ON INNOVATIVE STRUCTURE OF HIGH ASPECT RATIO COMPOSITES WING APPLICATION

摘要

Based on the bearing force characteristic of high aspect ratio wings, an innovative mixed structure is brought forward, which combines the advantages of wing spar structure and honeycomb sandwich structure. It requires the experimental investigations of the compress strength after low velocity impact of stitched and non-stitched laminates. The compressive test is conducted for three styles of honeycomb sandwich laminates. The finite element analysis method is adopted to compare the mixed structure with the other two structures. The results of experiments and calculation indicate that the innovative mixed structure possesses obvious technical predominance and visible effect of decreasing weight