Document Type : Original Article
Authors
1
Department of Mechanical Engineering, Sharif University of Technology, Tehran, Iran
2
Satellite Research Institute, Iranian Space Research Center, Tehran, Iran
3
Department of Mechanical Engineering, K.N. Toosi University of Technology, Tehran, Iran
4
Department of Aerospace Engineering, Sharif University of Technology, Tehran, Iran
Abstract
CubeSats are a class of nano satellites, despite being small, able to perform important space missions without the need for large and complicated satellites. Since during the operational life of the satellite, especially during 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 much important. 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 design of the structure, to increase the stiffness and natural frequencies, a middle plate is used. Second, the finite element analysis of satellite according to the ECSS standard is performed by Ansys Software. The numerical results show that the designed structure meets all requirements of the launcher, including stiffness and frequency requirements, while sustain the static and dynamic loads during launch phase.
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