Hybrid Materials and Structures for Aeronautic Applications

Abstract

A further increase in the strength to density ratio in lightweight structural materials with good impact and damage tolerance can only be achieved by a combination of low density fiber reinforced polymers with lightweight metals of high strength. Thus, the integrity of polymer/metal interfaces plays a central role in future weight reduction for transport applications. Particular demonstrator applications are fiber metal laminates (FML) for light weight high strength structures with high stiffness and high toughness. With the aid of the knowledge from characterization and modeling the material can be optimized regarding certain properties. In this way it is envisaged to develop a high performance material system with significantly increased damage tolerance and further improved strength to density and stiffness to density ratios in comparison to available materials, such as for example GLARE®. Results of the development of hybrid structures for aeroengine applications are transferred to the manufacturing of titanium-carbon fiber PEEK laminates. The development is driven by a close interaction of numerical and experimental methods. Theoretical and experimental studies regarding the mechanical potential of the hybrid laminates will be presented. Furthermore, the development of long-term stable interfaces is an objective.