Satellites operate in extreme cosmic environments and are easily shocked by the rocket vibration and acceleration, so they should be designed carefully to endure such conditions. These environmental conditions cause failure of electric equipment and the separation of satellites from its orbit. Therefore, dynamic and stability analyses should be performed to protect the electric equipment and satellite body from such conditions.
The main objective of this work is to confirm the study on the design of attachment of small satellites based on the fundamental frequency. The study was performed to design the separation system of small satellite in which mass increased, based on the design data and vibration test results of KITSAT-2. For this work, the dynamic analysis of attachment of small satellite is performed. Considering this results, the design parameters for the attachment of small satellites are researched based on the fundamental frequency.
