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7 条记录 (耗时 0.01 秒)

    Emergency opening system for an aircraft cabin door
    1.
    发明公开
    Emergency opening system for an aircraft cabin door 有权
    NotfallöffnungssystemfüreineFlugzeugkabinentür

    公开(公告)号：EP2644495A1

    公开(公告)日：2013-10-02

    申请号：EP12400008.4

    申请日：2012-03-27

    申请人： Eurocopter Deutschland GmbH

    发明人： Kress, Denis ,  Pichlmaier, Claus ,  Kirchner, Marc ,  Wolf, Christian

    IPC分类号： B64C1/14

    CPC分类号： B64C1/1423 ,  B64C1/1407 ,  B64C1/143

    摘要： The invention is related to an emergency opening system (1) of an aircraft cabin door (3) mounted in an aircraft fuselage structure (4) by means of a hinge arm (2). An actuator (7), designed to assist the opening of the aircraft cabin door (3) against the force of gravity by means of a gas operated actuating rod (8) is mounted with its fix end (9) to said hinge arm (2) and said actuating rod (8) is connected to an actuator joint (10). A fork lever (24) is linked to said actuator joint (10). A bell crank (13) is respectively pivotable mounted to said hinge arm (2) and to said actuator joint (10) for the fork lever (24). At least one coupling lever (12) is pivotable joint to said fork lever (24) at at least one coupling joint (14). Said at least one coupling lever (12) is mounted in at least one hinge (18) of the hinge arm (2) by means of a respective bolt (26), said bolt (26) being drivingly connected to said aircraft cabin door (3) for rotation of said aircraft cabin door (3).

    摘要翻译： 本发明涉及通过铰链臂（2）安装在飞行器机身结构（4）中的飞机机舱门（3）的紧急开启系统（1）。 一个致动器（7），其设计成通过气动操作的致动杆（8）抵抗重力来协助飞机机舱门（3）的打开，其固定端（9）安装到所述铰链臂（2） ），并且所述致动杆（8）连接到致动器接头（10）。 叉杆（24）连接到所述致动器接头（10）。 钟形曲柄（13）分别可枢转地安装到所述铰链臂（2）和用于叉杆（24）的所述致动器接头（10）。 至少一个联接杆（12）在至少一个联接接头（14）处可转动地连接到所述叉杆（24）。 所述至少一个联接杆（12）通过相应的螺栓（26）安装在所述铰链臂（2）的至少一个铰链（18）中，所述螺栓（26）被驱动地连接到所述飞机机舱门 3）用于所述飞机机舱门（3）的旋转。

    Loads interface, particularly a loads interface of an aircraft structure
    7.
    发明公开
    Loads interface, particularly a loads interface of an aircraft structure 有权
    加载界面，特别是飞机结构的加载界面

    公开(公告)号：EP2554471A1

    公开(公告)日：2013-02-06

    申请号：EP11400038.3

    申请日：2011-08-01

    申请人： Eurocopter Deutschland GmbH

    发明人： Wolf, Christian ,  Niemann, Hanno ,  Hopf, Matthias ,  Schmiedel, Patrik

    IPC分类号： B64C1/14 ,  E05D5/02

    CPC分类号： B64C1/1407 ,  E05D5/0207

    摘要： The invention relates to a loads interface (1) of an aircraft structure with an edge member (6) and a background structure both preferably made from fibre reinforced plastics. A loads transferring flange (2) is adapted and mounted to said edge member (6) to transmit bending moments into the background structure. Said loads transferring flange (2) is provided with two angled upper and lower planes (8, 9). Said edge member (6) is provided with two angled edge member's upper and lower transfer planes (10, 11). The two angled upper and lower planes (8, 9) and the two angled edge member's upper and lower transfer planes (10, 11) are paired essentially parallel and respectively oriented to each other with an angle of approximately 90°. The invention relates as well to applications of such a loads interface (1).

    摘要翻译： 本发明涉及具有优选由纤维增强塑料制成的边缘构件（6）和背景结构的飞机结构的载荷界面（1）。 载荷传递凸缘（2）适于并安装到所述边缘构件（6）上以将弯矩传递到背景结构中。 所述载荷传递凸缘（2）设置有两个成角度的上平面和下平面（8,9）。 所述边缘构件（6）设置有两个成角度的边缘构件的上和下传送平面（10,11）。 两个成角度的上和下平面（8,9）和两个成角度的边缘构件的上和下转印平面（10,11）基本平行配对并且分别以大约90°的角度彼此定位。 本发明还涉及这种负载接口（1）的应用。