Determination of the effect of production temperature and stacking parameters on the mechanical behavior of the thermoplastic composite lugs

Defense and aerospace technologies are developing rapidly day by day. Due to the demand on reduction of weight is such an essential issue in aviation, research into lighter materials has lately increased. At this point, composite materials are constantly developing as a field of use in aerospace. Thermoset composites are already widely used in the aviation industry, although thermoplastic composites are still the subject of research to expand their application. Because of its re-formability and ease of processing, as well as the convenience of stocking raw materials, thermoplastic composites have an advantage over thermoset composites. The goal of this thesis is to assess the impact of curing temperature on mechanical strength during autoclave manufacturing of poly-ether-ketone-ketone matrix carbon fiber reinforced (CF/PEKK) composites, which have recently been studied in defense and aerospace industries. The effect of the mechanical strength of the composite lug structures on the layup parameter will be investigated after the ideal curing temperature has been determined. In rotary-wing aircraft, composite lug structures are perforated structures that connect the rotor and blades. They play a crucial role in rotary-wing aircraft as primary structural parts. As a result of mechanical evaluation, performed static and fatigue test of the thermoplastic composite lugs were found to be successful. The tests conducted as part of this thesis demonstrate the usability of composite lug structures, which can be employed in a rotary-wing aircraft with a conceptual design, after more extensive testing. Furthermore, process parameters in the production phase have been clarified, and it is expected to serve as a foundation for future research.