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    Unitary aircraft windshield with conical single curvature
    1.
    发明授权
    Unitary aircraft windshield with conical single curvature 有权

    公开(公告)号：US11407487B2

    公开(公告)日：2022-08-09

    申请号：US16953832

    申请日：2020-11-20

    Applicant: Airbus Operations SAS

    Inventor： Patrick Lieven ,  Christophe Mialhe ,  Jérôme Phalippou

    IPC: B64C1/14 ,  B64C1/00

    Abstract: A windshield for an aircraft cockpit is provided which includes a glazed windshield part which has a single curvature corresponding to a portion of the envelope of a cone extending between a lower plane and an upper plane which intersect an axis of the cone. The single curvature of the glazed part of the windshield enables the glazed part to be produced more easily, for example by rolling or by hydroforming. It also makes it possible to create configurations for a cockpit for two pilots, a single pilot or even no pilot, on the basis of a single aerodynamic shape of the fuselage of the aircraft by only adapting the structure of the windshield. Also provided are a windshield frame for such a windshield, a windshield assembly including such a windshield frame and such a windshield, and an aircraft equipped with such a windshield.

    Aircraft including a fuselage and a panel removably fixed to the fuselage with the aid of fixing means
    2.
    发明授权
    Aircraft including a fuselage and a panel removably fixed to the fuselage with the aid of fixing means 有权

    公开(公告)号：US12187407B2

    公开(公告)日：2025-01-07

    申请号：US18337139

    申请日：2023-06-19

    Applicant: Airbus Operations SAS

    Inventor： Anthony Mertes ,  Patrick Lieven

    IPC: B64C1/14 ,  B64C1/12

    Abstract: An aircraft including a fuselage including an opening and beams that are aligned and that are interrupted at the edges of the opening, a removable panel where for each pair of aligned beams of the fuselage interrupted at the opening a beam of the removable panel extends between the two beams of the pair and each end of the beam of the removable panel faces an end of a beam of the pair and at the end of at least one beam of the fuselage facing an end of a beam of the removable panel, fixing means providing a removable fixing between the ends.

    Self-stiffened skin for aircraft fuselage including stringers with a closed section and associated manufacturing method
    3.
    发明授权
    Self-stiffened skin for aircraft fuselage including stringers with a closed section and associated manufacturing method 有权
    用于飞机机身的自加强皮肤，包括具有封闭截面的桁条和相关的制造方法

    公开(公告)号：US09446834B2

    公开(公告)日：2016-09-20

    申请号：US14140513

    申请日：2013-12-25

    Applicant: Airbus Operations (SAS)

    Inventor： Patrick Lieven ,  Romain Delahaye

    IPC: B64C1/06 ,  B64C1/12 ,  B29D99/00 ,  B64C1/00

    CPC classification number: B64C1/068 ,  B29D99/0014 ,  B64C1/064 ,  B64C1/12 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T156/1052 ,  Y10T428/13

    Abstract: Simplification of the manufacture of composite material fuselages for aircraft, as well as mass reduction of fuselage sections and space optimization inside such fuselage sections. To accomplish this, it is proposed to use stringers of a new type which have a closed transverse section, and which are thus able to be self-positioned relative to one another by being positioned edge-to-edge on a stringer supporting structure, such as the outer surface of a mandrel. The installation of the stringers in grooves of conjugate shape is by this means made unnecessary. The stringers have cut-outs located between circumferential frames, and are able to house utility systems.

    Abstract translation: 简化飞机复合材料机身的制造，以及机身部分的大量减少和机身部分内的空间优化。 为了实现这一点，提出了使用具有闭合横截面的新型的桁条，并且因此能够通过在纵梁支撑结构上边缘到边缘定位而相对于彼此自定位，例如 作为心轴的外表面。 通过这种方式将桁条安装在共轭形状的槽中是不必要的。 桁条具有位于圆周框架之间的切口，并且能够容纳公用事业系统。

    SUPPORT PLATE FOR THE PASSAGE OF SYSTEMS BETWEEN TWO ZONES WITH DIFFERENT PRESSURIZATIONS OF AN AIRCRAFT
    4.
    发明申请
    SUPPORT PLATE FOR THE PASSAGE OF SYSTEMS BETWEEN TWO ZONES WITH DIFFERENT PRESSURIZATIONS OF AN AIRCRAFT 有权
    在具有不同航空器加压的两个区域之间通过系统的支持板

    公开(公告)号：US20140346276A1

    公开(公告)日：2014-11-27

    申请号：US14285787

    申请日：2014-05-23

    Applicant: Airbus Operations (SAS)

    Inventor： Marc Tomasi ,  Patrick Lieven ,  Romain DELAHAYE ,  Matthieu De Kergommeaux

    IPC: B64C1/10

    CPC classification number: B64C1/10 ,  F16L3/00 ,  F16L5/12

    Abstract: A support plate for the passage of systems between two zones at different pressurizations of an aircraft, in the region of a bulkhead separating the two zones. The support plate comprises a connection plate including at least one retaining element and at least one sealing joint and is provided with a plurality of holes intended for the passage of an assembly of systems which have to pass through said bulkhead.

