Cruise missiles typically feature foldable wings to optimise storage and transport, necessitating rapid wing unfolding post-launch to ensure aerodynamic efficiency and stability. This study presents a coupled CFD - Flight Mechanics method for the simulation of a wing unfolding process of a cruise missile, marking a step towards predicting critical maneuvers during launch. Using the DLR TAU code with Chimera technique and its Six-Degree-of-Freedom module, the method effectively captures the dynamics of the wing unfolding while avoiding constant mesh regeneration. The unfolding process is driven by a predefined external torque and stopped using a spring-damper system to replicate realistic unfolding dynamics. A simplified cruise missile configuration is used, operating at \(\textrm{Ma}=0.8\) and \(\textrm{Re}_c=4.4\times 10^6\) . A mesh convergence study and a comparison of results from a Chimera and a classical mesh is done for verification. Parameter variations across different motor torques, spring constants and flight conditions confirm the robustness and demonstrate the feasibility of the method in predicting both aerodynamic and mechanical responses during the unfolding process. Future work will focus on incorporating degrees of freedom to the fuselage, a more realistic missile configuration and also applying the method to the fin unfolding.