Optimization of Rib distance in Wing box of the Aircraft for Maximization of Buckling Load

In Aerospace/aircraft design, to keep the weight as low as possible optimization is paramount for better performance. Optimization of the aircraft component/assemblies fulfil all the design specifications. In aircraft wing design buckling is one of the most critical design parameters. Therefore, while designing it is desirable to achieve minimum weight of the structure with maximum buckling eigenvalue. Buckling analysis plays a vital role in optimizing structural designs, ensuring structural integrity, and preventing catastrophic failures. It allows engineers to assess the stability of structural members under compressive loads, select appropriate materials and dimensions, and implement reinforcement strategies when necessary. Buckling analysis is a critical aspect of structural engineering that focuses on predicting the failure mode known as buckling, which occurs when a slender structural member fails due to excessive compressive forces. Buckling can result in catastrophic failure, making it essential to understand and prevent it in various applications, including buildings, bridges, and aerospace structures. In wing design optimization of buckling strength is possible by varying rib placement distance. In this study we will generate algorithm which will connect CAE tools with optimization technique using MATLAB software. While bending of wing top panel experiences compression and prone for buckling over the wing span therefore optimal placement of ribs to optimize the buckling strength is important. In this study an attempt will be made to generate an algorithm for the optimal placement of rib. The optimization algorithm will govern CAE software to get the optimal design. The project aims to utilize power of optimization algorithm with CAE tools by to investigating how the positioning of ribs within the wing box structure influences buckling behaviour. By systematically studying different rib configurations, the project seeks to identify optimal rib placements that enhance the wing box’s resistance to buckling, providing valuable insights for the design of robust and structurally sound aircraft wings. The project intends to provide valuable insights into the role of rib distribution in improving the structural performance of wing boxes, leading to potential design recommendations and guidelines for optimizing wing box designs to mitigate the risk of buckling failures in aircraft wings.