عنوان مقاله [English]
The use of multi-unit cubic satellite (CubeSats), designed nowadays, in accordance with a certain standard, have made any research aimed towards their optimization, quite significant. In the present paper, studies one such common satellite design structure known as “1U”. Our study is carried out with a focus on the structure subsystem, which is of high consequence, due to the direct relationship, it would establish with other subsystems. Informed by the conditions, such satellite structure is exposed to, the present paper, defines the dynamic equations governing its motion, as well as relevant heat, modal and static equations, and utilizes the finite element method (FEM), in several separate portions to solve them. To attain a higher accuracy, our study takes into account, the standards and design specifications for such satellites. Analysis indicate temperature variations on the outer structure of the satellite is in a range from −19.79°C up to 18.85. Moreover, the highest stress value taken by the satellite structure is 45.42 MPa, demonstrating structural resilience versus stress excreted. The first mode of satellite structural resonance is 467.647 Hz. reliability factor was obtained as well, from an investigation of stress values inside the structure. Put together, the results from the analyses have allowed us to conclude that the structure, is in fact resilient, against the excreted stress. Supplementary output from the present study is also valuable, in provision of various prerequisites to an optimal design of the structure subsystem, as well as several other subsystems.