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：US07942580B2

公开(公告)日：2011-05-17

申请号：US11608971

申请日：2006-12-11

申请人： Virginie Audart-Noel ,  Stephane Levert

发明人： Virginie Audart-Noel ,  Stephane Levert

IPC分类号： F16C27/00

CPC分类号： F16C11/0614 ,  B64D27/26 ,  B64D2027/266 ,  F16C27/02 ,  F16C2326/43 ,  Y02T50/44

摘要： A rear suspension (10) for an aircraft engine assembly comprises a structure comprising two three-point shackles (12, 12′) and one two-point shackle (14). One of the hinge pins in waiting on the two-point shackle (14), preferably the hinge pin (26) fixed to the engine yoke joint, is mounted with clearance and with a damping ring acting as a spring to prevent vibrations of the engines as long as the hinge pin (26) is not engaged. Each of the suspension connecting pins (10) is a ball joint connection, the beam (16) of the suspension (10) being provided with five aligned orifices (24, 24a, 28, 24′, 24a′).

摘要翻译： 用于飞机发动机组件的后悬架（10）包括包括两个三点钩环（12,12'）和一个两点卸扣（14）的结构。 等待两点卸扣（14）的铰链销之一，优选地固定在发动机轭架接头上的铰链销（26）安装有间隙，并具有用作弹簧的阻尼环，以防止发动机振动 只要铰链销（26）不接合即可。 悬挂连接销（10）中的每一个是球接头连接，悬架（10）的梁（16）设置有五个对准的孔（24,24a，28,24'，24a'）。

公开(公告)号：US20080296430A1

公开(公告)日：2008-12-04

申请号：US12064916

申请日：2006-08-31

申请人： Stéphane Combes ,  Stephane Levert ,  Laurent Lafont ,  Dominique Moreau

发明人： Stéphane Combes ,  Stephane Levert ,  Laurent Lafont ,  Dominique Moreau

IPC分类号： B64D27/00

CPC分类号： B64D27/26 ,  B64D2027/268

摘要： An arrangement configured to connect an evener bar onto a rigid structure of an aircraft engine mount, including a pin system slidingly mounted in a first passageway of a bracket to permit its displacement along a first longitudinal axis, in a first direction from a normal extended position to a retracted position in which the pin system is retracted within this same bracket, and conversely. The arrangement also includes a pin extending member carried by the system and configured to be moved parallel to the longitudinal axis, in a second direction from a normal retracted position to an extended position in which the pin extending member is joined to the system and projects beyond the system, and conversely.

摘要翻译： 一种被配置为将再生棒连接到飞行器发动机支架的刚性结构上的装置，包括滑动地安装在支架的第一通道中的销系统，以允许其沿着第一纵向轴线从第一方向从正常延伸位置 到缩回位置，其中销系统在该相同的支架内缩回，反之亦然。 该布置还包括由该系统承载的销销延伸构件，并且构造成在从正常缩回位置到延伸位置的第二方向上平行于纵向轴线移动，销延伸构件连接到系统并突出超出 系统，而相反。

公开(公告)号：US08042764B2

公开(公告)日：2011-10-25

申请号：US12089312

申请日：2006-10-10

申请人： Stephane Levert

发明人： Stephane Levert

IPC分类号： B64D27/00

CPC分类号： B64D27/26 ,  B64D2027/268 ,  F16B39/10 ,  F16B39/103 ,  Y10T403/1691

摘要： A nut system including a nut including a main thread with pitch p1 and arranged along a screwing axis of the nut. A threaded device is coupled in rotation with the nut, the threaded device including a secondary non-screwed thread on the main thread from which it is separated, the secondary thread being arranged along the screwing axis and having a pitch p2 different from p1. Such a nut system may find application with a device for resistance of thrusts generated by an aircraft engine.

摘要翻译： 螺母系统，包括具有螺距p1并沿螺母的螺纹轴线布置的螺母的螺母。 螺纹装置与螺母旋转联接，螺纹装置包括主螺纹上的次级非螺纹螺纹，从其分离，副螺纹沿着螺纹轴线布置并具有与p1不同的间距p2。 这种螺母系统可能会发现应用具有由飞机发动机产生的推力阻力的装置。

公开(公告)号：US20080169377A1

公开(公告)日：2008-07-17

申请号：US11769179

申请日：2007-06-27

申请人： Stephane Levert

发明人： Stephane Levert

IPC分类号： B64D27/00

CPC分类号： B64D27/26 ,  B64D2027/268

摘要： The present invention relates to a mounting device for an aircraft engine comprising a rigid structure and means for mounting the engine on the rigid structure, the mounting means comprising a thrust load recovery device (14) comprising two lateral thrust load recovery rods (26) each having a rear end (26b) mounted on a crossbar (28) of the device (14), by means of a first mechanical connection (44). At the rear end of each of the two rods, there is also provided a second mechanical connection (46) with play between the rear end (26b) and a support fitting (60) integral with the rigid structure. According to the invention, the first mechanical connection (44) is implemented using a pin (48) provided on the crossbar, passing through an orifice (50) provided in the rear end of the rod (26).

