Emirates aviation college CubeSat project: Tuning of natural modes, static and dynamic analyses of the strength model

CubeSats are standardized platforms for small orbital experiments, which prescribes a satellite with dimensions 10×10×10cm and mass one kilogram. This paper presents the overall configuration process of a CubeSat model for the given mission along with structural static and dynamic analyses for the proposed design using a finite element package. High requirements have been set regarding the structure of the satellite and its integrity, as it has to withstand high static, dynamic, thermal and the vacuum in space. Accordingly, a detailed static analysis is fulfilled to assure that the proposed primary and secondary structures can withstand the harsh g-loads during launching without permanent or excessive deformations regarding the allowed dynamic envelope for every subsystem and for the whole satellite. The CubeSat structure is designed with a structural stiffness which ensures that the fundamental frequencies of the satellite mounted on the launch vehicle adaptor are not less than prescribed values according to the candidate launcher. Therefore, modal tuning is fulfilled for the proposed CubeSat structure in order to assure that this satellite is unlikely to be highly exited by the launch vehicle´s long lasting harmonic vibrations while being mounted on the launch vehicle adaptor. In addition, the propulsion requirements and an initial sizing of the propulsion subsystem are provided. Finally, thermal buckling and post buckling response for the shear panels is presented to help in choosing the suitable panel thickness according to the solar panels safety requirements.