The thesis presents the preliminary analytical stress analysis of the fuselage skin and frames of a remotely piloted aircraft. The fuselage skin and frames are composite parts made from epoxy resin and carbon fibre fabric. Based on the CS-VLA standard two load cases were determined as a basis for stress analysis. The fuselage was split into loading stations, loaded according to the mass distribution in the fuselage. The skin and frames were analysed using beam theory and the elastic center method, which resulted in the calculation of bending and shear stresses in the frames and skin. The stress calculations serve as a basis for further fuselage design and optimization.
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