Hybrid Matrices Layer of Carbon Fiber Composites

Polymeric composites have gone through a level of maturity beyond the laboratory stage with the development of all composite aircraft structures. Yet the basic understanding of the material used in its primary structure has not been extensively investigated. Although this may be attributed in part to the proprietary nature of the system, we believe that it is because of lack of specific tools required for its analysis. Specifically, micromechanical models always assume an evenly distributed homogeneous matrix while lamination theory assumes constant stress through the laminate thickness. Specifically, this work focuses on the development of model systems that can be studied without concerns of proprietary and/or export control requirements. Consequently, the amount of toughness improvement must be balanced between interlaminar and intralaminar fracture toughness. Finally, this work has demonstrated that even though the multilayer structured laminates provide Mode II interlaminar fracture toughness improvements, their mechanical testing behavior is extremely different than conventional composite structures.