Finite element analysis of bonded, riveted and hybrid joints in glass fibre epoxy composite laminates for aircraft structure

Because of their superior fatigue resistance and high strength-to-weight ratio, composite materials are essential to the construction of modern airplanes. The joints that interconnect the various parts of these structures play a critical role in their integrity and functionality. In aerospace applications, bonded, riveted, and hybrid joints are among the many types of joints that are frequently used. A thorough finite element analysis (FEA) of hybrid, bonded, and riveted joints in glass fiber epoxy composite laminates for airplane structures is presented in this work. The literature review addresses earlier studies on bonded, riveted, and hybrid joints and emphasizes the importance of joints in composite constructions. There are gaps in our knowledge of these joints' performance under various stress scenarios, despite the fact that previous research offer insightful information about the mechanical behavior and failure processes of these joints. The mechanical behavior of composite materials and the fundamentals of FEA are explained by the theoretical basis. Additionally covered are basic principles that control the behavior of bonded, riveted, and hybrid joints; they set the foundation for further investigation. The manufacturing procedure, experimental setup, and specimen preparation for testing bonded, riveted, and hybrid joints are all described in the methodology. With parameters changed to examine their influence on joint performance, finite element models are created to mimic how joints behave under different loading scenarios. Experiments on mechanical testing of joints yield useful information about failure mechanisms, stiffness, and strength. To verify the accuracy of the numerical models, these outcomes are contrasted with FEA predictions. An analysis of the variables affecting the functionality of various joint types reveals the benefits and drawbacks of each. The stress distribution, deformation, and load-carrying capability of bonded, riveted, and hybrid joints are presented by the results of finite element analysis. The results show how various joint configurations impact structural behavior, offering important information for structural integrity and design optimization. Results from FEA and experimental investigations are interpreted in the discussion, with special attention to the implications for structural applications in airplanes. The comparative study of joint types provides direction for choosing the best joint designs to satisfy particular design specifications. To sum up, this research advances our knowledge of hybrid, bonded, and riveted connections in glass fiber epoxy composite laminates used in aircraft construction. The results provide important information for creating joints that satisfy demanding aerospace performance standards, thereby improving the dependability and safety of aircraft structures.