Finite Element Method Analysis on VTP to Determine Initial Crack Location at Nxxx Aircraft using MPC to Distribute Loads

In the field of aviation, every aircraft component plays a crucial role in ensuring safety, stability, and optimal performance during flight. One of these components, which plays a critical role, is the Vertical Tail Plane (VTP) or vertical stabilizer. The VTP not only provides vertical stability but also functions as a vital control tool for pilots to maintain the flight path and respond to external changes. Inspection and thickness improvements, along with the application of Multi-Point Constraint (MPC) to the VTP structure, are essential steps in the manufacturing process to prevent production errors that could cause damage to the aircraft. This study aims to determine the location of the initial crack in the VTP structure, which will then be used to calculate the crack propagation rate. If the crack propagation rate is fast, the geometry of the structure needs to be modified. The method used in this analysis is the Finite Element Method (FEM), implemented using MSC PATRAN software. By using FEM, thickness improvements and MPC application can be performed quickly and efficiently, ensuring that the analysis produces a safe and high-quality VTP component.