公开(公告)号：US08251311B2

公开(公告)日：2012-08-28

申请号：US12596501

申请日：2008-04-18

Applicant: Stephane Combes ,  Laurent Sammito ,  Michael Berjot

Inventor： Stephane Combes ,  Laurent Sammito ,  Michael Berjot

IPC: B64D27/00

CPC classification number: B64D27/26 ,  B64D2027/268

Abstract: An engine attachment pylon for an aircraft including an intermediate piece interposed between a crossbar support and a rigid caisson, a first shear slug passing through a first interface fixing plane between the piece and the caisson, and a second shear slug passing through a second interface fixing plane between the piece and the support. Also, in side elevation, the intersection point between an axis of the pin and the plane, as well as the intersection point between an axis of the pin and the plane, are located on the common axis of two lateral thrust force collection connecting rods articulated on the crossbar.

Abstract translation: 一种用于飞行器的发动机附接塔架，包括插入在横梁支架和刚性沉箱之间的中间件，穿过所述件和所述沉箱之间的第一界面固定平面的第一剪切块和穿过所述第二界面固定的第二剪切块 平面之间的片段和支撑。 此外，在侧视图中，销的轴线与平面之间的交点以及销和平面的轴线之间的交点位于两个侧向推力收集连杆的公共轴上 在横梁上

公开(公告)号：US08167238B2

公开(公告)日：2012-05-01

申请号：US12596784

申请日：2008-04-22

Applicant: Pascal Gardes ,  Stephane Combes

Inventor： Pascal Gardes ,  Stephane Combes

IPC: B64D27/00

CPC classification number: B64D27/26 ,  B64D2027/264 ,  B64D2027/266

Abstract: An aircraft assembly including a wing element and an attachment pylon of a turboengine, including a rigid structure forming a caisson defined externally by a first longeron, a second longeron, and two lateral panels. The assembly also includes an attachment mechanism of the structure on the wing element, fitted with two front attachments, each including two first fittings solid with the associated lateral panel. For each front attachment, the two first fittings are arranged respectively on either side of their associated lateral panel.

Abstract translation: 包括翼元件和涡轮发动机的附接塔的飞行器组件，包括形成由第一长龙，第二长龙和两个侧面板外部限定的沉箱的刚性结构。 组件还包括在翼元件上的结构的附接机构，其具有两个前附件，每个包括两个与相关联的侧板实体固定的第一配件。 对于每个前附件，两个第一配件分别布置在其相关侧板的两侧。

公开(公告)号：US20100116926A1

公开(公告)日：2010-05-13

申请号：US12594455

申请日：2008-04-11

Applicant: Stephane Combes ,  Emmanuel Guillet

Inventor： Stephane Combes ,  Emmanuel Guillet

IPC: B64D27/00

CPC classification number: B64D27/26 ,  B64D2027/268

Abstract: A device for attaching an aircraft engine including a thrust force take-up device that includes a main fitting to be fixed to an engine mounting beam fixed to a box structure, an additional fitting fixed to the main fitting, and two load reacting link rods connected to the main fitting by a balance beam, each of the link rods being connected to the balance beam by a first longitudinal end by a first mechanical connection that has at least one axis of rotation, each of the link rods being connected to the additional fitting by a second longitudinal end by a second mechanical connection that has at least one axis of rotation, the second mechanical connection having play, the first and second mechanical connections having at least one axis of rotation in common.

Abstract translation: 一种用于附接飞行器发动机的装置，包括：推力牵引装置，其包括固定到固定到箱结构的发动机安装梁的主配件，固定到主配件的附加配件以及连接的两个负载反作用连杆 通过平衡梁到主配件，每个连杆通过具有至少一个旋转轴线的第一机械连接件通过第一纵向端连接到平衡梁上，每个连杆连接到附加配件 通过具有至少一个旋转轴线的第二机械连接的第二纵向端，所述第二机械连接具有打开，所述第一和第二机械连接具有至少一个共同旋转轴线。

公开(公告)号：US20110266389A1

公开(公告)日：2011-11-03

申请号：US13078593

申请日：2011-04-01

Applicant: Stephane COMBES ,  Pascal Gardes

Inventor： Stephane COMBES ,  Pascal Gardes

IPC: B64D27/02 ,  B23P11/00

CPC classification number: B64D27/26 ,  B64D29/06 ,  F16B21/16

Abstract: The invention relates to a connection assembly of an engine pylori underneath an aircraft wing, the wing being provided with a fitting (6), the engine pylori being provided with a fork joint (5) nested in the fitting and fixed to the said fitting by means of a traversing pin system (10), provided with: an external primary pin (11), a secondary pin (12) mounted inside the primary pin, a primary shoulder (13) mounted directly around the primary pin, at a blind end of the pin system, to block the said pin in translation, a secondary shoulder (14) mounted around one end of the secondary pin, at a blind end of the pin system, to block the system in rotation, an interlocking assembly (15, 16) mounted around the primary pin and the secondary pin, at a free end of the pin system, to block the pin system in translation.

