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203 条记录 (耗时 0.023 秒)

    Method and apparatus for manufacturing a shell component for an aircraft or spacecraft
    1.
    发明授权
    Method and apparatus for manufacturing a shell component for an aircraft or spacecraft 有权

    公开(公告)号：EP2905221B1

    公开(公告)日：2018-07-04

    申请号：EP14154486.6

    申请日：2014-02-10

    申请人： Airbus Operations GmbH

    发明人： Brunner, Stefan ,  Schulze, Wolfgang ,  Tiryaki, Memis ,  Eilken, Wolfgang

    IPC分类号： B64C1/12 ,  B64C3/26 ,  B64F5/00

    CPC分类号： B64C1/12 ,  B23P2700/01 ,  B64C1/068 ,  B64C3/26 ,  B64F5/10 ,  B64G1/22 ,  Y10T29/49622 ,  Y10T29/5397

    摘要： The present invention provides a method of manufacturing a shell component for an aircraft or spacecraft. The method comprises a step of positioning a skin panel (102), which includes a skin (104) of the aircraft or spacecraft and first and second stringers (111,112) stiffening the skin, opposite a frame (106) having first and second mouseholes (121,122) for receiving the first and second stringers, a step of elastically bending the skin panelm (102), a step of inserting the first stringer (111) into the first mousehole (121), and a step of releasing the elastic bend to insert the second stringer (112) into the second mousehole (122). Under a further aspect, the invention provides an apparatus (200) for manufacturing a shell component for an aircraft or spacecraft, comprising a positioning unit (203) for positioning a skin panel (102), whic h includes a skin (104) of the aircraft or spacecraft and first and second stringers (111,112) stiffening the skin, opposite a frame (106) having first and second mouseholes (121,122) for receiving the first and second stringers (111,112), a bending unit (204) for elastically bending the skin panel (102), an inserting unit (202) for inserting the first stringer (111) into the first mousehole (121), and a control unit (208), which controls the bending unit (204) to release the elastic bend in order to insert the second stringer (112) into the second mousehole (122).

    SPACE SHUTTLE ORBITER AND RETURN SYSTEM
    4.
    发明公开
    SPACE SHUTTLE ORBITER AND RETURN SYSTEM 审中-公开
    航天飞机轨道飞行器和反向系统

    公开(公告)号：EP2989008A4

    公开(公告)日：2017-03-08

    申请号：EP14787564

    申请日：2014-04-15

    申请人： BIOSPHERE AEROSPACE LLC

    发明人： HELOU ELIE

    IPC分类号： B64G1/64

    CPC分类号： B64G1/005 ,  B64G1/002 ,  B64G1/14 ,  B64G1/22 ,  B64G1/222 ,  B64G1/40 ,  B64G1/401 ,  B64G1/403 ,  B64G1/58 ,  B64G1/62 ,  B64G2001/1092

    摘要： A launch system comprises a nose section comprising a nose coupling surface, a tail section comprising a tail coupling surface facing the nose coupling surface and a mast coupling the nose and tail sections. The mast is configured to expand and retract to displace the nose and tail sections within a range of distances from one another. In a retracted state, the nose and tail sections are either structurally coupled to one another at the nose and tail coupling surfaces or structurally coupled to at least one integrated module located between the nose and the tail sections.

    Panel structure and associated method
    5.
    发明公开
    Panel structure and associated method 审中-公开
    Plattenstruktur undzugehörigesVerfahren

    公开(公告)号：EP3009344A1

    公开(公告)日：2016-04-20

    申请号：EP14189185.3

    申请日：2014-10-16

    申请人： Airbus Operations GmbH

    发明人： Seack, Oliver

    IPC分类号： B64C1/12 ,  B64C1/10 ,  B64C3/22

    CPC分类号： B64C1/064 ,  B33Y10/00 ,  B33Y80/00 ,  B64C1/10 ,  B64C1/12 ,  B64C3/22 ,  B64G1/22

    摘要： The invention relates to a panel structure (1) for a vehicle, and especially for an aircraft (A) or spacecraft, comprising: an area member (2), especially a skin member, that defines an areal expanse with a first surface (3) and an opposite second surface (4) and having a thickness (5) between the first and second surfaces (3, 4); and a plurality of elongate stiffener members (6) which are attached to the area member (2) and extend over at least one of the first and second surfaces (3, 4); wherein at least one of the stiffener members (6) is bifurcated at a bifurcation point (P) into two or more branch stiffener members (6'). The invention also provides a method of producing such a panel structure (1).

