Abstract
To realize the practically Reusable Launch Vehicle (RLV), one of the most significant technologies is drastic weight reduction of airframe weight. Instead of the conventional aluminum tank, utilization of carbon fiber reinforced plastics (CFRP) for cryogenic propellant tanks is essential to reduce the tank weight. We built a small CFRP tank by filament winding, and performed pressure test and LN2 storage demonstration. After the test, there were various amount of leakage from the various area of the tank. In this study, microscopic analyses were conducted to find the mechanism of material damage and leak path formulation. The large void in the cross section is the most predominant factor of the leakage from this tank.
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