Abstract Fibre Metal Laminates are currently one of the most perspective hybrids for aerospace and other industries, because of unique properties, especially damage resistance and damage tolerance. However, the lack of post-impact compressive strength assessment of FMLs and problems with applying effective testing methods was the source of the study. The aim was to design a mechanically effective approach to gaining an understanding of the boundary conditions for post-impact compression of laminates. Based on the conducted research and proposed solution, the relevant behaviour of FMLs was achieved. The delamination growth was found to be linked with the initial damage region of the laminate. Lack of support on the middle part of the sheet left room for plastic deformation of the metal. The above gives the final shape to the plate, and plays a significant role in the process of initiation of metal deformation during compression after impact, and as a consequence, faster internal damage growth.