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1. 发明申请

WO2013045852A3 IMPROVED FRONT LANDING-GEAR WELL 审中-公开
标题翻译：改进的前置齿轮
公开(公告)号：WO2013045852A3
公开(公告)日：2013-10-03
申请号：PCT/FR2012052194
申请日：2012-09-27
申请人： AIRBUS OPERATIONS SAS
发明人： GUERING BERNARD , DURAND YVES
IPC分类号： B64C25/04
CPC分类号： B64C1/14 , B64C1/061 , B64C1/10 , B64C1/36 , B64C25/04 , B64C25/10 , B64C25/14
摘要： The present invention relates to a front portion of an aircraft (1) including a fuselage (15) and a landing-gear well (22) housing a front landing gear (30) including a brace strut (36) designed such as to adopt an extended configuration when the landing gear is down, in which configuration said brace strut (36) is aligned with a strut plane (P1) parallel to the transverse direction (Y) of the front portion. According to the invention, the front portion includes a transverse beam (40) for taking up the forces from the strut, arranged above the landing-gear well (22) and mounted at the two ends thereof on the fuselage (15), the beam (40) having a generally rectangular cross-section in which the median plane (P2), parallel to the length of the rectangle, coincides with the strut plane (P1).
摘要翻译：本发明涉及飞机（1）的前部，其包括机身（15）和起落架井架（22），该起落架井架（22）容纳前起落架（30），前起落架（30）包括支柱支柱（36），其被设计成采用当起落架下降时，延伸构造，其中所述支撑支柱（36）与平行于前部横向（Y）的支柱平面（P1）对齐。根据本发明，前部包括横梁（40），用于从支柱上取下力，该横梁设置在起落架井（22）的上方，并在其两端安装在机身（15）上，梁（40）具有大致矩形的横截面，其中平行于矩形长度的中间平面（P2）与支柱平面（P1）重合。

2. 发明申请

WO2012146858A3 AIRCRAFT FUSELAGE AND METHOD FOR CONSTRUCTING A FLOOR IN SUCH A FUSELAGE 审中-公开
标题翻译：用于构造这样一个地板的地板的飞机熔接和方法
公开(公告)号：WO2012146858A3
公开(公告)日：2014-03-20
申请号：PCT/FR2012050840
申请日：2012-04-17
申请人： AIRBUS OPERATIONS SAS , GUERING BERNARD
发明人： GUERING BERNARD
IPC分类号： B64C1/18
CPC分类号： B64C1/061 , B64C1/18 , Y10T29/49622
摘要： Such a fuselage comprises cross-members (104) for constructing a floor, at least one of said cross-members (104) comprising an upper part (124), a lower part (126), means (140-150) for connecting the lower part to the upper part, and at least one opening (152) for the passage of systems (14), said opening being defined between the lower part and the upper part. The upper part (124) of the cross-member is fixed to the fuselage and the dimensions thereof are such that it can withstand the stresses that may be applied to said cross-member when the aircraft is on the ground, and the lower part (126) is fixed to the upper part (124) in such a way as to reinforce it such that, once they are assembled, the upper part (124) and the lower part (126) can withstand the stresses that may be applied to said cross-member (104) when the aircraft is in flight.
摘要翻译：这样的机身包括用于构造地板的横向构件（104），所述横向构件（104）中的至少一个包括上部（124），下部（126），用于将下部到上部，以及用于系统（14）通过的至少一个开口（152），所述开口限定在下部和上部之间。横梁的上部（124）固定在机身上，其尺寸使得它能承受当飞机在地面上时施加到所述横梁上的应力，下部 126）被固定到上部（124），以便加强它，使得一旦它们被组装，上部（124）和下部（126）就可以承受可施加到所述的上部当飞机飞行时，横梁（104）。

3. 发明申请

WO2013045809A3 ELECTRICAL CENTER FOR AN AIRCRAFT 审中-公开
标题翻译：飞机电气中心
公开(公告)号：WO2013045809A3
公开(公告)日：2014-03-13
申请号：PCT/FR2012052138
申请日：2012-09-25
申请人： AIRBUS OPERATIONS SAS
发明人： GUERING BERNARD , DURAND YVES
IPC分类号： H05K7/14
CPC分类号： H05K7/02 , B64D47/00 , H05K7/1439 , H05K7/1449
摘要： The invention relates to an electrical center for an aircraft, comprising at least one rack (54) on which at least one module (56) is arranged, said module containing components and including at least one input suitable for being connected to at least one power cable (60) and at least one output suitable for being connected to at least one output cable (64), characterized in that, for one module (56), the output cable(s) (64) pass beneath or into the rack (54) arranged beneath the module.
摘要翻译：本发明涉及一种用于飞行器的电气中心，包括至少一个机架（54），至少一个模块（56）布置在该机架上，所述模块包含组件，并且包括至少一个适于连接至少一个功率的输入电缆（60）和至少一个适于连接到至少一个输出电缆（64）的输出端，其特征在于，对于一个模块（56），所述输出电缆（64）在所述机架 54）。

