A Micromechanical Fatigue Damage Model for Unidirectional Metal-matrix Composites

摘要

Improvements in design and the enhancement in perofrmance of aerospace vehicles calls for the development of advanced materials capable of sustainign the increaisng loading conditions while maintaining their structural integrity. Special consideration must be given to the behavior of such materials under fatigue loading conditions that dominate the flight regime loads. A micromechanical fatigue damage model for unidirectional metal-matrix composites is propsoed. Damage evolution is considered at the constituent level through the application of the Mori-Tanaka averaging scheme. Individual damage criteria for the constituents are proposed and employed to define damage evolution equations for each of the consultants. The numerical results for high cycle fatigue loading are presented for variations in the material and model parameters.