one piece with the first brace and the second portion is made in one piece with the second brace. Furthermore, the braces define a stop limit surface configured to limit rotation of the rudder bar.

摘要翻译： 一种用于组装系统的发动机附件，其构造成安装在飞行器发动机的附件支柱的刚性结构和发动机之间。 附件包括主体，通过铰链销在主体上的铰接安装件上的舵杆和两个推力吸收杆，每个推杆吸收杆的一端连接到舵杆。 主体包括叠置在第一支架上的第一主支架和第二主支架。 铰链销由第一部分和第二部分形成，其中第一部分与第一支架制成一体，并且第二部分与第二支架一体制成。 此外，支架限定了限制舵杆旋转的限位表面。

公开(公告)号：US08336812B2

公开(公告)日：2012-12-25

申请号：US11817837

申请日：2006-03-15

申请人： Jacques Beaufort ,  Jean-Francois Dumont

发明人： Jacques Beaufort ,  Jean-Francois Dumont

IPC分类号： B64D27/26 ,  F02C7/20

CPC分类号： B64D27/26 ,  B64D2027/268 ,  Y02T50/44

摘要： An engine attachment for an assembly system configured to be mounted between a rigid structure of an attachment strut of an aircraft engine and an engine. The attachment includes a main body, a rudder bar on an articulated mounting on the main body by a hinge pin, and two thrust absorption rods each with one end connected to the rudder bar. The main body includes a first main brace and a second main brace superimposed on the first brace. The hinge pin is formed by a first portion and a second portion, wherein the first portion is made in one piece with the first brace and the second portion is made in one piece with the second brace. Furthermore, the braces define a stop limit surface configured to limit rotation of the rudder bar.

摘要翻译： 一种用于组装系统的发动机附件，其构造成安装在飞行器发动机的附件支柱的刚性结构和发动机之间。 附件包括主体，通过铰链销在主体上的铰接安装件上的舵杆和两个推力吸收杆，每个推杆吸收杆的一端连接到舵杆。 主体包括叠置在第一支架上的第一主支架和第二主支架。 铰链销由第一部分和第二部分形成，其中第一部分与第一支架制成一体，并且第二部分与第二支架一体制成。 此外，支架限定了限制舵杆旋转的限位表面。

公开(公告)号：US08186618B2

公开(公告)日：2012-05-29

申请号：US12298328

申请日：2007-05-14

申请人： Jacques Beaufort

发明人： Jacques Beaufort

IPC分类号： B64D27/26

CPC分类号： B64D27/26 ,  B64D2027/264 ,  B64D2027/268

摘要： A device for attaching an aircraft engine including a rigid structure forming a structure box, and a device for absorbing thrust loads including a main fitting fixedly mounted on one of the spars forming the structure box, by a fixing mechanism. The fixing mechanism includes a fixing peg mounted on the spar and including a main portion located on the outside relatively to the box, the fitting being crossed by the portion of the peg and pressed against the spar by a bell-shaped supporting washer surrounding the main portion and stressed by a screw crossing it, the latter being screwed into a barrel nut housed in a bore made within the main portion.

摘要翻译： 一种用于安装包括形成结构箱的刚性结构的飞行器发动机的装置，以及用于吸收推力载荷的装置，包括通过固定机构固定地安装在形成结构箱的一个翼梁上的主配件。 固定机构包括安装在翼梁上的固定栓，并且包括位于相对于箱体的外侧的主要部分，该配件由该钉的一部分穿过，并通过围绕主体的钟形支撑垫圈抵靠翼梁 部分并且被穿过螺钉的螺钉应力，后者被拧入容纳在主要部分内的孔中的桶形螺母中。

公开(公告)号：US07959107B2

公开(公告)日：2011-06-14

申请号：US11765065

申请日：2007-06-19

申请人： Jacques Beaufort

发明人： Jacques Beaufort

IPC分类号： B64C1/14

CPC分类号： B64D29/06 ,  E05D3/022 ,  E05Y2900/502 ,  Y10T16/522

摘要： A hinge device of a nacelle cowling of an aircraft engine on a supporting structure is disclosed. The hinge device includes two fittings and a link rod connected thereto and mounted on the fitting by an end connection. The link rod is further mounted on the fitting by an intermediate connection including a pivot pin slidably housed in a hole, and the end connection includes a guide pin slidably housed in a guide ramp. The connections are designed so as to create, upon rotation of the link rod about the pin, a relative movement of the axis in the ramp, simultaneously causing a relative movement of the pin in the hole.

