航空機用複合材構造の試作レス製造技術の研究

概要

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Process induced deformation on composite parts affects their quality and causes additional efforts and costs for the assembly. Try and error approaches have been used for the shape compensation in industries. A process simulation for predicting process induced deformation on composite structures was proposed and evaluated by actual scale wing spars in this study. The proposed method was based on the detailed material data including the temperature dependence of elastic modulus and the coefficients of thermal expansion of the cured lamina, and the resin viscosity and volume change during process. The resin cure shrinkage contributing the deformation was quantified with the assumption that the resin gelation coincides with the viscosity rise up during process. The cure properties of lamina were calculated with a unit cell model of finite elements which consisted of the fiber and the resin. These lamina properties were incorporated into the versatile finite element software, MSC Marc, with the user subroutine developed by authors. Simple L shape parts were manufactured due to verify the process simulation before the wing spar simulation. The wing spar simulation showed that the process simulation could predict the spring-in deformation of the parts well.