| Summary: | 碩士 === 國立成功大學 === 航空太空工程學系 === 107 === The OOA process uses partially impregnated prepregs for composite laminates; gases and volatiles are removed by vacuum through the dry region of the prepregs. In this study, the fully impregnated carbon fiber prepregs and dry carbon fabric were assembled to form a hybrid laminate similar to the partially impregnated laminate. By calculating the volume of fiber pores and resin volume in the laminate, we acquired the saturation degree of the hybrid laminate. Three types of hybrid laminates were fabricated by OOA process to represent the different saturation conditions: super-saturation, saturation, and under-saturation. Tensile test was performed on all these specimens. The result shows that if the original thickness ratio of prepregs to carbon fabric is 1.04, and saturation index of 1.27, hybrid laminate with competitive tensile properties as that manufactured by conventional autoclave process can be obtained.
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