The aim of this study is to design a 3 Unit CubeSat structure performing finite element analysis under static, dynamic and thermal loads. The main idea of this process is to construct a 3U CubeSat main frame that can structurally endure launching process and space environment. To accomplish the task, a 3U CubeSat structure is designed and standard loads that a 3 unit CubeSat structure has to endure are obtained. After the selection of a suitable material, modal analysis, quasi-static launch analysis and thermal stress analysis coupled with heat transfer analysis are accomplished in Abaqus environment. Finally, the results are evaluatedand endurance level of the
design is determined.