中文摘要：

结构轻量化是航空航天发展的永恒主题,波纹夹层圆柱壳作为常见的轻质结构形式,在航空航天领域具有很大的发展空间。采用模具热压法,制备出纵向和环向碳纤维复合材料波纹夹层圆柱壳,其中芯子整体成型,面板分瓣制备。采用经典板壳屈曲理论,分析纵向和环向波纹夹层圆柱壳的轴压力学性能,得到了欧拉屈曲、整体屈曲、局部屈曲和面板压溃4种失效模式下的极限载荷理论公式。绘制出结构的失效机制图,直观显示出了失效模式与试件尺寸之间的关系。通过对纵向和环向波纹夹层圆柱壳的轴向压缩试验,获得了结构的载荷-位移曲线及局部屈曲和面板压溃2种失效模式。结果表明：纵向波纹夹层圆柱壳的轴向承载能力及载荷/质量效率优于环向波纹夹层圆柱壳,在一定范围内增加圆柱壳面板的厚度、减小圆柱壳的高度可提高结构的载荷/质量效率。

英文摘要：

The aim for lightweight structure is the eternal subject for the developing of aeronautics and astronautics,corrugated sandwich cylindrical shell as a common form of lightweight construction has great potential infields of aeronautics and astronautics.The longitudinal and circular carbon fiber composite corrugated sandwich cylindrical shells were fabricated by hot press method.The corrugated cores and skins were made in integral and split forming,separately.The axial compressive mechanical properties of longitudinal and circular corrugated sandwich cylindrical shells were analyzed using the classic theory of plate and shell buckling.Ultimate load theoretical equations were obtained under four kinds of failure modes including Euler buckling,overall buckling,local buckling and face crushing.The failure mechanism maps of structure have been drawn which obviously show the relationship between failure modes and specimen size.The axial compression tests have been conducted on the longitudinal and circular corrugated sandwich cylindrical shell,the load-displacement curves and two kinds of failure modes including local buckling and face crushing have been obtained.The results show that longitudinal corrugated sandwich cylindrical shells is better than that of circular corrugated sandwich cylindrical shells in axial bearing load and efficiency of load/mass.Increase the thickness of cylindrical shell panel or decrease the height of cylindrical shell in a certain range can improve the efficiency of load/mass for structure.