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Progressive Fracture of Fiber Composite Thin Shell Structures Under Internal Pressure and Axial LoadsGraphite/epoxy composite thin shell structures were simulated to investigate damage and fracture progression due to internal pressure and axial loading. Defective and defect-free structures (thin cylinders) were examined. The three different laminates examined had fiber orientations of (90/0/+/-0)(sub s), where 0 is 45, 60, and 75 deg. CODSTRAN, an integrated computer code that scales up constituent level properties to the structural level and accounts for all possible failure modes, was used to simulate composite degradation under loading. Damage initiation, growth, accumulation, and propagation to fracture were included in the simulation. Burst pressures for defective and defect-free shells were compared to evaluate damage tolerance. The results showed that damage initiation began with matrix failure whereas damage and/or fracture progression occurred as a result of additional matrix failure and fiber fracture. In both thin cylinder cases examined (defective and defect-free), the optimum layup configuration was (90/0/+/-60)(sub s) because it had the best damage tolerance with respect to the burst pressure.
Document ID
19970001596
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Gotsis, Pascal K. (NASA Moffett Field, CA United States)
Chamis, Christos C. (NASA Moffett Field, CA United States)
Minnetyan, Levon (Clarkson Univ. Potsdam, NY United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1996
Subject Category
Structural Mechanics
Report/Patent Number
NAS 1.15:107234
NASA-TM-107234
E-10277
Accession Number
97N11390
Funding Number(s)
PROJECT: RTOP 505-63-5B
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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