The purpose is to provide an end-user's perspective on the state of the art in life prediction and failure analysis by focusing on subsonic transport fuselage issues being addressed in the NASA/Boeing Advanced Technology Composite Aircraft Structure (ATCAS) contract and a related task-order contract. First, some discrepancies between the ATCAS tension-fracture test database and classical prediction methods is discussed, followed by an overview of material modeling work aimed at explaining some of these discrepancies. Finally, analysis efforts associated with a pressure-box test fixture are addressed, as an illustration of modeling complexities required to model and interpret tests.
Nonlinear and Progressive Failure Aspects of Transport Composite Fuselage Damage Tolerance
1993
25 pages
Report
Keine Angabe
Englisch
Aircraft , Composite Materials , Engineering Materials , Structural Mechanics , Composite structures , Crack propagation , Failure analysis , Fracture mechanics , Fuselages , Life (Durability) , Subsonic aircraft , Tensile tests , Aircraft structures , Composite materials , Data bases , Finite element method , Prediction analysis techniques
Nonlinear and Progressive Failure Aspects of Transport Composite Fuselage Damage Tolerance
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