Approximate nonlinear analysis method for debonding of skin/stringer composite assemblies

AIAA Journal

Volumn 46, Issue 5, 2008, Pages 1144-1159

  Cosentino, Enzo ^a,c   Weaver, Paul M ^b,d,e  

^a AIRBUS OPERATIONS LTD   (United Kingdom)

^b UNIVERSITY OF BRISTOL   (United Kingdom)

^c Composite Structures Development Centre ^*

^d Queens Building 239   (United Kingdom)

^e AIAA ^*

Author keywords

[No Author keywords available]

Indexed keywords

ANALYSIS METHODS; COMPOSITE PANELS; COMPOSITE WINGS; CRITICAL REGIONS; ECCENTRICITY (ECC); EXPERIMENTAL DATA; GALERKIN; INITIATION (ELECTRIC DISCHARGES); LARGE DEFLECTIONS; LINEAR ELASTIC FRACTURE MECHANICS (LEFCM); NON-LINEAR APPROACH; NON-LINEAR FINITE-ELEMENT ANALYSIS; NONLINEAR STRUCTURAL BEHAVIOR; NUMERICA L RESULTS; ORTHOGONAL EIGENFUNCTIONS; PRESENT METHOD; RAYLEIGH-RITZ APPROACHES; STIFFENED PANELS; THREE DIMENSIONAL (3D); VALIDATION STUDIES; VON KARMAN;

AEROSPACE APPLICATIONS; BRITTLE FRACTURE; CRACK DETECTION; CRACK INITIATION; FINITE DIFFERENCE METHOD; FINITE ELEMENT METHOD; FRACTURE; FRACTURE FIXATION; FRACTURE MECHANICS; MATHEMATICAL MODELS; NONLINEAR PROGRAMMING; NUMBER THEORY; NUMERICAL METHODS; PLATES (STRUCTURAL COMPONENTS); STRENGTH OF MATERIALS; STRESS CORROSION CRACKING; THREE DIMENSIONAL;

NONLINEAR ANALYSIS;

EID: 44849090630     PISSN: 00011452     EISSN: None     Source Type: Journal    
DOI: 10.2514/1.31914     Document Type: Article

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