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    Drainage mast of the compartment of an aircraft subjected to a negative pressure
    63.
    发明授权
    Drainage mast of the compartment of an aircraft subjected to a negative pressure 有权
    飞机受到负压的舱室的排水桅杆

    公开(公告)号：US09452833B2

    公开(公告)日：2016-09-27

    申请号：US14336085

    申请日：2014-07-21

    Applicant: Airbus Operations S.L.

    Inventor： Carlos Casado Montero ,  Jose Angel Hernanz Manrique ,  Jose Grana Otero ,  Ignacio Esteban Parra Fabian ,  Miguel Angel Gallego Lorenzo

    IPC: B64D1/00 ,  B64D1/16 ,  B64C1/14

    CPC classification number: B64D1/16 ,  B64C1/1453

    Abstract: A drainage mast able to drain effectively the liquid contained in the compartment of an aircraft when the pressure within the compartment is lower than the outside pressure without using any pressure control active device and without causing any significant perturbation to the aerodynamic behavior of the aircraft. The drainage mast is configured with a cross section area decreasing from its entry section to the compartment to its outlet section and is disposed at an acute angle α relative to the compartment in the airflow direction. The entry and outlet sections have two perpendicular symmetry axes of different length, the entry section is arranged with its longer axis of symmetry substantially parallel to the airflow direction. The drainage mast has a symmetrical configuration with respect to a plane substantially perpendicular to the fuselage envelope passing through the longer axis of symmetry of the entry section.

    Abstract translation: 当排气室内的压力低于外部压力时，不使用任何压力控制有源装置并且不会对飞行器的空气动力学行为产生任何明显的扰动，排水桅杆能够有效地排出飞机内部所含的液体。 排水桅杆构造有从入口部分到隔室到其出口部分的横截面面积，并且相对于隔室在气流方向上以锐角α设置。 入口和出口部分具有不同长度的两个垂直对称轴，入口部分布置成具有与气流方向基本平行的较长对称轴。 排水桅杆相对于基本上垂直于通过入口部分的较长对称轴的机身外壳的平面具有对称的构造。

    AIRCRAFT TAIL CONE
    64.
    发明申请
    AIRCRAFT TAIL CONE 审中-公开
    飞机尾灯

    公开(公告)号：US20160229513A1

    公开(公告)日：2016-08-11

    申请号：US15018481

    申请日：2016-02-08

    Applicant: Airbus Operations (SAS) ,  Airbus Operations GmbH ,  Airbus Operations S.L.

    Inventor： Henning Scheel ,  Eric Bouchet ,  Julien Guillemaut ,  Esteban Martino-Gonzalez

    IPC: B64C1/14 ,  B64C1/16 ,  B64C1/10

    CPC classification number: B64C1/1446 ,  B64C1/10 ,  B64C1/16 ,  B64D27/14 ,  B64D27/20 ,  B64D29/08 ,  B64D37/005 ,  B64D2041/002 ,  Y02T50/44

    Abstract: An aircraft tail cone comprising a fuselage in which avionic equipment is housed. The tail cone comprises two lateral hatches formed in the fuselage, at least one hatch being formed on each of the two opposite sides of the fuselage. Each hatch is mounted removably with respect to the fuselage so as to take up a closed first position in which the hatch closes a lateral opening in the fuselage, and an open second position in which the open hatch allows access to the inside of the tail cone through the corresponding opening The avionic equipment that requires regular inspection and/or maintenance operations is housed in a part of the tail cone which is accessible through the two lateral openings in the fuselage to a person who remains on the outside of the fuselage.

    Abstract translation: 飞机尾锥包括机身，其中安装有航空电子设备。 尾锥包括形成在机身中的两个横向舱口，至少一个舱口形成在机身的两个相对的两侧上。 每个舱口相对于机身可移除地安装，以便收起闭合的第一位置，其中舱口关闭机身中的侧向开口，以及打开的第二位置，打开的舱口允许进入尾锥体的内部 通过相应的开口需要定期检查和/或维护操作的航空电子设备被容纳在尾锥的一部分中，该尾锥可以通过机身中的两个侧向开口接近留在机身外部的人。

    Leading edge for an aircraft lifting surface
    65.
    发明授权
    Leading edge for an aircraft lifting surface 有权
    飞机起重面的前沿

    公开(公告)号：US09381992B2

    公开(公告)日：2016-07-05

    申请号：US14579717

    申请日：2014-12-22

    Applicant: Airbus Operations S.L.

