quasi-static and dynamic analysis of a 12u cubesat under flight-phase environmental loads

Cubesats are a class of nanosatellites that, despite being small, are able to perform important space missions without the need for large and complicated satellites. since during the operational life of the satellite, especially during the launch phase, various quasi-static and dynamic loads are applied to the satellites, therefore, the strength and dynamic analyses of the satellite structure, as the main element to tolerate external loads, are of great importance. in this paper, the mechanical design and full finite element analysis of the structure of a 12u remote-sensing cubesat, including modal, random vibrations, sinusoidal vibrations, and quasi-static analysis, are performed. first, the design process of the presented 12u cubesat, which fulfills the requirements of cubesats, is expressed. in the design of the structure, a middle plate is used to increase the stiffness and natural frequencies. second, ansys software performs the finite element analysis of the satellite according to the ecss standard. the numerical results show that the designed structure meets all requirements of the launcher, including stiffness and frequency requirements while sustaining the static and dynamic loads during the launch phase