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Effects of truncation of a predominantly compression load spectrum on the life of a notched graphite/epoxy laminate

Author
Phillips, E. P.
Published
Jun 1, 1979.
Physical Description
1 electronic document
Online Version

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Summary
The fatigue behavior of a notched, graphite/epoxy (T300/5208) laminate subjected to predominantly compressive loading was explored in a series of constant-amplitude and transport wing spectrum tests. Results of these tests indicate that (1) the amount of local (near the notch) buckling allowed in the tests significantly affected fatigue life; (2) spectrum truncation of either the high- or low-load end of the spectrum produced lives greater than those obtained in the baseline, complete-spectrum test, but life was much more sensitive to truncations at the high-load end; and (3) the Palmgren-Miner linear cumulative damage theory always predicted lives much longer than the actual spectrum loading test lives.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19790018256.
Accession ID: 79N26427.
NASA-TM-80114.
ASTM Symp. on the Fatigue of Fibrous Composite Mater.; 22-23 May 1979; San Francisco, CA; United States.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15725202