Vibration Analysis And Drop Test Of ۳U CubeSat

The objective of this paper is to analyze the various impacts on the structure of a ۳U CubeSat using the Finite Element Method (FEM) and simulations performed in SolidWorks. This analysis examines the stress distribution and potential deformations in the satellite body under critical conditions such as high G-forces, mechanical shocks during launch, severe vibrations during rocket separation, and other extreme events. The results show that the CubeSat structure is capable of withstanding natural frequencies ranging from ۳۷۰۶.۹ Hz to ۴۵۶۹.۵ Hz in the vibration analysis, and can endure forces up to ۱۶ G during the drop test, with a very low probability of permanent deformation or structural failure under the simulated conditions. This analysis helps designers ensure the safety and structural integrity of the satellite under mission-critical environments. Furthermore, the vibration and natural frequency analyses confirm the structure's ability to avoid resonance phenomena and the associated risks of damage. This paper explores effective methods for designing robust satellite structures, identifies key challenges in CubeSat structural design, and provides recommendations for improving satellite performance, durability, and operational reliability in harsh space environments.

کلیدواژه ها:

۳U CubeSat ، Impact Test ، Drop test ، Vibration Analysis