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Test and Analysis of Composite Hat Stringer Pull-off Test SpecimensHat stringer pull-off tests were performed to evaluate the delamination failure mechanisms in the flange region for a rod-reinforced hat stringer section. A special test fixture was used to pull the hat off the stringer while reacting the pull-off load through roller supports at both stringer flanges. Microscopic examinations of the failed specimens revealed that failure occurred at the ply termination in the flange area where the flange of the stiffener is built up by adding 45/-45 tape plies on the top surface. Test results indicated that the as-manufactured microstructure in the flange region has a strong influence on the delamination initiation and the associated pull-off loads. Finite element models were created for each specimen with a detailed mesh based on micrographs of the critical location. A fracture mechanics approach and a mixed mode delamination criterion were used to predict the onset of delamination and the pull-off load. By modeling the critical local details of each specimen from micrographs, the model was able to accurately predict the hat stringer pull-off loads and replicate the variability in the test results.
Document ID
19960045790
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Li, Jian
(NASA Langley Research Center Hampton,VA United States)
OBrien, T. Kevin
(Army Research Lab. Adelphi, MD United States)
Rousseau, Carl Q.
(Bell Helicopter Co. Fort Worth, TX United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1996
Subject Category
Composite Materials
Report/Patent Number
ARL-MR-327
NAS 1.15:110263
NASA-TM-110263
Report Number: ARL-MR-327
Report Number: NAS 1.15:110263
Report Number: NASA-TM-110263
Accession Number
96N32661
Funding Number(s)
PROJECT: RTOP 505-63-50-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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