A Micromechanics Model of Stiffness Matrix for Composite Rod Reinforced Laminates

摘要

The composite pultruded rod refinforced structures have been considered as a potential application for a new generation of aircraft vehicles because of low cost manufacturing. Conventional analysis using the effective properties of the rod reinforced laminate fails to accurately predict the structural response, particularly, in buckling load. A closed-form micromechanics model of stiffness was develolped to account for the exact position of the rod in the rod layer. The model was validated by the finite element analysis. The variation of the stiffness due to various shapes of the rod was also investigated.