Repair concept supported by laser removal and inductive heating

Abstract

With the increasing number of composite applications in aircrafts, it is essential to supply repair concepts with respect to the material properties. In addition to the carbon fiber reinforced composites with a thermoset matrix system, other matrix systems like highperformance thermoplastics have been continuously gaining market share. In comparison to other matrix systems, highperformance thermoplastics have advantages like their ability to reshape and to weld after the first molding process. These advantages can be used to develop new repair concepts. The developing repair concept concentrates mainly on two steps between the detection of the damage and the post repair inspection. One of the steps is the scarfing out with the purpose to remove the damaged area. To simplify this step, the inclusion of a laser support to the repairing process was investigated. As a non-contact, thermal treatment, a UV Laser offers a ply-by-ply removal and can generate a precise stepped-lap repair geometry. With the help of these new possibilities, a load path conforming repair geometry can be developed. Another important step is the application of the repair patch by heating up the interface zone between the patch and the undamaged area. The necessary heat can be generated with the help of inductive heated metallic sheet. The results of the investigations regarding the laser support and the inductive heating will be presented in this paper.