Slavinskis, Andris, juhendajaIlbis, Erik, juhendajaIakubivskyi, IaroslavTartu Ülikool. Loodus- ja täppisteaduste valdkondTartu Ülikool. Tehnoloogiainstituut2017-06-082017-06-082017http://hdl.handle.net/10062/56555Any object that has been launched into orbit has experienced statical and dynamical loads during its travel through the atmosphere. The loads are of random nature and cannot be fully predicted as per real conditions. The structural requirements for ESTCube-2 have been determined as for the worst-case scenario, since the launch vehicle was not known at that stage of the project. A three-unit CubeSat will be subject to high-level sine and random vibration as well as shock response spectrum loading. Before physical testing, structural simulations were made and stresses were analysed in order to confirm the structural reliability and margins. Margins are essential in the design process due to uncertainties in the predicted vibration environment. In addition, the thesis presents the design of primary and secondary structures. As a result of this thesis, a final materials selection, topography optimisation, and manufacturing of the structure will be made. Moreover, the simulation results obtained here will be the subject of comparison with the physical testing results in the later stage of the ESTCube project. ESTCube-2 will be launched in the first half of 2019, and will serve as a testbed for the ESTCube-3 mission in the solar wind environment.engESTCube, nanosatellite, structural analysis, simulations, FEMAPmagistritöödThesis