Residual strength prediction of damaged composite fuselage panel with R-curve method

Composites Science and Technology

Volumn 66, Issue 14, 2006, Pages 2557-2565

  Wang, John T ^a   Poe Jr , Clarence C ^a   Ambur, Damodar R ^a   Sleight, David W ^a  

^a NASA LANGLEY RESEARCH CENTER   (United States)

Author keywords

A. Composites; B. Strength; C. Damage tolerance; C. Finite element analysis (FEA)

Indexed keywords

COMPOSITE STRUCTURES; CRACK PROPAGATION; FINITE ELEMENT METHOD; FORECASTING; FUSELAGES; STIFFNESS; STRENGTH OF MATERIALS; TENSILE PROPERTIES;

COMPOSITE FUSELAGE PANEL; CRACKED TENSILE PLATE; DAMAGE TOLERANCE; RESIDUAL STRENGTH;

STRUCTURAL PANELS;

CALCULATION; COMPOSITE; DAMAGE; FINITE ELEMENT ANALYSIS; STRENGTH;

EID: 33746562963     PISSN: 02663538     EISSN: None     Source Type: Journal    
DOI: 10.1016/j.compscitech.2006.01.011     Document Type: Article

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