Design iterations and structural finite element analysis of a prototype communication satellite

Satellite structures are subjected to enormous mechanical loading during launch. These mechanical loads can be given as sinusoidal vibration loads, quasi-static loads, acoustic loads and shock loads. Satellite structures have to withstand mechanical loads throughout their mission life. Another crucial phenomenon is total mass of the satellite because every single mass effects launching cost and mission life time. Suitable satellite structure sizes cannot be found directly during preliminary design phase. For that reason, iterative studies must be done. In this thesis, iterative studies will be considered with material thickness changes and composite material usage on the primary load carrying structures which are central cylinder and shear panels. After defining the candidate launchers, center of gravity, stiffness, quasi-static and global buckling requirements will be considered. After that global finite element model of the satellite has generated with respect to proper mesh size which is found by mesh convergence study. A commercial software Hypermesh is used to generate finite element model of the satellite. To find proper iteration model, first stiffness requirements must be met. After quasi-static panel margin of safeties must be satisfied. And then global buckling margin of safeties must be suitable. After satisfying all of these requirements, total mass of the satellite has to be considered to select proper iteration model. After selecting proper iteration model detailed finite element analysis and primary notching analysis have performed. NX Nastran solver has used to solve mathematical model of the satellite.