    摘要翻译： 本发明涉及一种用于车辆，特别是用于飞行器（A）或航天器的面板结构（1），其包括：区域构件（2），特别是皮肤构件，其限定具有第一表面（3 ）和相对的第二表面（4），并且在第一和第二表面（3,4）之间具有厚度（5）; 和多个细长的加强件（6），它们附接到区域部件（2）并在第一和第二表面（3,4）中的至少一个上延伸; 其中所述加强件（6）中的至少一个在分叉点（P）处分叉成两个或更多个分支加强件（6'）。 本发明还提供一种制造这种面板结构（1）的方法。

    SPACE SHUTTLE ORBITER AND RETURN SYSTEM
    6.
    发明公开
    SPACE SHUTTLE ORBITER AND RETURN SYSTEM 审中-公开
    RAUMFÄHRENORBITERUND UMKEHRSYSTEM

    公开(公告)号：EP2989008A1

    公开(公告)日：2016-03-02

    申请号：EP14787564.5

    申请日：2014-04-15

    申请人： Biosphere Aerospace LLC

    发明人： HELOU, Elie

    IPC分类号： B64G1/64

    CPC分类号： B64G1/005 ,  B64G1/002 ,  B64G1/14 ,  B64G1/22 ,  B64G1/222 ,  B64G1/40 ,  B64G1/401 ,  B64G1/403 ,  B64G1/58 ,  B64G1/62 ,  B64G2001/1092

    摘要： A launch system comprises a nose section comprising a nose coupling surface, a tail section comprising a tail coupling surface facing the nose coupling surface and a mast coupling the nose and tail sections. The mast is configured to expand and retract to displace the nose and tail sections within a range of distances from one another. In a retracted state, the nose and tail sections are either structurally coupled to one another at the nose and tail coupling surfaces or structurally coupled to at least one integrated module located between the nose and the tail sections.

    摘要翻译： 发射系统包括鼻部，其包括鼻部联接表面，尾部包括面向鼻部联接表面的尾部联接表面和连接鼻部和尾部的杆。 桅杆被配置成展开和缩回以在彼此的距离范围内移动鼻部和尾部。 在缩回状态下，鼻部和尾部部分在结构上在鼻部和尾部联接表面处彼此联接，或者结构上耦合到位于鼻部和尾部之间的至少一个集成模块。

    Method and apparatus for manufacturing a shell component for an aircraft or spacecraft
    7.
    发明公开
    Method and apparatus for manufacturing a shell component for an aircraft or spacecraft 有权
    用于生产壳结构用于飞行器或航天器的方法和装置

