The behavior of a high temperature carbon / polyimide composite, T650 / AFR-PE-4, in a cryogenic environment was studied. The results were compared to results from similar testing of a carbon / epoxy and a carbon / bismaleimide composite in order to begin to scale the difficulties involved with using high temperature polymer matrix composites (PMCs) in cryogen containers on launch vehicles. T650 / AFR-PE-4 developed transverse cracks in all plies after fewer cycles than a carbon / bismaleimide (IM7 / 5250-4) when each was cycled between -196 deg C and their respective maximum service temperatures. A change to a crossply resulted in a substantial reduction in the tendency toward a complete crack network in past work on IM7 / 5250-4. However, the same change from a (0/45/-45/90)s lay-up to a (0/90)2S lay-up produced only a small delay of 50 cycles in the formation of transverse cracks in all plies of the T650 / AFR-PE-4 samples. On the other hand, the lay-up change corresponded to a large permeability reduction possibly due to less delamination in the (0/90)2S samples or due to some of the transverse cracks remaining near the sample edges. Transverse strength and Mode I toughness of unidirectional laminates were also measured at room temperature (RT) and -196 deg C to determine sources of the increased damage.
Comparison of matrix cracking in high temperature and lower temperature PMCs from cryogenice exposure
Vergleich der Matrixrissbildung in Hochtemperatur- und Tieftemperatur-PMCs durch Tiefsttemperaturexposition
2007
8 Seiten, 12 Quellen
Conference paper
English
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