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.