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Failure of CFRP airframe sandwich panels under crash-relevant loading conditions

机译:CFRP机体夹芯板在与碰撞相关的载荷条件下失效

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摘要

New aircraft fuselage concepts have to prove equivalent crashworthiness standards compared to conventional metallic fuselages for certification. Brittle failure mechanisms of CFRP structures make the verification of equivalent crashworthiness for novel CFRP fuselage concepts challenging since conventional metal fuselages absorb a significant part of the kinetic energy by plasticization. In this context, the damage initiation and failure of twin-walled fuselage panels were investigated under crash relevant bending-compression loads. Since the sandwich failure is initiated by core failure, a trigger concept for CFRP composite sandwich panels was developed based on local modifications in the fold pattern of the core for controlled failure initiation. By locally adjusting the collapse strength of the core in normal direction, the failure position and failure load can be adapted according to the defined kinematic hinge requirements. The core trigger concept was validated in experiments with triggered and untriggered sandwich panels under identical loading conditions.
机译:与传统的金属机身相比,新的飞机机身概念必须证明等效的防撞标准。 CFRP结构的脆性破坏机制使新颖的CFRP机身概念的等效耐撞性验证颇具挑战性,因为常规的金属机身通过塑化吸收了很大一部分动能。在这种情况下,研究了双壁机身面板在碰撞相关的弯曲压缩载荷下的破坏起因和失效。由于夹层破坏是由芯部破坏引发的,因此基于可控破坏引发的芯部折叠模式的局部修改,开发了CFRP复合夹芯板的触发概念。通过局部调整铁心在法线方向上的塌陷强度,可以根据定义的运动铰链要求来调整失效位置和失效载荷。在相同的负载条件下,使用触发式和未触发式夹芯板的实验中验证了核心触发器概念。

著录项

  • 来源
    《Composite Structures》 |2014年第6期|11-21|共11页
  • 作者单位

    Institute of Structures and Design, German Aerospace Center (DLR), Germany;

    Institute of Aircraft Design, University of Stuttgart, Germany;

    Institute of Structures and Design, German Aerospace Center (DLR), Germany;

    Institute of Structures and Design, German Aerospace Center (DLR), Germany;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Crash; Sandwich structures; Foldcore; Energy absorption;

    机译:崩溃;三明治结构;折芯;能量吸收;

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