Abstract translation: 本发明涉及飞机机翼下方的发动机幽门螺杆的连接组件，翼部设置有配件（6），发动机幽门设置有嵌套在配件中的叉接头（5），并通过 具有：外部主销（11），安装在所述主销内部的辅助销（12）的横向销系统（10）的装置，在所述主销周边直接安装的主肩部（13） 所述销系统中的所述销平移，在所述销系统的盲端处安装在所述副销的一端周围的次级肩部（14），以阻止所述系统旋转;联锁组件（15， 16）安装在主销和辅助销周围，在销系统的自由端，以平移来阻止销系统。

公开(公告)号：US20100181417A1

公开(公告)日：2010-07-22

申请号：US12664256

申请日：2008-06-19

Applicant: Stephane Combes ,  Didier Rovatti

Inventor： Stephane Combes ,  Didier Rovatti

IPC: B64D27/26

CPC classification number: B64D27/26 ,  Y02T50/44

Abstract: An attachment device for an aircraft engine including a rigid structure and an attachment mechanism of the engine onto the rigid structure. The attachment mechanism includes two thrust take-up connecting rods mechanically connected to a spreader, a connection fitting fixed to the rigid structure to which the spreader is mechanically connected by a junction fitting by a connection pin, and an additional fitting to which the connecting rods, the spreader, and the connection fitting are mechanically connected. A clearance is provided at the mechanical link between the connecting rods and the additional fitting, the link between the additional fitting and the connection fitting being made using the connection pin being inserted laterally, orthogonal to the median plane of the attachment device.

Abstract translation: 一种用于飞机发动机的附接装置，包括刚性结构和发动机在刚性结构上的附接机构。 连接机构包括机械地连接到吊具的两个推力连接杆，固定到刚性结构的连接配件，通过连接销通过连接接头将吊具机械连接到该连接配件上，连接杆 ，吊具和连接配件机械连接。 在连接杆和附加配件之间的机械连接处设置有间隙，附加配件和连接配件之间的连接是使用连接销横向插入的，该连接销正交于附接装置的中间平面。

公开(公告)号：US20080237394A1

公开(公告)日：2008-10-02

申请号：US12065837

申请日：2006-09-26

Applicant: Stephane Combes ,  Laurent Lafont

Inventor： Stephane Combes ,  Laurent Lafont

IPC: B64D27/02

CPC classification number: B64D27/26 ,  B64D27/12 ,  B64D2027/268

Abstract: A device for suspension of an engine, configured to be inserted between an aircraft wing and the engine. The device includes a rigid structure and a forward aerodynamic structure mounted fixed on the structure through a suspension mechanism. The forward aerodynamic structure is configured to carry engine fan casings and to be inserted between the rigid structure and the wing. The suspension mechanism includes at least one adjustable length connecting rod of which one end is mounted on the rigid structure, and the other end is mounted on the forward aerodynamic structure.

Abstract translation: 一种用于悬挂发动机的装置，其被构造成插入飞机机翼和发动机之间。 该装置包括刚性结构和通过悬挂机构固定在结构上的前向空气动力学结构。 前向空气动力学结构被配置为承载发动机风扇壳体并且被插入在刚性结构和机翼之间。 悬架机构包括至少一个可调长度的连杆，其一端安装在刚性结构上，另一端安装在前空气动力结构上。

公开(公告)号：US20080197262A1

公开(公告)日：2008-08-21

申请号：US11916537

申请日：2006-06-27

Applicant: Stephane Combes

Inventor： Stephane Combes

IPC: B64D27/00

CPC classification number: B64D27/26 ,  Y02T50/44

Abstract: An engine attachment pylon for an aircraft including an aft engine attachment fitted with an aft attachment body and two lateral brackets each including a longitudinal portion in contact with an inner face of the lateral panel associated with it and mounted fixed on the same inner face, and a transverse portion including an attachment interface for the aft attachment body, the transverse portion configured to pass through a recess formed on the associated lateral panel.