    Inventor： Fernando Pereira Mosqueira ,  Enrique Guinaldo Fernandez ,  Carlos Garcia Nieto ,  Francisco Javier Honorato Ruiz ,  Andrea Ivan Marasco

    IPC: B64C3/18 ,  B64C3/28 ,  B64C3/26

    CPC classification number: B64C3/185 ,  B64C3/26 ,  B64C3/28

    Abstract: An optimized leading edge for an aircraft lifting or supporting surfaces, such as wings and stabilizers, wherein the leading edge includes inboard and outboard leading edge sections that are span-wise arranged so as to form together an aerodynamic surface of the leading edge. Each of the leading edge sections includes a skin panel and a support structure formed by spars that are internally arranged in the skin panel. These two support structures are designed taking into account the different load requirements of those two different sections, so that the number of spars in each leading edge section is progressively reduced from root to tip of the leading edge, in such a way that the support structure of the outboard leading edge section, has less spars than the inboard leading edge section. Hence the weight of the leading edge is reduced while still maintaining the required structural behavior.

    Abstract translation: 用于飞行器提升或支撑表面（例如翼和稳定器）的优化前缘，其中前缘包括横跨方向布置以一起形成前缘的空气动力学表面的内侧和外侧前缘部分。 每个前缘部分包括皮肤面板和由内部布置在皮肤面板中的翼梁形成的支撑结构。 这两个支撑结构被设计成考虑到这两个不同部分的不同负载要求，使得每个前缘部分中的翼梁的数量从前端的根部到尖端逐渐减小，使得支撑结构 的外侧前缘部分，具有比内侧前缘部分更少的翼梁。 因此，前沿的重量减小，同时仍然保持所需的结构行为。

    DOOR FOR CLOSING OPENING IN STRUCTURE AND AIRCRAFT
    67.
    发明申请
    DOOR FOR CLOSING OPENING IN STRUCTURE AND AIRCRAFT 审中-公开
    关闭结构和飞机开启门

    公开(公告)号：US20160176496A1

    公开(公告)日：2016-06-23

    申请号：US14977121

    申请日：2015-12-21

    Applicant: AIRBUS (S.A.S.) ,  Airbus Operations S.L.

    Inventor： Zengli Han ,  Haifeng Chen ,  Ming Luo ,  Angel Postigo-Rodriguez ,  Daniel De-La-Sen-Perez ,  Laure Partouche

    IPC: B64C1/14 ,  E05C3/12 ,  E06B3/04

    CPC classification number: B64C1/1446 ,  B64C3/34 ,  E05C3/124 ,  E06B3/04

    Abstract: The present invention relates to a door for closing an opening in a structure, including: a body arranged to be capable of abutting against a first side of the opening; at least one clamping member configured to be capable of abutting against an opposite second side of the opening; and a fastener arranged to fasten or release the clamping member relative to the body. The clamping member is moveable relative to the body between a first position where the clamping member abuts against the second side of the opening so as to clamp the structure between the body and the clamping member and a second position where the clamping member allows the door to be opened. The present invention further relates to an aircraft including the above door.

    Abstract translation: 本发明涉及一种用于关闭结构中的开口的门，包括：主体，其能够抵靠开口的第一侧; 至少一个夹紧构件构造成能够抵靠所述开口的相对的第二侧; 以及紧固件，其布置成相对于主体紧固或释放夹紧构件。 夹紧构件可相对于主体在第一位置和第二位置之间移动，该第一位置与夹紧构件抵靠开口的第二侧之间，以便将构件夹在主体和夹紧构件之间，并且夹紧构件允许门 被打开 本发明还涉及一种包括上述门的飞行器。

    AIRCRAFT HYBRID ENGINE
    68.
    发明申请
    AIRCRAFT HYBRID ENGINE 审中-公开
    飞机混合发动机

    公开(公告)号：US20160076446A1

    公开(公告)日：2016-03-17

    申请号：US14856834

    申请日：2015-09-17

    Applicant: Airbus Operations S.L.

    Inventor： Nicolas Bailey Noval ,  Raul Llamas Sandin

    IPC: F02C6/14 ,  F02C6/20

    CPC classification number: F02C6/14 ,  F02C6/20 ,  F02C6/206 ,  F02K3/06 ,  F02K5/00 ,  F05D2220/323 ,  F05D2220/64 ,  F05D2220/76

    Abstract: A propulsion engine comprising at least a first propulsion unit including a first fan encased by a geared ring and a gas turbine engine driving a first shaft connected to the first fan, at least a second propulsion unit including a second fan encased by a geared ring connected to a second shaft operatively coupled to an electric machine and at least an electric storage device connected to the electric machine. The geared rings are configured to transmit torque between the fans so that they can rotate in conjunction (directly or through an intermediate gear) when they are driven by at least one of said first and second shafts. The propulsion engine is arranged for controlling the torque to be supplied to the assembly of the first and second fans by the gas turbine engine and/or by the electric machine acting as a motor or as a generator.

