Structural Integrity Investigations on the Advanced Flying Wing UAV under Various Thermal Loading Conditions through Coupled Engineering Computations

The primary aim of this research is to develop and analyze a sophisticated model of a Flying-Wing Unmanned Aerial Vehicle (FWUAV) that exhibits improved flying capabilities and advanced maneuvering techniques. The FWUAV is capable of functioning in both subsonic and supersonic conditions, and its physical structure is specifically engineered to withstand high-velocity scenarios. Although existing FWUAVs currently operate at moderate speeds, the proposed model is well-suited for a range of high-speed applications. The wing of the FWUAV is designed to mimic the wings of a Peregrine falcon. It features sharp, pointed edges at the front, as well as a slender body and curved wings. These design elements enhance maneuverability and reduce drag on the surface of the model during both forward flight and vertical take-off and landing, regardless of external conditions. The UAV's construction features a unique cupped wing profile, like a three-pointed beak, which enables excellent gliding flight performance, similar to that of a falcon. Due to these unique attributes, the model's lift tends to rise, resulting in increased efficiency in comparison to the current models. The design is created using CATIA software and subsequently analyzed for optimal feasibility using ANSYS Fluent Software. The model undergoes Computational Fluid Dynamics (CFD) Simulations, which are conducted with the required operating circumstances that are suited for the specified application. The computational analysis of the collected data demonstrates the efficacy of the model, while also paving the road for future advancements in the current design proposal. In addition to conducting accurate simulations, the model's structural qualities are also assessed using the fluid-structure interaction (FSI) method to identify the best appropriate material for the framework. The forward speed, vertical speed, rate of ascent, and other parameters are determined by analyzing and comparing the numerical design calculations and employing modern computing tools. These factors are then considered as the concluding factors.