De-icing systems remove ice formed on aircraft protected surfaces according to a periodic cycle by reducing the adhesive shear strength between ice and surface. In the present work, an immersed boundary method is used to predict ice-shedding trajectories and impact. At the start of shedding trajectory calculations, when the ice-shed particle is still close to the wing surface, there is a high probability of collision with the surface. A linear spring collision model is presented assuming the interacting bodies are connected tangentially and normally by linear springs. The verification of the model is done with results from literature and study of trajectories around a cylinder.