    Abstract translation: 一种推进发动机，包括至少第一推进单元，其包括由齿轮环包围的第一风扇和驱动连接到第一风扇的第一轴的燃气涡轮发动机，至少第二推进单元，包括由齿轮环连接的第二风扇， 到可操作地耦合到电机的第二轴和连接到电机的至少一个蓄电装置。 齿轮环被配置为在风扇之间传递扭矩，使得它们可以在它们被所述第一和第二轴中的至少一个驱动时结合（直接地或通过中间齿轮）旋转。 推进发动机被布置成用于控制由燃气涡轮发动机和/或用作电动机或发电机的电机供应到第一和第二风扇的组件的扭矩。

    AIRCRAFT WITH A NACELLE-HOUSED MAIN LANDING GEAR
    69.
    发明申请
    AIRCRAFT WITH A NACELLE-HOUSED MAIN LANDING GEAR 有权
    具有小型主要起落架的飞机

    公开(公告)号：US20160046365A1

    公开(公告)日：2016-02-18

    申请号：US14625776

    申请日：2015-02-19

    Applicant: AIRBUS OPERATIONS, S.L.

    Inventor： Alfonso González Gonzalbo ,  José María Díaz Parrila

    IPC: B64C25/14 ,  B64C3/18 ,  B64C25/34 ,  B64D27/18

    CPC classification number: B64C25/14 ,  B64C3/185 ,  B64C7/02 ,  B64C25/34 ,  B64D27/18

    Abstract: A main landing gear for aircraft having a fuselage, a wing and a jet engine on opposite sides of the fuselage and housed in a nacelle attached to the wing. The main landing gear includes a landing gear at each side of the wing having wheels coupled to a driving device that moves the wheels between stowed and deployed positions. The engine nacelles each include a well located laterally with respect to the jet engines and configured as a housing space for stowing the wheels of the landing gears.

    Abstract translation: 飞机的主要起落架，具有在机身相对两侧的机身，机翼和喷气发动机，并安装在机翼附近的机舱中。 主起落架包括在机翼的每一侧的起落架，其具有联接到驱动装置的轮子，该驱动装置在收起位置和展开位置之间移动车轮。 发动机舱各自包括相对于喷气发动机横向定位的井，并且构造为用于收起起落架的车轮的收容空间。

    Air intake with double inlet door
    70.
    发明授权
    Air intake with double inlet door 有权
    双进气门进气口

    公开(公告)号：US09254925B2

    公开(公告)日：2016-02-09

    申请号：US13628293

    申请日：2012-09-27

    Applicant: AIRBUS OPERATIONS, S.L.

    Inventor： Javier Garcia Nevado ,  Ivan Garcia Lopez ,  Octavio Hernandez Gonzalez

    IPC: B64D41/00 ,  F02C7/04 ,  B64D33/02

    CPC classification number: B64D41/00 ,  B64D2033/0213 ,  Y10T137/0536

    Abstract: An APU air intake having a foldable intake door, including a frame with airfoil profiles. The frame is turned to an aperture angle (α) with respect to the frame support, and each airfoil profile is turned to a profile angle (βi) with respect to the frame. The aperture angle (α) varies from 0° to 22°, and the profile angles (βi) vary from 0° to 110°. The frame is moved by an actuator and the airfoil profiles are operated by extendable rods and secondary rods each secondary rod having rod supports. A latching mechanism is assembled onto each extendable rod, including a rare earth magnet and either a magnet contact plate or a plate with another magnet.

    Abstract translation: 具有可折叠进气门的APU进气门，包括具有翼型的框架。 框架相对于框架支撑件转动为开口角（α），并且每个翼型轮廓相对于框架转向轮廓角（＆lt; bgr i）。 孔径角（α）从0°变化到22°，轮廓角（＆bgr; i）从0°变化到110°。 框架由致动器移动，并且翼型件由可伸展杆和辅助杆操作，每个副杆具有杆支撑件。 闭锁机构组装到每个可延伸杆上，包括稀土磁体和磁体接触板或具有另一个磁体的板。

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