G.W.A.I.H.I.R. Guided Wing Aircraft for Intelligent Hybrid Insertion and Recovery

The paper outlines the conceptual and preliminary design of a hybrid vertical takeoff and landing (VTOL) heavy lift unmanned aerial vehicle (UAV) for autonomous cargo transport missions. The primary design objective was to create an aircraft capable of carrying a 15 kg payload over a range of 33 km, achieving a top cruise speed of 45 km/h and maintaining an endurance capacity of at least 90 minutes. A comprehensive literature review informed key design decision, including airfoil selection, structural material, propulsion system configuration, and control. Key requirements were established early in the design process, such as payload capacity, energy efficiency, structural strength, and system integration. Several initial conceptual designs were explored and assessed through a formal trade study process, leading to the selection of a forward-swept wing hybrid VTOL configuration. Extensive analyses were performed across aerodynamics, structures, propulsion, and sizing fields, backed by computational modeling and simulation tools. The thrust system was chosen using a weighted decision matrix that considered thrust requirements, efficiency, weight, and cost. Airfoil selection involved comparing low Reynolds number performance and drag polars, leading to the choice of the FX 63-137 airfoil profile as the best option. Structural design was validated through lift distribution modeling, shear force and bending moment calculations, and conservative material selection practices. A comprehensive 3D CAD design was utilized to integrate aerodynamic, structural, and subsystem elements with manufacturability and weight distribution. The results demonstrate the technical credibility of the design in meeting the mission requirements. Final recommendations are provided to guide ongoing development, including enhancements to autonomous control methods, comprehensive finite element structural analysis, and prototype fabrication for flight evaluation.