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AIRCRAFT INCLUDING STIFFENER EDGE JUNCTIONS AND METHOD FOR PRODUCING ONE SUCH AIRCRAFT

机译:包括加劲肋边缘的飞机和一种这样的飞机的制造方法

摘要

A system for transmitting stresses at the intersection between a reinforcing frame and a stiffener in a fuselage and to a method for producing one such system. An aircraft fuselage includes stiffeners interrupted by reinforcing frames. At aforementioned interruptions, the stresses experienced by the stiffeners must be transmitted despite the presence of the reinforcing frames. Known solutions are difficult to manufacture and install and do not provide a simple stress transmission path when produced solely from composite materials. In order to solve this problem, the disclosed embodiments include the creation of battens that cover the ends of consecutive sections of a stiffener and the skin of the fuselage, extending under the reinforcing frame in order to join aforementioned two consecutive sections.
机译:一种用于在机身中的加强框架与加劲肋之间的相交处传递应力的系统,以及一种用于制造这种系统的方法。飞机机身包括被加强框架打断的加劲肋。在上述中断处,尽管存在加强框架,但仍必须传递加劲肋所承受的应力。当仅由复合材料制成时,已知的解决方案难以制造和安装,并且不能提供简单的应力传递路径。为了解决该问题,所公开的实施例包括创建覆盖加强件的连续部分的端部和机身的蒙皮的条板,这些条板在加强框架下方延伸以接合上述两个连续的部分。

著录项

  • 公开/公告号EP2209712B1

    专利类型

  • 公开/公告日2011-05-04

    原文格式PDF

  • 申请/专利权人 AIRBUS OPERATIONS (S.A.S);

    申请/专利号EP20080839369

  • 发明设计人 GAUTHIE LAURENT;BERNADET PHILIPPE;

    申请日2008-09-12

  • 分类号B64C1/06;B64C1/12;

  • 国家 EP

  • 入库时间 2022-08-21 17:57:04

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