公开(公告)号：US20080197233A1

公开(公告)日：2008-08-21

申请号：US11914560

申请日：2006-06-27

Applicant: Stephane Combes ,  Laurent Lafont ,  Stephane Levert

Inventor： Stephane Combes ,  Laurent Lafont ,  Stephane Levert

IPC: B64D27/26

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 a first shear pin capable of resisting forces applied along a transverse direction of the pylon. The first pin passes through a lower spar of a rigid structure of the pylon and includes a lower end housed in the aft attachment body. The lower end includes a reaming through which a first pin passes, that also passes through the aft attachment body.

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能够抵抗沿着塔架的横向方向施加的力的第一剪切销。 第一销穿过塔的刚性结构的下部翼梁，并且包括容纳在后部附接体中的下端。 下端包括第一销通过的铰孔，其也穿过后部附接体。

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：US08613404B2

公开(公告)日：2013-12-24

申请号：US13239939

申请日：2011-09-22

Applicant: Laurent Lafont ,  Stephane Combes ,  Stephane Levert

Inventor： Laurent Lafont ,  Stephane Combes ,  Stephane Levert

IPC: B64B1/24

CPC classification number: B64D27/26 ,  B64D2027/268

Abstract: The present invention relates to a take-up device for thrust forces (14) for an aircraft engine attachment pylon (4), comprising a first fitting (194) attached to a rigid structure (108) of the attachment pylon, and two lateral connecting rods (14a) for take-up of thrust forces. It also comprises an axis system (190) bearing three first ball joint organs (192a, 196a) arranged along the latter and belonging respectively to a primary ball joint (192) and two secondary ball joints (196) arranged on either side of the primary ball joint, the first fitting (194) integrating a second ball joint organ (192b) cooperating with the first organ (192a) of the primary ball joint (192), and an end of each of the two connecting rods (14a) integrating a second ball joint organ (196b) cooperating respectively with the first organs (196a) of the two secondary ball joints (196).

Abstract translation: 本发明涉及一种用于飞机发动机附件塔（4）的用于推力（14）的卷取装置，包括附接到附接塔的刚性结构（108）的第一配件（194）和两个横向连接 杆（14a）用于吸收推力。 它还包括轴承系统（190），其轴承有三个第一球形接头器件（192a，196a），其沿着该第一球形接头器件（192a，196a）布置并分别属于主球接头（192）和两个辅助球接头（196） 球形接头，与第一球窝接头（192）的第一器官（192a）配合的第二球窝接头器官（192b）的第一配件（194）和两个连接杆（14a）中的每一个的一端 第二球关节器官（196b）分别与两个次级球窝接头（196）的第一器官（196a）配合。

公开(公告)号：US07967242B2

公开(公告)日：2011-06-28

申请号：US12065837

申请日：2006-09-26

Applicant: Stephane Combes ,  Laurent Lafont

Inventor： Stephane Combes ,  Laurent Lafont

IPC: B64D27/00

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：US07950604B2

公开(公告)日：2011-05-31

申请号：US11916537

申请日：2006-06-27

Applicant: Stephane Combes ,  Laurent Lafont

Inventor： Stephane Combes ,  Laurent Lafont

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：US07891604B2

公开(公告)日：2011-02-22

申请号：US11914560

申请日：2006-06-27

Applicant: Stephane Combes ,  Laurent Lafont ,  Stephane Levert

Inventor： Stephane Combes ,  Laurent Lafont ,  Stephane Levert

IPC: B64D27/26

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 a first shear pin capable of resisting forces applied along a transverse direction of the pylon. The first pin passes through a lower spar of a rigid structure of the pylon and includes a lower end housed in the aft attachment body. The lower end includes a reaming through which a first pin passes, that also passes through the aft attachment body.

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能够抵抗沿着塔架的横向方向施加的力的第一剪切销。 第一销穿过塔的刚性结构的下部翼梁，并且包括容纳在后部附接体中的下端。 下端包括第一销通过的铰孔，其也穿过后部附接体。

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：US08146856B2

公开(公告)日：2012-04-03

申请号：US12596555

申请日：2008-04-18

Applicant: Stephane Combes ,  Didier Rovatti

Inventor： Stephane Combes ,  Didier Rovatti

IPC: B64D27/00

CPC classification number: B64D27/26 ,  B64D2027/268

Abstract: An attachment device for an aircraft engine that includes a rigid structure and an attachment mechanism of the engine to the rigid structure. The attachment mechanism includes a device reacting to thrust forces generated by the engine, the reacting device including two link rods mechanically connected to a balance beam at a rear end by a first mechanical connection, a main fitting fixed to the rigid structure to which the balance beam is mechanically connected, and two additional fittings fixed to the rigid structure to which the link rods are mechanically connected with play. The mechanical connections between the balance beam and the main fitting and between the link rods and the additional fittings each include a pin orthogonal to a mid-plane of transmission of the forces.

Abstract translation: 一种用于飞机发动机的附接装置，其包括发动机刚性结构的刚性结构和附接机构。 附接机构包括对由发动机产生的推力作出反应的装置，该反作用装置包括通过第一机械连接在后端机械地连接到平衡梁的两个连杆，固定到刚性结构的主配件， 梁被机械地连接，并且两个附加的配件固定到刚性结构，链节杆与机械连接。 平衡梁和主配件之间以及连杆和附加配件之间的机械连接各自包括与力的传播中平面正交的销。