摘要翻译： 公开了一种在支撑结构上的飞机发动机的机舱罩的铰链装置。 铰链装置包括两个配件和连接到其上的连杆，并通过端部连接安装在配件上。 连杆通过包括可滑动地容纳在孔中的枢轴销的中间连接件进一步安装在配件上，并且端连接件包括可滑动地容纳在引导斜坡中的引导销。 连接件被设计成在链条围绕销旋转时产生轴在斜面中的相对运动，同时引起销在孔中的相对移动。

公开(公告)号：US20080023584A1

公开(公告)日：2008-01-31

申请号：US11765065

申请日：2007-06-19

申请人： Jacques BEAUFORT

发明人： Jacques BEAUFORT

IPC分类号： B64C1/14 ,  B64D27/00 ,  E05D7/00

CPC分类号： B64D29/06 ,  E05D3/022 ,  E05Y2900/502 ,  Y10T16/522

摘要： This invention relates to a hinge device (20) of a nacelle cowling of an aircraft engine (6) on a supporting structure, including two fittings as well as a link rod (34) connected thereto and mounted on the fitting (32) by means of an end connection (48). According to the invention, the link rod is also mounted on the fitting (32) by means of an intermediate connection (56) including a pivot pin (58) slidably housed in a hole (60), and the connection (48) includes a guide pin (50) slidably housed in a guide ramp (54), and the connections (48, 56) are designed so as to create, upon rotation of the link rod about the pin (58), a relative movement of the axis (50) in the ramp (54), simultaneously causing a relative movement of the pin (58) in the hole (54).

摘要翻译： 本发明涉及一种在支撑结构上的飞机发动机（6）的机舱罩的铰链装置（20），其包括两个配件以及连接到其上的连杆（34），并通过装置 的端部连接（48）。 根据本发明，连杆通过包括可滑动地容纳在孔（60）中的枢轴销（58）的中间连接件（56）安装在配件（32）上，并且连接件（48）包括一个 引导销（50）可滑动地容纳在引导斜面（54）中，并且连接件（48,56）被设计成当连杆绕销（58）旋转时产生轴线（58,56）的相对运动 50）在斜坡（54）中，同时引起销（58）在孔（54）中的相对运动。

公开(公告)号：US08322651B2

公开(公告)日：2012-12-04

申请号：US12304772

申请日：2007-07-09

申请人： Stephane Levert ,  Jacques Beaufort

发明人： Stephane Levert ,  Jacques Beaufort

IPC分类号： B64D27/00

CPC分类号： B64D27/26 ,  B64C27/26 ,  B64D2027/268

摘要： A mounting structure for an aircraft engine including a rigid structure and a mechanism to mount the engine on the rigid structure. The mounting mechanism includes a thrust load device including two side thrust links each including an aft end mounted on an evener bar of the device, via a mechanical connection. Each connection is formed by a lug provided on the evener bar and passing through an orifice made in the aft end, the lug being arranged so as to extend substantially laterally relative to the mounting structure.

摘要翻译： 一种用于飞机发动机的安装结构，包括刚性结构和将发动机安装在刚性结构上的机构。 安装机构包括推力负载装置，该推力负载装置包括两个侧向推力连接件，每个侧推力连接件通过机械连接件包括安装在装置的再生杆上的后端。 每个连接由设置在延长杆上并通过在后端制成的孔的凸耳形成，凸耳布置成相对于安装结构基本上横向延伸。

公开(公告)号：US07147185B2

公开(公告)日：2006-12-12

申请号：US10954192

申请日：2004-10-01

申请人： Jacques Beaufort

发明人： Jacques Beaufort

IPC分类号： B64D27/00

CPC分类号： B64D29/06

摘要： The invention relates to a device (131) for assembly of a shroud (26) arranged between an air intake (22) and a pylon (2) fixed to the engine (4), the device comprising: stressed flexible means (130) provided with a first end (130a) and a second end (130b); first connection means connected to the air intake and to the end (130a); and second connection means connected to the shroud and to the end (130b). According to the invention, the second connection means comprise a primary assembly (140) fixed to the shroud and a secondary assembly (142) fixed to the second end (130b), and the primary and secondary assemblies (140,142) are connected to each other through a pivot connection (144).

摘要翻译： 本发明涉及一种用于组装布置在固定到发动机（4）的进气口（22）和塔架（2）之间的护罩（26）的装置（131），该装置包括：应力柔性装置（130） 具有第一端（130a）和第二端（130b）; 连接到进气口和端部（130a）的第一连接装置; 以及连接到护罩和端部（130b）的第二连接装置。 根据本发明，第二连接装置包括固定到护罩的主组件（140）和固定到第二端（130b）的次级组件（142），并且主组件和次组件（140,142）连接到每个 另一个通过枢轴连接（144）。