ABSTRACT
The difficulties encountered in attempting to model titanium matrix composites (TMCs) is directly related to the application environment. As a high-temperature material for aerospace applications, TMCs are expected to experience extreme thermal and mechanical loads, such as is found in propulsion systems and hypersonic airframe components. Although many different discrete analyses have been used, this chapter primarily limits the discussion to those that have been embedded into readily available computer programs and the finite element method. The micromechanics models that are available in computer programs consist of the multicell model, the vanishing fiber diameter model, the concentric cylinder approach, and the method of cells. The chapter summarizes the models by discussing their constitutive relations, nonlinear capabilities, results, and how they have been used to analyze metal matrix composites.
