The wide application of composite materials is the major technical challenge for drastically reducing the structural weight of the planned future reusable launch vehicles. The use of carbon fiber reinforced plastics(CFRP) to the cryogenic propellant tanks which are the largest components of the vehicle structure is one of the most promising technologies for realizing the weight reduction. Investigation of the mechanical properties of CFRP under cryogenic temperature is thus essential in the considerations of the basic design concept of the vehicle. The goals of this study are firstly to investigate and summarize the temperature dependent mechanical properties of the epoxy-based CFRP, and secondly to analyze the laminate behaviors under cryogenic environment and look into the possible onset of delaminations and transverse cracks which are the major failure modes of the laminates.
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