Abstract
Analysis of monocoque and semi-monocoque cylindrical flight vehicle structures by using finite element method has been carried out. Shell elements are used for idealizing skin portions and end rings and beam elements are used for idealizing stiffeners. The behaviour of these structures is compared in terms of mass, deformation, stress and buckling under structural and thermo-structural loads to study the effect of number of longitudinal stiffeners. The study shows that semi-monocoque structures give higher factor of safety and buckling load factor when only structural loads (axial force and bending moment) are acting on them and the same structure give lesser factor of safety and buckling load factor when thermal loads (temperatures) and structural loads (axial force and bending moment) are acting on them in a combined manner. It is concluded that monocoque structures are best suitable under thermo-structural load environments.
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