Abstract: The aircraft sub-cargo columns are susceptible to global instability under load due to open-section characteristics, which limits the energy absorption efficiency. Focusing on columns co-curing with carbon fiber reinforced polymer (CFRP) and aluminum alloy (Al), a finite element model was developed based on the Chang-Chang failure criterion and GISSMO damage model, and its validity was verified by comparing with quasi-static axial compression test results. Designs of longitudinal corrugation and fixed-flange were proposed, and the axial failure modes and energy absorption characteristics were compared. The effects of CFRP/Al configurations, CFRP layups, and CFRP/Al interfacial strength were investigated. The results show that the finite element model can accurately simulate axial compression failure mode of CFRP/Al hybrid columns, with a maximum error of −9.45% in energy absorption characteristics evaluation indicators. Compared to the straight columns, the total energy absorption increases by 15.08% with fixed-flange design, by 30.83% with longitudinal corrugation design, and by 39.26% with both longitudinal corrugation and fixed-flange designs. The CFRP/Al configuration plays a critical role in axial compression failure stability of corrugated columns. The ±45° and 90° fibers have a restraining effect on transverse deformation, while an excessive proportion of ±45° fibers can lead to structural fracture. Enhancing the CFRP/Al interfacial strength can effectively prevent fracture and preserve structural integrity. Comprehensive analysis reveals that corrugated column featuring inner Al configuration, 0/90_2s layup, and J47C co-curing process exhibits a stable energy absorption process and superior energy absorption performance, providing valuable guidance for the controlled failure and stable energy absorption design of aircraft sub-cargo columns.