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    Tool for the production of fiber composite components
    1.
    发明申请
    Tool for the production of fiber composite components 审中-公开
    用于生产纤维复合材料的工具

    公开(公告)号：US20080044506A1

    公开(公告)日：2008-02-21

    申请号：US11893028

    申请日：2007-08-14

    申请人： Pierre Zahlen ,  Clemens Heim ,  Jan Roettjer ,  Axel Herrmann

    发明人： Pierre Zahlen ,  Clemens Heim ,  Jan Roettjer ,  Axel Herrmann

    IPC分类号： B29C70/36

    CPC分类号： B29C70/443 ,  B29C70/548

    摘要： The present invention provides a tool for the production of fiber composite components. The tool has a surface for depositing semifinished fiber products on the surface, the surface having a number of openings for feeding a matrix to the deposited semifinished fiber products. It is consequently possible to dispense entirely or partly with a conventional flow promoter and possible to achieve a high quality of fiber composite component.

    摘要翻译： 本发明提供了一种用于生产纤维复合材料组件的工具。 该工具具有用于在表面上沉积半成品纤维产品的表面，该表面具有用于将基质供给到沉积的半成品纤维产品的许多开口。 因此，可以完全或部分地用常规流动促进剂分配并且可能实现高质量的纤维复合材料组分。

    Process for producing fibre preforms
    5.
    发明授权
    Process for producing fibre preforms 有权
    生产纤维预制件的工艺

    公开(公告)号：US08771567B2

    公开(公告)日：2014-07-08

    申请号：US12903867

    申请日：2010-10-13

    申请人： Joachim Piepenbrock ,  Carsten Barlag ,  Pierre Zahlen ,  Bernd Wohlmann ,  Markus Schneider

    发明人： Joachim Piepenbrock ,  Carsten Barlag ,  Pierre Zahlen ,  Bernd Wohlmann ,  Markus Schneider

    IPC分类号： B32B37/00

    CPC分类号： B29B11/16

    摘要： A process for producing fiber preforms for composite material components makes it possible to directly produce complex geometries in a flexible and low-cost manner by applying a plurality of dry fiber rovings independently of one another even in spatially uneven contours. It is no longer necessary to use cut fabric strips since fiber preforms are produced straight from the dry fiber rovings. This obviates the need to carry out production, transport and order picking processes. It is not necessary to cut fiber strips to size, and therefore a saving may be made on material. In addition, it is possible to increase the mechanical characteristic values in the composite material because it is not necessary to sew fiber webs. The described process can also readily be scaled since the number of dry fiber rovings arranged next to one another make it possible to vary the area which can be covered.

    摘要翻译： 用于生产复合材料部件的纤维预制件的方法使得可以以柔性和低成本的方式直接制造复杂的几何形状，即使在空间不均匀的轮廓中彼此独立地施加多个干纤维粗纱。 不需要使用切割织物条，因为纤维预制件直接从干纤维粗纱生产。 这样就不需要进行生产，运输和订单拣选过程。 不需要将纤维条切割成尺寸，因此可以节省材料。 此外，由于不需要缝合纤维网，因此可以增加复合材料中的机械特性值。 所描述的方法也可以容易地缩放，因为彼此相邻布置的干纤维粗纱的数量使得可以改变可被覆盖的面积。

    Method for producing a fiber composite component for aviation and spaceflight
    6.
    发明授权
    Method for producing a fiber composite component for aviation and spaceflight 有权
    航空航天纤维复合材料制造方法

    公开(公告)号：US09492974B2

    公开(公告)日：2016-11-15

    申请号：US12309015

    申请日：2007-07-04

    申请人： Pierre Zahlen ,  Torben Jacob

    发明人： Pierre Zahlen ,  Torben Jacob

    IPC分类号： B29C70/44 ,  B29C33/48 ,  B29C33/44 ,  B29C33/52 ,  B29C33/50 ,  B29C70/30 ,  B29C43/36 ,  B29L31/30

    CPC分类号： B29C70/446 ,  B29C33/448 ,  B29C33/485 ,  B29C33/505 ,  B29C33/52 ,  B29C70/30 ,  B29C70/443 ,  B29C2043/3644 ,  B29C2043/3668 ,  B29L2031/3082 ,  Y02T50/43

    摘要： A method for producing a fiber composite component, in particular for aerospace, includes the following method steps: introducing an elastic core sleeve into a prestressing mechanism; expanding the core sleeve that is introduced, for elastic prestressing of the same, by activating the prestressing mechanism; introducing a core body through an opening of the expanded core sleeve; releasing the core sleeve by deactivating the prestressing mechanism, for the snug enclosing of the core body by the core sleeve and thus for the forming of the molding core (14); and at least partly laying at least one semifinished fiber product on the molding core that is formed, for the shaping of the fiber composite component to be produced.

