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LEADING-EDGE STRUCTURE FOR AIRCRAFT, WING FOR AIRCRAFT, AND AIRCRAFT

机译:飞机,飞机机翼和飞机的前沿结构

摘要

PROBLEM TO BE SOLVED: To provide an aircraft front edge structure that, when colliding with a flying object, can effectively absorb collision energy from the flying object without causing an increase in weight.;SOLUTION: An aircraft front edge structure 10 includes: a beam 11 extending in a predetermined direction; multiple ribs 13 provided while having an interval in the predetermined direction of the beam 11; and an outer cover 17 supported by the multiple ribs 13. The multiple ribs 13 include: first ribs 14; multiple second ribs 15 disposed between a pair of first ribs 14, 14. The second ribs 15 do not support the outer cover in the vicinity of a front end.;SELECTED DRAWING: Figure 2;COPYRIGHT: (C)2017,JPO&INPIT
机译:要解决的问题:提供一种飞机前缘结构,当其与飞行物体碰撞时,可以有效吸收飞行物的碰撞能量而不会导致重量增加。解决方案:飞机前缘结构10包括:梁11沿预定方向延伸;多个肋13设置成在梁11的预定方向上具有间隔。多个肋13包括:第一肋14;和由多个肋13支撑的外盖17。多个第二肋15设置在一对第一肋14、14之间。第二肋15在前端附近不支撑外盖。选图:图2;版权:(C)2017,JPO&INPIT

著录项

  • 公开/公告号EP3135578B1

    专利类型

  • 公开/公告日2018-11-07

    原文格式PDF

  • 申请/专利权人 MITSUBISHI AIRCRAFT CORPORATION;

    申请/专利号EP20160184482

  • 发明设计人 TACHIBANA KAZUKI;HARA KOHEI;

    申请日2016-08-17

  • 分类号B64C3/28;

  • 国家 EP

  • 入库时间 2022-08-21 13:19:22

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