This study provides an analytical simulation of drag braking experienced by a miniature spacecraft while its solar array system is deployed in orbit. The study was carried out by the authors of the current work. This offers the designer aid in detecting possible difficulties that may develop when the system is being tested on the ground. A piece of software known as Mechanical Desktop (MDT) is used in order to model the deployment mechanism (DM), and another piece of software known as the Finite Element Analysis Package is utilized in order to analyse the DM (ANSYS 11). The Design and Stress analysis is carried out at the periods of the DM's operation that are considered to be the most crucial. In order to establish whether or not the DM can be relied upon, several various models of finite element analysis were investigated. Testing for random vibration, testing for modal vibration, and testing for static vibration were all tied to these studies in some way. The current investigation will ensure that the mechanism will continue to function properly even after the satellite has been launched into orbit, and it may be able to assist in the evaluation of whether or not the mechanism will be able to persist under operational situations that are typical of the real world.