Novel engine fan blades are made from 3D woven composite materials and incorporate a protective metallic layer at the leading edge. The end-of-life of such structures involves complicated disassembly and recycling processes. Laser-shock is being investigated as an environmentally friendly disassembly method. In this context, symmetric laser-shock experiments that were conducted in a previous work using a time delay between the shots have been proven successful for debonding initiation and propagation. In this paper, a numerical model simulating the symmetric laser-shock disassembly of Ti/CFRP specimens has been developed using the LS-Dyna explicit FE code. The objective of the model is to give a deeper insight of the physical mechanisms and to optimize the experimental process. To obtain input for the composite damage model, Split-Hopkinson tests have been conducted. The numerical results correlate well with back-face velocity profiles, experimentally obtained by VISAR measurements, and damage patterns in the adhesive and the composite material, experimentally characterized by electronic microscope photographs.