高超音速弹用承载/烧蚀一体化复合材料弹翼研究

Research on bearing/ablation integrated composite wing of hypersonic speed missile

本文针对某型导弹的复合材料弹翼结构进行了设计,根据其耐烧蚀性能及刚度性能要求,提出外层铺放一层耐烧蚀功能层材料,内层铺放承载层材料,功能层与承载层采用共固化的模压成型工艺方案。通过烧蚀试验证明硼酚醛树脂的耐烧蚀性能较好,因此采用硼酚醛树脂预浸料作为弹翼功能层,以环氧树脂预浸料作为承载层;制备弹翼,对其进行烧蚀及力学性能试验,结果均满足要求;通过ABAQUS有限元分析软件,对弹翼力学性能进行数值模拟,最大变形量位于弹翼后上部,仿真结果与试验结果吻合较好,误差率为6.47%。与传统铝合金弹翼进行对比,采用复合材料弹翼可以减重42.8%,优势明显。

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.