    公开(公告)号：EP2905221A1

    公开(公告)日：2015-08-12

    申请号：EP14154486.6

    申请日：2014-02-10

    申请人： Airbus Operations GmbH

    发明人： Brunner, Stefan ,  Schulze, Wolfgang ,  Tiryaki, Memis ,  Eilken, Wolfgang

    IPC分类号： B64C1/12 ,  B64C3/26 ,  B64F5/00

    CPC分类号： B64C1/12 ,  B23P2700/01 ,  B64C1/068 ,  B64C3/26 ,  B64F5/10 ,  B64G1/22 ,  Y10T29/49622 ,  Y10T29/5397

    摘要： The present invention provides a method of manufacturing a shell component for an aircraft or spacecraft. The method comprises a step of positioning a skin panel (102), which includes a skin (104) of the aircraft or spacecraft and first and second stringers (111,112) stiffening the skin, opposite a frame (106) having first and second mouseholes (121,122) for receiving the first and second stringers, a step of elastically bending the skin panelm (102), a step of inserting the first stringer (111) into the first mousehole (121), and a step of releasing the elastic bend to insert the second stringer (112) into the second mousehole (122). Under a further aspect, the invention provides an apparatus (200) for manufacturing a shell component for an aircraft or spacecraft, comprising a positioning unit (203) for positioning a skin panel (102), whic h includes a skin (104) of the aircraft or spacecraft and first and second stringers (111,112) stiffening the skin, opposite a frame (106) having first and second mouseholes (121,122) for receiving the first and second stringers (111,112), a bending unit (204) for elastically bending the skin panel (102), an inserting unit (202) for inserting the first stringer (111) into the first mousehole (121), and a control unit (208), which controls the bending unit (204) to release the elastic bend in order to insert the second stringer (112) into the second mousehole (122).

    摘要翻译： 本发明提供了制造的壳成分，用于在飞机或航天器的方法。 该方法包括定位蒙皮面板（102），其包括硬化的皮肤的飞机或航天器以及第一和第二纵梁（111112）的皮肤（104），一个框架（106）相对的具有第一的工序和第二鼠洞（ 121122），用于接收所述第一和第二纵梁的，可弹性的步骤弯曲皮肤panelm（102），将所述第一桁（111）到所述第一鼠洞（121）的步骤，和释放所述弹性弯曲，以插入的步骤 第二纵梁（112）到第二鼠洞（122）。 下一个另外的方面，本发明提供一种用于制造外壳部件用于在飞机或航天器，用于定位皮肤面板（102）包括定位部（203）的装置（200），其中H包括的皮肤（104） 飞机或航天器以及第一和第二纵梁（111112）加强皮肤，相对的具有框架（106）的第一和第二鼠标的孔（121,122），用于接收所述第一和第二纵梁（111112），弯曲部（204），用于弹性地弯曲所述 用于插入第一纵梁（111）到所述第一鼠洞（121）插入单元（202）的蒙皮壁板（102），以及控制所述弯曲部（204）的控制单元（208），以释放所述弹性弯曲在 为了插入第二纵梁（112）到第二鼠洞（122）。

    Fibre reinforced plastic profiles having sections with different fibre types
    9.
    发明公开
    Fibre reinforced plastic profiles having sections with different fibre types 审中-公开
    FaserverstärkteKunststoffprofile mit Abschnitten mit unterschiedlichen Fasertypen

    公开(公告)号：EP2767388A1

    公开(公告)日：2014-08-20

    申请号：EP13155436.2

    申请日：2013-02-15

    申请人： Airbus Operations GmbH

    发明人： Werner, Sven

    IPC分类号： B29D99/00 ,  B29C70/30 ,  B29L31/30

    CPC分类号： B64C1/00 ,  B29C70/30 ,  B29D99/0007 ,  B29L2031/3076 ,  B32B5/12 ,  B64G1/22 ,  Y02T50/43 ,  Y10T428/24942 ,  Y10T428/24992 ,  Y10T428/249922

    摘要： The present invention pertains to a fibre reinforced plastic profile, in particular for an aircraft or spacecraft, comprising a stacked ply assembly including a plurality of stacked plies each comprising fibre material, the ply assembly having a profile cross section comprising at least one first section, at least one second section, and at least one splice section located between the at least one first section and the at least one second section. The splice section includes a first plurality of stacked plies having fibres of a first fibre material and a second plurality of stacked plies having fibres of a second fibre material. In the splice section, respective plies of the first plurality of stacked plies are intertwiningly abutted with respective plies of the second plurality of stacked plies.

    摘要翻译： 本发明涉及一种纤维增强塑料型材，特别是用于飞行器或航天器，其包括层叠的层叠组件，该层叠组件包括多个堆叠的层，每层包括纤维材料，该层叠组件具有包括至少一个第一部分的轮廓横截面， 至少一个第二部分，以及位于所述至少一个第一部分和所述至少一个第二部分之间的至少一个接合部分。 接头部分包括具有第一纤维材料的纤维的第一多个堆叠层和具有第二纤维材料的纤维的第二多个堆叠层。 在接头部分中，第一多个堆叠层的相应层相互缠绕在第二多个层叠层的相应层中。