Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : September 08, 2019 - September 11, 2019
Sandwich structures made of carbon fiber reinforced plastics (CFRPs) have excellent characteristics such as lightweight, high stiffness, and low coefficient of thermal expansion. Therefore, CFRP is one of attractive candidates as structural material in aerospace field. Today, the use of satellite at high temperature environment such as exploration in Venus, etc. In this research, for the application to CFRP sandwich panel for the light weight satellite mirror, quality improvement CFRP honeycomb core produced by VaRTM method. Since the VaRTM method involves the process of forming resin directly into the fiber, the rate of occurrence of stiffness and strength is low because voids and loss of fiber linearity due to resin flow is like to occur. It is issue. Observing resin impregnation behavior of VaRTM method was carried out by video camera and digital microscope. As a result, Impregnation speed of double fiber is slower than impregnation speed that become cause of void occur. The difference in impregnation speed was confirmed by distance of resin injection. It was shown that it is necessary to clarify the influence of lamination condition, detailed factor of the resin injection condition and to decision the impregnation condition suitable for structure.