4. 发明申请

WO2012110725A2 CENTRAL PYLON FOR AN AIRCRAFT COCKPIT AND AIRCRAFT COMPRISING SUCH A PYLON 审中-公开
标题翻译：用于飞机机组的中央飞行器和包含这样一个PYLON的飞机
公开(公告)号：WO2012110725A2
公开(公告)日：2012-08-23
申请号：PCT/FR2012050189
申请日：2012-01-30
申请人： AIRBUS OPERATIONS SAS , GUERING BERNARD
发明人： GUERING BERNARD
IPC分类号： B64D31/04 , B64D11/00
CPC分类号： B64D11/00 , B64D31/04 , B64D43/00
摘要： The invention relates to a central pylon of an aircraft cockpit, which is used to secure the control and regulation equipment of the aircraft. The pylon includes: an equipment module (40) comprising controls connected to at least a first electrical connector (58); and a one-piece chassis (41) comprising an upper face provided with a tray (45) having at least a second electrical connector (43) positioned on the base of the tray and connected to the aircraft on-board computers, the equipment module being installed in the tray, while the at least one first electrical connector (58) of the equipment module is inserted into at least a second electrical connector (43), such as to connect the equipment module and the on-board computers. The invention also relates to an aircraft comprising such a pylon.
摘要翻译：本发明涉及飞机驾驶舱的中央塔架，其用于固定飞机的控制和调节设备。所述挂架包括：设备模块（40），包括连接到至少第一电连接器（58）的控制器; 以及一体式底盘（41），其包括设置有托盘（45）的上表面，所述托盘具有至少第二电连接器（43），所述至少第二电连接器（43）定位在所述托盘的基座上并连接到所述飞行器机载计算机，所述设备模块被安装在所述托盘中，而所述设备模块的所述至少一个第一电连接器（58）插入到至少第二电连接器（43）中，以便连接所述设备模块和所述车载计算机。本发明还涉及一种包括这种塔架的飞行器。

5. 发明申请

WO2013098526A9 ASSEMBLY OF COMPACTLY INTEGRATED CONTACTORS IN AN ELECTRICAL CORE 审中-公开
标题翻译：在电芯中组装集成接触器
公开(公告)号：WO2013098526A9
公开(公告)日：2014-08-07
申请号：PCT/FR2012053087
申请日：2012-12-27
申请人： AIRBUS OPERATIONS SAS
发明人： GUERING BERNARD
IPC分类号： H02B1/04 , H02B1/056 , H02B1/20
CPC分类号： H02B1/24 , H02B1/04 , H02B1/056 , H02B1/20
摘要： An electrical core comprising an assembly of power management and distribution contactors. The power management contactors (2) are attached to a first support element (12) and the distribution contactors (4) are carried by a second support element (14) superimposed on the first so as to form a multilayer assembly. The distribution contactors (4) are arranged in double symmetry about two axes perpendicular to one another. They are mechanically linked through a mechanical linkage element extending between two rows of contactors (4) and which carries electrical connection elements (20) connecting the contactors to an element for connecting (22) to a power source. The contactors (2, 4) are assembled in modules (6, 8) according to their type. In particular, the management module (6) comprises at least one modular element common (7, 50, 60) to the power management contactors (2) which is suitable for performing a given secondary function other than the function of establishing a contact.
摘要翻译：一种电芯，包括电源管理和分配接触器的组件。电源管理接触器（2）附接到第一支撑元件（12）并且分配接触器（4）由叠置在第一支撑元件（14）上的第二支撑元件（14）承载，以形成多层组件。分布接触器（4）围绕彼此垂直的两个轴线以双重对称的方式布置。它们通过在两排接触器（4）之间延伸的机械连接元件机械连接，并且将连接接触器的电连接元件（20）连接到用于连接（22）到电源的元件。接触器（2,4）根据其类型组装在模块（6,8）中。特别地，管理模块（6）包括至少一个模块化元件公共端（7,50,60）到电源管理接触器（2），该模块元件公共端（7,50,60）适于执行除了建立触点的功能之外的给定辅助功能。

