Abstract
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.
Highlights
Composite materials are desirable in lightweight structures due to their high specific stiffness and strength
The present paper provides a coupling between an experimental measuring using strain gauge technique and finite element method using ANSYS 14
It’s found that the modulus of elasticity and tensile strength of Carbon–Epoxy are greater than Kevlar-Epoxy and Glass–Epoxy. This is attributed to many reasons such as (1) Woven fibers better than discontinuous fibers in carrying load (2) Carbon content in fibers affect to the strength of fibers and laminate shell
Summary
Composite materials are desirable in lightweight structures due to their high specific stiffness and strength. In the aerospace industry is high performance versus weight ratios that it is possible to achieve using these materials and on the necessity to lower the weight of the aircraft as much as possible to enhance its efficiency. A stress analysis of stiffened cylindrical composite shell under transverse end load has been analyzed [3]. A new method for an elastic-plastic analysis of stress and deformation fields in composite overwrapped cylinder under the pressure load has been provided [4]. Experimental and numerical analysis of grid composite cylindrical shell subjected to transverse loading [5] and various end loading [6] have been made. Buckling analysis of thin walled composite cylindrical shells with and without cutouts under applying axial load on glass fiber reinforced plastic shell has been made [8]. The present paper provides a coupling between an experimental measuring using strain gauge technique and finite element method using ANSYS 14
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