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Cube Satellites (CubeSat) are class of satellite having various components in a small volume. A satellite faces challenges like excessive vibration, random shocks which affect the internal components during a launch. For the CubeSat to survive through the random vibrations during launch of a random vibration response is necessary to analyze the structure deformation for various frequencies. The present study evaluates the frequency response to random vibration on a 1U CubeSat structure. The vibration analysis is performed to match the requirements of the Polar Satellite Launch Vehicle (PSLV) of the Indian Space Research Organization (ISRO). A modal analysis and random vibration analysis is performed with three different spacer design configurations to find the natural frequencies of the CubeSat structure as well as electronics components with specified boundary conditions. The modal analysis performed showcased the first natural frequency of the CubeSat structure to be 798.8 Hz. The stress response generated by the random frequency excitation showed the second design iteration of alternating spacers to be suitable for launch.

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Frequency Response Analyses of 1U CubeSat Under Random Vibration Condition

  • 会议论文

  • 发表日期：

    2025年

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  • Atharva Sapre,
  • Manasvi Parab,
  • Pankaj Dhatrak

摘要

Cube Satellites (CubeSat) are class of satellite having various components in a small volume. A satellite faces challenges like excessive vibration, random shocks which affect the internal components during a launch. For the CubeSat to survive through the random vibrations during launch of a random vibration response is necessary to analyze the structure deformation for various frequencies. The present study evaluates the frequency response to random vibration on a 1U CubeSat structure. The vibration analysis is performed to match the requirements of the Polar Satellite Launch Vehicle (PSLV) of the Indian Space Research Organization (ISRO). A modal analysis and random vibration analysis is performed with three different spacer design configurations to find the natural frequencies of the CubeSat structure as well as electronics components with specified boundary conditions. The modal analysis performed showcased the first natural frequency of the CubeSat structure to be 798.8 Hz. The stress response generated by the random frequency excitation showed the second design iteration of alternating spacers to be suitable for launch.