Abstract: 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.