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Composite shell structures have many applications in aerospace industry in which deal with various loading abundantly. In  present paper Strain gauge instrument with rectangular rosette strain gauges were used to detect the maximum stress and strain distributions along the shell composite structure. Also a finite element analysis was done for validation of experimental results. The FEM software used was ANSYS14. Impact test, density measurement, and bending test were performed in order to detect physical and mechanical properties such as toughness, principal stresses, and density, of the three laminated composite shells. In addition, the results between experimental and ANSYS were compared. It was observed that an important discrepancy is found between theoretical and experimental results. It was also found a large difference in modulus of elasticity, toughness, and tensile strength for each composite material. These differences are  tabulated in many tables in the last paper.

An analytical elastic-plastic stress analysis is carried out on metal-matrix composite beams of arbitrary orientation, supported from two ends under a transverse uniformly distributed load. The composite layer consists of stainless steel fiber and aluminum matrix. The material is assumed to be perfectly plastic during the elastic–plastic solution. The intensity of the uniform force is chosen at a small value; therefore, the normal stress component is neglected in the elastic-plastic solution. The expansion of the plastic region and plastic stress component of σxare determined for orientation angles of 0, 30, 45, 60 and 90o. Plastic yielding occurs for 0 o and 90 o orientation angles on the lower and upper surfaces of the beam at the same distances from the mid-point. However, it starts first at the lower surface for 30, 45 and 60 o orientation angles.