    Abstract translation: 用于在分离两个区域的隔板区域中用于在飞行器的不同加压的两个区域之间通过系统的支撑板。 支撑板包括连接板，该连接板包括至少一个保持元件和至少一个密封接头，并且设置有多个孔，用于通过必须通过所述隔板的系统组件。

    FRONT STRUCTURE OF AN AIRCRAFT FUSELAGE COMPRISING LANDING GEAR
    5.
    发明申请
    FRONT STRUCTURE OF AN AIRCRAFT FUSELAGE COMPRISING LANDING GEAR 有权
    包含着陆齿轮的飞机配件的前结构

    公开(公告)号：US20130134259A1

    公开(公告)日：2013-05-30

    申请号：US13689324

    申请日：2012-11-29

    Applicant: Airbus Operations (SAS)

    Inventor： Patrick Lieven ,  Pascal Chaumel

    IPC: B64C25/20

    CPC classification number: B64C25/20 ,  B64C1/068 ,  B64C25/14

    Abstract: A front structure of an aircraft fuselage comprising landing gear pivoting about a main shaft and a stay shaft. The front structure also comprises a first reinforcing frame and a second reinforcing frame, the main shaft and the stay shaft being respectively connected to the first and second frames, and a device for the mechanical connection and transfer of forces connecting the stay shaft and the main shaft and transferring to the main shaft a portion of the forces induced by the wheels of the landing gear onto the stay shaft, the second frame and said device being perpendicular to one another.

    Abstract translation: 飞机机身的前部结构，包括围绕主轴和支撑轴枢转的起落架。 前部结构还包括第一加强框架和第二加强框架，主轴和支撑轴分别连接到第一和第二框架，以及用于机械连接和传递连接支撑轴和主体的力的装置 并且将起落架的车轮所引起的力的一部分传递到主轴上，并将第二框架和所述装置彼此垂直。

    On-board meteorological radar having a rotating antenna
    7.
    发明授权
    On-board meteorological radar having a rotating antenna 有权
    具有旋转天线的车载气象雷达

    公开(公告)号：US09377529B2

    公开(公告)日：2016-06-28

    申请号：US14252209

    申请日：2014-04-14

    Applicant: Airbus Operations (SAS)

    Inventor： Patrick Lieven

    IPC: G01S13/95 ,  G01S13/88 ,  H01Q3/02 ,  H01Q1/28 ,  H01Q3/04 ,  H01Q19/17 ,  H01Q19/19 ,  G01S7/02

    CPC classification number: G01S13/953 ,  G01S13/882 ,  G01S2007/027 ,  H01Q1/281 ,  H01Q3/02 ,  H01Q3/04 ,  H01Q19/17 ,  H01Q19/19 ,  Y02A90/18

    Abstract: A meteorological radar installed on board an aircraft, including a mechanical support fixed to a bulkhead of a nose of the aircraft, wherein an antenna is mounted on the mechanical support to enable turning mobility around an axis of rotation. The antenna includes a pedestal, on which at least one blade, extending radially along the axis of rotation, is installed. A free side of the blade, along which a plurality of radiating elements is distributed, perceptibly has the shape of a portion of conic in a plane including the axis of rotation. Because the blade is mobile only in rotation along the axis of rotation, and the selection of the emission/reception direction is performed electronically, not mechanically, the space and length requirements of the meteorological radar are fixed, whether the meteorological radar is in operation or not, and are determined based on the eccentricity and parameter of the conic.

    Abstract translation: 安装在飞机上的气象雷达，包括固定到飞机鼻部的隔板的机械支撑，其中天线安装在机械支撑件上，以实现围绕旋转轴的转动移动。 天线包括基座，其上安装有沿旋转轴线径向延伸的至少一个叶片。 沿着多个辐射元件分布的叶片的自由侧可感知地具有在包括旋转轴线的平面中的锥体的一部分的形状。 因为叶片只能沿着旋转轴线旋转移动，并且电子地而不是机械地执行发射/接收方向的选择，气象雷达的空间和长度要求是固定的，无论气象雷达是在运行还是 不是，并且基于圆锥的偏心度和参数确定。

    SELF-STIFFENED SKIN FOR AIRCRAFT FUSELAGE INCLUDING STRINGERS WITH A CLOSED SECTION AND ASSOCIATED MANUFACTURING METHOD
    9.
    发明申请
    SELF-STIFFENED SKIN FOR AIRCRAFT FUSELAGE INCLUDING STRINGERS WITH A CLOSED SECTION AND ASSOCIATED MANUFACTURING METHOD 有权
    用于飞机融合的自强式皮肤，包括具有封闭部分的STRINGERS和相关制造方法

    公开(公告)号：US20140186559A1

    公开(公告)日：2014-07-03

    申请号：US14140513

    申请日：2013-12-25

    Applicant: Airbus Operations (SAS)

    Inventor： Patrick Lieven ,  Romain Delahaye

    IPC: B64C1/06 ,  B29D99/00

    CPC classification number: B64C1/068 ,  B29D99/0014 ,  B64C1/064 ,  B64C1/12 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T156/1052 ,  Y10T428/13

    Abstract: Simplification of the manufacture of composite material fuselages for aircraft, as well as mass reduction of fuselage sections and space optimization inside such fuselage sections. To accomplish this, it is proposed to use stringers of a new type which have a closed transverse section, and which are thus able to be self-positioned relative to one another by being positioned edge-to-edge on a stringer supporting structure, such as the outer surface of a mandrel. The installation of the stringers in grooves of conjugate shape is by this means made unnecessary. The stringers have cut-outs located between circumferential frames, and are able to house utility systems.

    Abstract translation: 简化飞机复合材料机身的制造，以及机身部分的大量减少和机身部分内的空间优化。 为了实现这一点，提出了使用具有闭合横截面的新型的桁条，并且因此能够通过在纵梁支撑结构上边缘到边缘定位而相对于彼此自定位，例如 作为心轴的外表面。 通过这种方式将桁条安装在共轭形状的槽中是不必要的。 桁条具有位于圆周框架之间的切口，并且能够容纳公用事业系统。

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