Abstract
Long-term loading can have a significant effect on the performance of aerospace composite structures. The size of this effect depends on the type of composite used, the fiber orientation within a particular composite, and the imposed stress and temperature levels. Test data for graphite-epoxy composite under undirectional state of stress and controlled temperature environment are presented. The behavior of specimens of different lamina orientation tested under identical conditions was compared. The stress situation and temperature level are the most influential parameters on the creep deformation of the material, being greatest where the reinforcing fibers are not aligned in the direction of the load application. A relation between time to rupture, temperature, and stress level was shown and compared to other composite systems. The results show the detrimental effects of stress level, time, and temperature on the strength and deformation. Based on these data, the behavior under long-term loading could be extrapolated from reasonably short-time tests composite materials, fiber composites,
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