Fatigue of cord-rubber composites: II. Strain-based failure criteria

Citation
Bl. Lee et al., Fatigue of cord-rubber composites: II. Strain-based failure criteria, RUBBER CHEM, 71(5), 1998, pp. 866-888
Citations number
47
Categorie Soggetti
Organic Chemistry/Polymer Science","Material Science & Engineering
Journal title
RUBBER CHEMISTRY AND TECHNOLOGY
ISSN journal
00359475 → ACNP
Volume
71
Issue
5
Year of publication
1998
Pages
866 - 888
Database
ISI
SICI code
0035-9475(199811/12)71:5<866:FOCCIS>2.0.ZU;2-R
Abstract
Fatigue failure mechanisms under low-frequency loading and their dependence on the strain properties were assessed for the rubber matrix composite of bias aircraft tire carcass reinforced by nylon cords as weill as two model rubber composites reinforced by steel wire cables. Under cyclic tension at constant stress amplitude, these angle-plied, cord-rubber composite laminat es exhibited localized damage in the form of cord-matrix debonding, matrix cracking, and delamination. The process of fatigue damage accumulation in t he cord-rubber composite laminate was accompanied by a steady increase of c yclic strain (dynamic creep) and moderate temperature changes. The fatigue life was found to be linearly proportional to the inverse of the dynamic cr eep rate, i.c., the time required to increase cyclic strain by a unit amoun t. Regardless of the associated level of stress amplitude or fatigue life, the gross failure under low-frequency loading occurred when the total strai n accumulation, i.c., cumulative creep strain, reached the static failure s train. The use of higher stress amplitude resulted in a decrease of fatigue life by simply shortening the time to reach the critical level of strain f or gross failure. This observation indicates that the damage initiation and eventual structural failure of angle-plied, cord-rubber composite laminate s are "strain-controlled" processes. These critical strain properties appea r to be controlled by the process of interfacial failure between the cord a nd matrix. Under static tension, the strain levels for cord matrix debondin g and gross failure of composite laminates showed no significant dependence on the level of carbon black loading of the matrix compound, despite the f act that carbon black loading strongly affected the modulus, strength and s train properties of the matrix, Also the number of debonding sites around t he cut ends of cords increased at almost the same rate as the static strain increased regardless of the variation of matrix properties.