摘要翻译： 本发明涉及一种用于飞行器发动机的安装装置，其包括刚性结构和用于将发动机安装在刚性结构上的装置，所述安装装置包括推力负载恢复装置（14），其包括两个侧向推力负载恢复杆（26） 具有通过第一机械连接（44）安装在所述装置（14）的横杆（28）上的后端（26b）。 在两个杆的每一个的后端处，还设置有在后端（26b）和与刚性结构一体的支撑配件（60）之间的间隙的第二机械连接（46）。 根据本发明，第一机械连接（44）使用设置在横杆上的销（48）来实现，其穿过设置在杆（26）的后端中的孔口（50）。

公开(公告)号：US08613404B2

公开(公告)日：2013-12-24

申请号：US13239939

申请日：2011-09-22

申请人： Laurent Lafont ,  Stephane Combes ,  Stephane Levert

发明人： Laurent Lafont ,  Stephane Combes ,  Stephane Levert

IPC分类号： B64B1/24

CPC分类号： B64D27/26 ,  B64D2027/268

摘要： 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).

摘要翻译： 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：US07891604B2

公开(公告)日：2011-02-22

申请号：US11914560

申请日：2006-06-27

申请人： Stephane Combes ,  Laurent Lafont ,  Stephane Levert

发明人： Stephane Combes ,  Laurent Lafont ,  Stephane Levert

IPC分类号： B64D27/26

CPC分类号： B64D27/26 ,  Y02T50/44

摘要： 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.

摘要翻译： 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：US20080232924A1

公开(公告)日：2008-09-25

申请号：US12089312

申请日：2006-10-10

申请人： Stephane Levert

发明人： Stephane Levert

IPC分类号： B64D27/26 ,  F16D1/00 ,  B64D27/00

CPC分类号： B64D27/26 ,  B64D2027/268 ,  F16B39/10 ,  F16B39/103 ,  Y10T403/1691

摘要： The invention relates to a nut system (100) comprising a nut (104) provided with a main thread (106) with pitch p1 and arranged along a screwing axis (108) of the nut. According to the invention, it also comprises a threaded device (116) coupled in rotation with the nut, this threaded device comprising a secondary non-screwed thread (122) on the main thread (106) from which it is separated, the secondary thread being arranged along the screwing axis and having a pitch p2 different from p1. Application of the invention with a device for resistance of thrusts generated by an aircraft engine.

摘要翻译： 本发明涉及一种螺母系统（100），该螺母系统（100）包括螺母（104），螺母（104）设置有具有螺距p 1并沿着螺母的螺纹轴线（108）布置的主螺纹（106）。 根据本发明，其还包括与螺母旋转联接的螺纹装置（116），该螺纹装置包括主螺纹（106）上的第二非螺纹螺纹（122），从其分离，副螺纹 沿螺旋轴线布置并且具有与p 1不同的间距p 2。本发明具有用于由飞机发动机产生的推力阻力的装置。

公开(公告)号：US20080197233A1

公开(公告)日：2008-08-21

申请号：US11914560

申请日：2006-06-27

申请人： Stephane Combes ,  Laurent Lafont ,  Stephane Levert

发明人： Stephane Combes ,  Laurent Lafont ,  Stephane Levert

IPC分类号： B64D27/26

CPC分类号： B64D27/26 ,  Y02T50/44

摘要： 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.

摘要翻译： 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：US20070138337A1

公开(公告)日：2007-06-21

申请号：US11608971

申请日：2006-12-11

申请人： Virginie Audart-Noel ,  Stephane Levert

发明人： Virginie Audart-Noel ,  Stephane Levert

IPC分类号： B64D33/00

CPC分类号： F16C11/0614 ,  B64D27/26 ,  B64D2027/266 ,  F16C27/02 ,  F16C2326/43 ,  Y02T50/44

摘要： A rear suspension (10) for an aircraft engine assembly comprises a structure comprising two three-point shackles (12, 12′) and one two-point shackle (14). One of the hinge pins in waiting on the two-point shackle (14), preferably the hinge pin (26) fixed to the engine yoke joint, is mounted with clearance and with a damping ring acting as a spring to prevent vibrations of the engines as long as the hinge pin (26) is not engaged. Each of the suspension connecting pins (10) is a ball joint connection, the beam (16) of the suspension (10) being provided with five aligned orifices (24, 24a, 28, 24′, 24a′).

摘要翻译： 用于飞机发动机组件的后悬架（10）包括包括两个三点钩环（12,12'）和一个两点卸扣（14）的结构。 等待两点卸扣（14）的铰链销之一，优选地固定在发动机轭架接头上的铰链销（26）安装有间隙，并具有用作弹簧的阻尼环，以防止发动机振动 只要铰链销（26）不接合即可。 悬挂连接销（10）中的每一个是球接头连接，悬架（10）的梁（16）设置有五个对准的孔（24,24a，28,24'，24a'）。