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    SECURE BEAM, IN PARTICULAR STRONG FRAME OF FUSELAGE, AND AIRCRAFT FUSELAGE PROVIDED WITH SUCH FRAMES
    1.
    发明申请
    SECURE BEAM, IN PARTICULAR STRONG FRAME OF FUSELAGE, AND AIRCRAFT FUSELAGE PROVIDED WITH SUCH FRAMES 审中-公开
    安全梁，特别是紧固的框架，以及提供这种框架的飞机熔接

    公开(公告)号：US20130157017A1

    公开(公告)日：2013-06-20

    申请号：US13714789

    申请日：2012-12-14

    申请人： Airbus Operations (SAS)

    发明人： Julien Guillemaut ,  Guillaume Gallant ,  Jerome Colmagro

    IPC分类号： B64C1/06

    CPC分类号： B64C1/062 ,  B64C1/061 ,  Y10T428/24612 ,  Y10T428/24628 ,  Y10T428/249923

    摘要： An arrangement for freeing the structures of fail-safe type from the damage tolerance criterion and to allow a significantly improved fatigue resistance, while producing a weight saving. This is provided by forming a composite hybrid structure in a configuration that makes it possible to combine the advantages of metal and of composite material. In a secure hybrid structure, at least two longitudinal structural spars are joined back to back by fastening means. One of the spars is metal and equipped with stability partitions, whereas another spar is made of a composite material with carbon fibers oriented in the direction of the forces to be predicted such that this spar exhibits a rigidity equivalent to that of the metal spar.

    摘要翻译： 一种用于从故障公差标准中释放故障安全型结构并允许显着提高耐疲劳性的装置，同时节省重量。 这通过形成能够结合金属和复合材料的优点的构造的复合混合结构来提供。 在安全的混合结构中，至少两个纵向结构翼梁通过紧固装置背对背连接。 其中一个翼梁是金属并具有稳定的隔板，而另一个翼梁由复合材料制成，碳纤维沿着待预测的力的方向定向，使得该翼梁具有与金属翼梁相当的刚度。

    Thrust reverser system limiting aerodynamic perturbation in an inactive configuration
    2.
    发明授权
    Thrust reverser system limiting aerodynamic perturbation in an inactive configuration 有权

    公开(公告)号：US10519899B2

    公开(公告)日：2019-12-31

    申请号：US15693735

    申请日：2017-09-01

    申请人： Airbus Operations (SAS)

    发明人： Olivier Pautis ,  Jerome Colmagro

    IPC分类号： F02K1/72 ,  F02K1/76

    摘要： A thrust reverser system with a thrust reverser cascade and a reverser door with door segments laid out in a folded condition relatively to each other in an inactive configuration of the reverser system, and accommodated in an accommodation space located outside the secondary channel. Upon passing from the inactive configuration to the active configuration a rearward displacement of the cascade towards a nacelle aperture, released by an external movable nacelle cowl driven rearwards by the cascade, and a deployment of segments until they attain a deployed closing position within the secondary channel occurs simultaneously.

    Aircraft nacelle comprising at least one fan cowl door which is mounted so as to be able to rotate about the longitudinal axis of the nacelle
    4.
    发明授权
    Aircraft nacelle comprising at least one fan cowl door which is mounted so as to be able to rotate about the longitudinal axis of the nacelle 有权

    公开(公告)号：US10144500B2

    公开(公告)日：2018-12-04

    申请号：US15160579

    申请日：2016-05-20

    申请人： Airbus Operations (SAS)

    发明人： Olivier Pautis ,  Jerome Colmagro

    IPC分类号： B64C7/02 ,  B64D29/08 ,  B64D27/26 ,  B64D29/06

    摘要： A nacelle having a longitudinal axis and comprising a chassis, two articulated fan cowl doors and a sliding fan cowl door. Each articulated fan cowl door is rotatably mounted in an upper portion of the chassis, each about their own opening axis. The opening axes are parallel to the longitudinal axis. The articulated doors pivot between a closed position and an open position. The sliding fan cowl door, in its closed position, is placed between free edges of the articulated fan cowl doors. A sliding arrangement for the sliding door is configured such that, in the open position of either articulated door, the sliding fan cowl door can rotate about the longitudinal axis. The nacelle has fan cowl doors which take up less space when in the open position and which are more compact, in comparison to articulated fan cowl doors without a sliding fan cowl door.

    Aircraft nacelle comprising at least one fan cowl door which is mounted so as to be able to rotate about the longitudinal axis of the nacelle
    8.
    发明申请
    Aircraft nacelle comprising at least one fan cowl door which is mounted so as to be able to rotate about the longitudinal axis of the nacelle 审中-公开
    飞机机舱包括至少一个风扇整流罩门，其安装成能够围绕机舱的纵向轴线旋转

    公开(公告)号：US20160340024A1

    公开(公告)日：2016-11-24

    申请号：US15160579

    申请日：2016-05-20

    申请人： Airbus Operations (SAS)

    发明人： Olivier Pautis ,  Jerome Colmagro

    IPC分类号： B64C7/02 ,  B64D27/26 ,  B64D29/08 ,  B64D29/06

    CPC分类号： B64C7/02 ,  B64D27/26 ,  B64D29/06 ,  B64D29/08 ,  F05D2230/72

    摘要： A nacelle having a longitudinal axis and comprising a chassis, two articulated fan cowl doors and a sliding fan cowl door. Each articulated fan cowl door is rotatably mounted in an upper portion of the chassis, each about their own opening axis. The opening axes are parallel to the longitudinal axis. The articulated doors pivot between a closed position and an open position. The sliding fan cowl door, in its closed position, is placed between free edges of the articulated fan cowl doors. A sliding arrangement for the sliding door is configured such that, in the open position of either articulated door, the sliding fan cowl door can rotate about the longitudinal axis. The nacelle has fan cowl doors which take up less space when in the open position and which are more compact, in comparison to articulated fan cowl doors without a sliding fan cowl door.

    摘要翻译： 具有纵向轴线并且包括底盘的机舱，两个铰接式风扇整流罩门和滑动风扇整流罩门。 每个铰接式风扇整流罩门可旋转地安装在底盘的上部，每个围绕其自身的开口轴线。 开口轴线平行于纵向轴线。 铰接门在关闭位置和打开位置之间枢转。 在其关闭位置的滑动风扇整流罩门被放置在铰接式风扇整流罩门的自由边缘之间。 用于滑动门的滑动装置构造成使得在铰接门的打开位置中，滑动风扇整流罩门可围绕纵向轴线旋转。 机舱具有风扇整流罩门，当处于打开位置时占用更少的空间，并且与没有滑动风扇整流罩门的铰接式风扇罩相比更紧凑。