Design, manufacturing and testing of composite wing model via integral forming process

Four different structure wings were designed according to the given configuration. Based on the optimized curing process of the resin, the four composite wing models were manufactured via integral forming technique. The three point bending test results show that the I-beam wing has the highest load-carrying efficiency, then the following is the C-beam wing. The skin-foam wing has the minimum load-carrying efficiency. The failure of skin-foam wing is caused by compression failure of upper skin at loading point, while the skin-stiffened wing is failures from the shear break of support point. The C-beam and I-beam structure wings both have shear failures at the wing leading edge between loading point and support point. The finite element analysis (FEA) result is consistent well with those of experiment.