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Volumn 42, Issue 10, 2004, Pages 1445-1464

The computational post buckling analysis of fuselage stiffened panels loaded in compression

Author keywords

Fuselage buckling analysis; Non linear finite element modelling; Post buckling analysis; Stiffened panel compression testing

Indexed keywords

BUCKLING; COMPRESSION TESTING; COMPUTATIONAL METHODS; COMPUTER SIMULATION; FINITE ELEMENT METHOD; STIFFNESS;

EID: 3142658923     PISSN: 02638231     EISSN: None     Source Type: Journal    
DOI: 10.1016/j.tws.2004.04.002     Document Type: Article
Times cited : (68)

References (18)
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  • 12
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    • Hu, S.Z.1    Jiang, L.2
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    • Design of fibre metal laminates shear panels for ultra-high capacity aircraft
    • Wittenberg T.C., van Baten J.J., de Boer A. Design of fibre metal laminates shear panels for ultra-high capacity aircraft. Aircraft Design. 4:2001;99-133.
    • (2001) Aircraft Design , vol.4 , pp. 99-133
    • Wittenberg, T.C.1    Van Baten, J.J.2    De Boer, A.3
  • 16
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    • An experimental investigation of the post-buckling efficiency of Z-section stringer-skin panels
    • Rothwell A. An experimental investigation of the post-buckling efficiency of Z-section stringer-skin panels. Aeronautical Journal. 85:1981;29-33.
    • (1981) Aeronautical Journal , vol.85 , pp. 29-33
    • Rothwell, A.1
  • 18
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    • Efficient non-linear modelling of fuselage panels
    • ICAS-2002-3.2.1, Toronto, Canada
    • Murphy A., Price M., Gibson A., Armstrong C.G. Efficient non-linear modelling of fuselage panels. ICAS-2002-3.2.1, ICAS 2002, Toronto, Canada:2002.
    • (2002) ICAS 2002
    • Murphy, A.1    Price, M.2    Gibson, A.3    Armstrong, C.G.4


* 이 정보는 Elsevier사의 SCOPUS DB에서 KISTI가 분석하여 추출한 것입니다.