Space structures face many different and extreme types of loading throughout their life time from harsh launch environment to the harsh space environment. Dynamic loading in space structures is found to be the main concern with its variety and extreme loading conditions from periodic loading to acoustic/random vibration and shocks. Shock in space structures are produced by pyrotechnic devices placed in the launchers initiating the stage separations, in addition, other less intense shock sources can be the deployment mechanisms for solar cells, antennas, and other satellite components. These high intensity shocks are of a main concern for sensitive space structures, like PCBs, crystals, and fragile optical components. Testing used to be the main method for studying the effect of shocks on structures and components. But with the increasing shock intensity in launchers due to the decreased amount of damping materials, and the increasing customer qualification requirements, the possibility of simulating shocks using Finite Element Models (FEM) has been studied. Different possible simulations methods have been studied, applied to a simple model, and compared with the ringing plate test results developing an efficient and reliable method for shock simulation using Finite Element Methods. The effects of the different parameter on the simulation results have been studied and some recommendations for shock simulation using Finite Element Methods have been conducted. The developed method have been studied further and applied to a more complex real life model to study its effectiveness in simulating real space structures. The overall outcome of the simulation method has proven its reliability in simulating satellite structures subjected to Pyro-shocks and other shock loading when compared to ringing plate test results. This simulation method has been developed at RUAG Space AB in Göteborg, Sweden and has been approved as a possible simulation method in their future shock analysis.