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  Design Optimization of Innovative Lightweight Stiffened Thin-walled Lower Helicopter Fuselage Panel with Discrete Source Damage Subjected to Combined In-plane Compression and Shear Loads


   Faculty of Engineering, Computing and the Environment

   Applications accepted all year round  Self-Funded PhD Students Only

About the Project

On the purpose of improving the structural efficiency of stiffened panels, which is widely used in the design and manufacturing of helicopter fuselage panels. Incorporating innovative design and technologies has always posed a significant challenge for aerospace structures designers, particularly when the proposed novel concept challenges the existing knowledge base and the accuracy of commonly used approximate hand calculation methods. This project aims to investigate the structural design and analysis of an innovative lightweight thin-walled panel for helicopter airframe structures via fully integrated finite element analysis and design optimization methods. The optimal feasible designs then will be evaluated based on their performance criteria under the applied loads. To guarantee structural strength and stability, linear static and buckling analyses are performed. Furthermore, the variation of natural frequency and mode shapes of intact and damaged panel structures will be studied. The effects of damage parameters such as damage location and size will be examined when studying the proposed innovative panel structure's characteristics. Various damages will be evaluated, including localized plate thickness loss and stiffness reduction.


Engineering (12) Mathematics (25)

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