Abstract: In this paper, the composite wing structure of a missile is designed. According to the requirement of ablative resistance performance and stiffness performance, this paper presents the molding technology scheme of the ablative resistance functional layer for the outer layer and the bearing layer for the inner layer, and the co-curing of the functional layer and bearing layer. According to the ablation test, it was found that the ablative performance of boron phenolic resin was better, so the prepreg of boron phenolic resin was used as the functional layer of the wing of missile and the prepreg of epoxy resin as the bearing layer. The experimental results of ablative and mechanical properties were satisfactory. The mechanical properties of the missile wing were numerically simulated by ABAQUS finite element analysis software. The maximum deformation was located at the back and upper part of the missile wing. The simulation results were in good agreement with the test results, and the error rate was 6.47%. Compared with the traditional aluminum alloy missile wing, the composite missile wing can reduce the weight by 42.8%, which has obvious advantages.

Key words: composite missile wing, ablation resistance, bearing/ablation integrated, co-curing