he satellite structure should have high strength to withstand the harsh conditions resulting from the transient dynamic loads of low frequency, during the initial period in the launch phase. Satellite structures of similar shapes, manufactured by similar manufacturing processes, but made of different class of aluminum, have similar vibration behavior. However, for satellite structures manufactured by different manufacturing processes, it becomes necessary to study and analyze the structures to determine their vibration behavior.  In this paper, the dynamic behavior of three identical satellite structures (two formed and one machined), has been analyzed and compared using the Finite Element Method. Incremental forming and machining have been selected as manufacturing methods. We have used the analysis results for qualification of design and the manufacturing methods, without performing the costly vibration tests. The results show the superiority of the formed structures from the vibration behavior point of view. The results also demonstrate the viability of forming as possible replacements for the machining process, with potential for cost reduction.