    摘要翻译： 特别是用于航空航天的纤维复合部件的制造方法，包括以下方法步骤：将弹性芯套筒引入预应力机构; 通过启动预应力机构，扩大引入的芯套，用于弹性预应力; 通过所述膨胀的芯套的开口引入芯体; 通过使预应力机构失效来释放芯套筒，以便通过芯套筒紧密地包住芯体，从而形成模芯（14）; 并且至少部分地将至少一个半成品纤维产品放置在所形成的成型芯上，用于成形要生产的纤维复合材料部件。

    Method For Producing a Fiber Composite Component For Aviation and Spaceflight
    8.
    发明申请
    Method For Producing a Fiber Composite Component For Aviation and Spaceflight 有权
    用于航空和航天飞行器生产光纤复合材料的方法

    公开(公告)号：US20100044912A1

    公开(公告)日：2010-02-25

    申请号：US12309015

    申请日：2007-07-04

    申请人： Pierre Zahlen ,  Torben Jacob

    发明人： Pierre Zahlen ,  Torben Jacob

    IPC分类号： B29C70/44 ,  B29C33/50

    CPC分类号： B29C70/446 ,  B29C33/448 ,  B29C33/485 ,  B29C33/505 ,  B29C33/52 ,  B29C70/30 ,  B29C70/443 ,  B29C2043/3644 ,  B29C2043/3668 ,  B29L2031/3082 ,  Y02T50/43

    摘要： A method for producing a fiber composite component, in particular for aerospace, includes the following method steps: introducing an elastic core sleeve into a prestressing mechanism; expanding the core sleeve that is introduced, for elastic prestressing of the same, by activating the prestressing mechanism; introducing a core body through an opening of the expanded core sleeve; releasing the core sleeve by deactivating the prestressing mechanism, for the snug enclosing of the core body by the core sleeve and thus for the forming of the molding core (14); and at least partly laying at least one semifinished fiber product on the molding core that is formed, for the shaping of the fiber composite component to be produced.

    摘要翻译： 特别是用于航空航天的纤维复合部件的制造方法，包括以下方法步骤：将弹性芯套筒引入预应力机构; 通过启动预应力机构，扩大引入的芯套，用于弹性预应力; 通过所述膨胀的芯套的开口引入芯体; 通过使预应力机构失效来释放芯套筒，以便通过芯套筒紧密地包住芯体，从而形成模芯（14）; 并且至少部分地将至少一个半成品纤维产品放置在所形成的成型芯上，用于成形要生产的纤维复合材料部件。

    Pressure fuselage of an aircraft or spacecraft with pressure calotte
    10.
    发明授权
    Pressure fuselage of an aircraft or spacecraft with pressure calotte 失效
    具有压力的飞机或航天器的压力机身

    公开(公告)号：US08702038B2

    公开(公告)日：2014-04-22

    申请号：US12845012

    申请日：2010-07-28

    申请人： Richard Bauer ,  Pierre Zahlen

    发明人： Richard Bauer ,  Pierre Zahlen

    IPC分类号： B64C1/10

    CPC分类号： B64C1/10

    摘要： A pressure fuselage of an aircraft or a spacecraft includes at least two fuselage sections disposed longitudinally along the fuselage; at least one pressure calotte disposed in the fuselage so as to form a pressurized area; and an arcuate frame profile having a Y-shaped cross-section with a long profile leg connected to at least one of the at least two fuselage sections and a short profile leg extending at an acute angle from the long profile leg toward an inside of the at least two fuselage sections and attached to the at least one pressure calotte.

    摘要翻译： 飞机或航天器的压力机身包括至少两个沿机身纵向设置的机身部分; 设置在机身中的至少一个压力杯，以形成加压区域; 以及弓形框架轮廓，其具有Y形横截面，其具有连接到所述至少两个机身部分中的至少一个的长型腿，以及从所述长型腿朝向所述长型轮的内侧以锐角延伸的短型腿 至少两个机身部分并连接到所述至少一个压力辊。