Dynamic Characteristics of Deployable Structures in the DaejeonSat-1 16U Satellite

After orbital deployment, the DaejeonSat-1 satellite begins its mission by deploying the onboard selfie camera and solar panel. These components are actuated by torsion spring mechanisms. If deployment fails, the mission performance can be severely affected. During deployment, physical contact between components may damage sensitive electronics or sensors. To prevent such damage, physical contact must be minimized. If the solar panel does not deploy properly, the satellite cannot receive sufficient power from the sun. This risk requires careful analysis and testing of the deployment process. In a microgravity environment, the motion of deployment can lead to attitude changes such as tilting. These changes may disturb the satellite’s attitude control system. It is important to study the satellite’s behavior during deployment to reduce such disturbances. This study uses multi-body dynamic simulations to model the deployment of the selfie camera and solar panel. The simulations evaluate change in attitude, possible contact between components, and the stability of the entire process. Based on the analysis results, an optimal deployment mechanism was derived to minimize risk and ensure reliable mission performance.