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  • 저자

    박성준

  • 학위수여기관

    경상대학교 대학원

  • 학위구분

    국내석사

  • 학과

    기계항공공학부 항공우주공학과

  • 지도교수

  • 발행년도

    2014

  • 총페이지

    p.56

  • 키워드

    FEA Analysis Composite Through-thickness stress Corner radius;

  • 언어

    kor

  • 원문 URL

    http://www.riss.kr/link?id=T13534243&outLink=K  

  • 초록

    Major aircraft companies are competitively adopting composite materials to the primary structures such as spars, stringers and skins. Among them, the wing spar is the biggest and most challenging part to apply the composite materials. Most of composite wing spars have the shape of C- or I-section corner radius at the joint of flange and web and are thicker than other part. When an opening load is applied to the thick spar, the corner radius is vulnerable part and easily experiences local failures. The local failures are mainly attributed to the through-thickness stresses. Therefore, designers are anxious for the reliable analysis method to accurately predict the stresses and failure at the corner radius. In this study, various thick composite corner radius structures with C-section were tested under opening load with different thicknesses and heights. Based on test results, a three-dimensional finite element model in conjunction with various failure criteria was proposed to predict the through-thickness stresses and failure of the corner radius. The finite element results are also compared with failure loads by existing design criteria. Finally authors proposed an improved method to accurately predict the failure load of thick composite corer radius part.


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