Manufacturing process simulation and structural evaluation of grid stiffened composite structures

摘要

This paper presents a study of carbon composite structures with advanced architectures. These architectures are specifically tailored for light weight aircraft components by application of integrated local skin reinforcement with the use of rib and grid stiffening. The overall aim of this study is to evaluate buckling and strength performance using numerical methods, taking into account composite curing aspects, manufacturing and testing of this optimized design. On a coupon scale the effects of variations in grid height, grid/skin interface design and skin thickness have been analysed and manufacturing trials have been performed. The knowledge from these coupon level simulations and manufacturing trials have been used to design and manufacture an aircraft front-fuselage panel section with a buckling-optimized curved grid stiffening reinforcement. Tow cutting is used at each of the grid intersections to prevent tow overlapping and maintain quality of the laminate in the grid. In the investigated application area, grid stiffening designs in the front-fuselage section have shown weight gains compared to conventionally stiffened panel designs.