Reliable payload separation systems are of fundamental importance in any satellite mission. Due to the unique requirements of satellite missions, separation adapters must be modified for every novel spacecraft. Efficient and reliable analysis is needed to minimize the demand for qualification testing. The goal of this paper is to compare different modelling tools in order to develop a verified analysis approach to simulate spacecraft release using separation systems. This is achieved by validating the analysis results using data of a high-speed imaging test. A system by RUAG Space AB is used as a representation of a separation system, incorporating a clampband based connection and a Clampband Opening Device (CBOD) as a release actuator. The two commonly used programs MSC Nastran and Abaqus will be investigated as nonlinear Finite Element analysis methods. To evaluate the performance of the programs simulation time and the result deviations compared to the test results are being taken into account as parameters. With respect to the result deviations both programs have shown similar results, however neither program was able to achieve the desired accuracy. Regarding the simulation time Abaqus attained favourable results over MSC Nastran for the overall simulation.