6. 发明申请

WO2013045810A2 ELECTRICAL CABINET FOR AN AIRCRAFT, INCLUDING AN IMPROVED ELECTRICAL CONNECTION SYSTEM 审中-公开
标题翻译：用于飞机的电气机柜，包括改进的电气连接系统
公开(公告)号：WO2013045810A2
公开(公告)日：2013-04-04
申请号：PCT/FR2012052139
申请日：2012-09-25
申请人： AIRBUS OPERATIONS SAS
发明人： GUERING BERNARD , DURAND YVES
IPC分类号： H05K7/14
CPC分类号： B60R16/03 , B60R16/0207 , H05K7/1439 , H05K7/1449
摘要： The invention relates to an electrical cabinet for an aircraft, including at least one motherboard (54) comprising, on a first surface thereof, sockets (62) into which PCB boards (56) can be inserted to provide one or more electrical functions, said electrical cabinet being connected to the electrical circuit of the aircraft, which is organized into various electrical harnesses (52) via an electrical connection system, characterized in that the electrical connection system includes at least one additional layer (58) at the second surface (64) of the motherboard (54), the free surface (66) of the last additional layer including sockets (68), each of which ensures the electrical connection to an electrical harness of the aircraft, the additional layer(s) (58) including tracks that enable the reorganization of the electrical circuits from the sockets (62) for the PCB boards (56) so as to make the sockets for the PCB boards consistent with the sockets (68) for the harnesses of the aircraft.
摘要翻译：本发明涉及一种用于飞行器的电气柜，包括至少一个母板（54），其在其第一表面上包括插座（62），PCB板（56）可以插入其中以提供一个或多个电功能，所述电气柜被连接到飞行器的电路，其经由电连接系统被组织成各种电气线束（52），其特征在于，电连接系统包括在第二表面（64）处的至少一个附加层（58）），所述最后一个附加层的自由表面（66）包括插座（68），每个插座（68）确保与飞行器的电气线束的电连接，所述附加层（58）包括能够从用于PCB板（56）的插座（62）重组电路以使PCB板的插座与用于飞机的线束的插座（68）一致的轨道。

7. 发明申请

WO2010026345A3 AIRCRAFT SEAT ASSEMBLY STRUCTURE, AND FITTED FUSELAGE 审中-公开
标题翻译：飞机座椅组装结构和紧固件
公开(公告)号：WO2010026345A3
公开(公告)日：2010-05-20
申请号：PCT/FR2009051669
申请日：2009-09-04
申请人： AIRBUS OPERATIONS SAS , GUERING BERNARD
发明人： GUERING BERNARD
IPC分类号： B64D11/06 , B60N2/015 , B60N2/07
CPC分类号： B64D11/0696 , B64D11/06 , B64D11/0629 , B64D11/0649 , Y02T50/46
摘要： The invention relates to an aircraft seat assembly structure (4) that comprises at least one seat portion structure (5) supporting at least one seat portion, a reference mark being associated with said seat assembly structure that is defined by: a longitudinal axis X, along which the seat portion structure (5) comprises a front portion and a rear portion; an axis Y, perpendicular to the axis X and forming with said axis X a horizontal plane XY when the at least one seat portion is horizontal; and an axis Z, perpendicular to the plane XY. The seat portion structure (5) comprises, in the front portion thereof, a torque bar (50) substantially parallel to the axis Y having, on a first side end (502) thereof, a front lateral fastening device (500) to be rigidly connected to a means (26) for laterally attaching an aircraft body structure (2). The invention also relates to a fuselage comprising said body structure having said lateral attachment means and to the aircraft comprising said fuselage and the seat assembly structure (4).
摘要翻译：本发明涉及一种飞机座椅组件结构（4），其包括支撑至少一个座椅部分的至少一个座椅部分结构（5），参考标记与所述座椅组件结构相关联，所述参考标记由以下限定：纵向轴线X，沿着该座椅部分结构（5）包括前部和后部; 垂直于轴线X并且当所述至少一个座位部分水平时与所述轴线X形成水平平面XY的轴线Y; 和垂直于平面XY的轴线Z. 座椅部分结构（5）在其前部包括基本上平行于轴线Y的扭矩杆（50），在其第一侧端（502）上具有刚性地固定的前侧向紧固装置（500）连接到用于横向附接飞机本体结构（2）的装置（26）。本发明还涉及一种机身，其包括具有所述侧向附接装置的所述车身结构以及包括所述机身和所述座椅组件结构（4）的飞行器。

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