Abstract translation: 一种用于飞行器的发动机附接塔架，包括装配有后部附接体的后部发动机附件和两个横向支架，每个横向支架包括与其相关联并安装在相同内表面上的侧板的内表面的纵向部分，以及 横向部分，其包括用于后部附接体的附接界面，所述横向部分被配置为穿过形成在相关联的侧板上的凹部。

公开(公告)号：US08561941B2

公开(公告)日：2013-10-22

申请号：US13078593

申请日：2011-04-01

Applicant: Stephane Combes ,  Pascal Gardes

Inventor： Stephane Combes ,  Pascal Gardes

IPC: B64D27/00

CPC classification number: B64D27/26 ,  B64D29/06 ,  F16B21/16

Abstract: A connection assembly of an engine pylon underneath an aircraft wing, the wing being provided with a fitting, the engine pylon being provided with a fork joint nested in the fitting and fixed to the said fitting by means of a traversing pin system, including: an external primary pin, a secondary pin mounted inside the primary pin, a primary shoulder mounted directly around the primary pin, at a blind end of the pin system, to block the said pin in translation, a secondary shoulder mounted around one end of the secondary pin, at a blind end of the pin system, to block the system in rotation, and an interlocking assembly mounted around the primary pin and the secondary pin, at a free end of the pin system, to block the pin system in translation.

Abstract translation: 一种在飞行器机翼下方的发动机塔架的连接组件，所述机翼设置有配件，所述发动机吊架设置有嵌套在所述配件中的叉形接头，并通过横动销系统固定到所述配件，包括： 外部主销，安装在所述主销内的辅助销，在所述销系统的盲端处直接安装在所述主销周围的主肩部，以平滑地阻挡所述销，安装在所述二次侧的一端的副肩 引脚在引脚系统的盲端处阻止系统旋转，并且在引脚系统的自由端处安装在主引脚和次级引脚周围的互锁组件以平移来阻止引脚系统。

公开(公告)号：US20100133376A1

公开(公告)日：2010-06-03

申请号：US12598649

申请日：2008-05-21

Applicant: Laurent Foyer ,  Fabien Menou ,  Stephane Combes

Inventor： Laurent Foyer ,  Fabien Menou ,  Stephane Combes

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D2027/266

Abstract: A mounting pylon for an aircraft engine. The pylon includes a rigid structure forming a box including an inclined lower spar and an upper spar, and an engine mounting system mounted fixedly on the structure and including a forward attachment including an attachment body including a horizontal securing surface lying flat against a horizontal securing surface of the rigid structure. The horizontal securing surface of the rigid structure is defined by a tapered shim mounted on the inclined lower spar, externally relative to the box.

Abstract translation: 飞机发动机的安装塔架。 该塔架包括形成包括倾斜的下部翼梁和上部翼梁的箱体的刚性结构，以及固定地安装在该结构上的发动机安装系统，并且包括一个前部附件，该附件包括一个水平的固定表面， 的刚性结构。 刚性结构的水平固定表面由安装在倾斜的下部翼梁上的锥形垫片限定，相对于箱体在外部。

公开(公告)号：US20100127117A1

公开(公告)日：2010-05-27

申请号：US12596501

申请日：2008-04-18

Applicant: Stephane Combes ,  Laurent Sammito ,  Michael Berjot

Inventor： Stephane Combes ,  Laurent Sammito ,  Michael Berjot

IPC: B64D27/02 ,  B64D27/26

CPC classification number: B64D27/26 ,  B64D2027/268

Abstract: An engine attachment pylon for an aircraft including an intermediate piece interposed between a crossbar support and a rigid caisson, a first shear slug passing through a first interface fixing plane between the piece and the caisson, and a second shear slug passing through a second interface fixing plane between the piece and the support. Also, in side elevation, the intersection point between an axis of the pin and the plane, as well as the intersection point between an axis of the pin and the plane, are located on the common axis of two lateral thrust force collection connecting rods articulated on the crossbar.

Abstract translation: 一种用于飞行器的发动机附接塔架，包括插入在横梁支架和刚性沉箱之间的中间件，穿过所述件和所述沉箱之间的第一界面固定平面的第一剪切块和穿过所述第二界面固定的第二剪切块 平面之间的片段和支撑。 此外，在侧视图中，销的轴线与平面之间的交点以及销和平面的轴线之间的交点位于两个侧向推力收集连杆的公共轴上 在横梁上