In this study, in order to develop a vertical takeoff and landing modular body platform that meets takeoff and speed performance, each mission file was prepared for conventional takeoff (CTOL) and vertical takeoff and landing (VTOL) based on the design requirements. The conceptual design took the basic shape and, in the first place, estimated the initial weight of the aircraft components and the entire BOM. After reflecting the components and weights applied to the drones in the design, the main wing shape design, weight center and neutral point prediction, and thrust system design were performed using XFLR5. ANSYS Workbench V14.5 was used for CFD analysis of the aircraft and ICEM-CFD was used as a program to generate Hybrid Mesh (Hexa Mesh & Prism Mesh). Through analytical techniques, the airfoil used for the main wing was designed as NACA4412 and the tail wing was designed as the V-Tail type, which minimizes the aft effects of the thrust device, and the basic airfoil of the tail wing for stability was selected as NACA0009. Because the droneapplied in this study must have the ability to make both a vertical takeoff and a horizontal flight, the N. P. position designed in flight mode and the distance of each rotor of the quadrotor are similarly designed.
Installing a quad copter in H-configuration onto the wings is one of the ways to introduce vertical flight to a fixed wing UAV. Forward flight is attained by tilting the motors to create forward thrust. This paper discusses the design considerations for the Hybrid VTOL UAV and presents the results from flight tests. The motors are electric and powered by Lithium-Polymer batteries. XFLR5 is used to calculate the aerodynamics variables of the design. Drag and flight endurance is calculated empirically and compared against the real values obtained from flight tests.
This paper discusses the design, fabrication and flight test of a vertical takeoff and landing aircraft equipped with a module capable of detecting the position of GPS disturbance signal (jamming signal)when such signal is detected. During the initial shape design, an estimation of the aircraft weight was first made based on the aircraft components and the bill of materials (BOM) of the aircraft. After reflecting the weight of all the components in the design, the shape design of the main wing was performed, followed by center of gravity and neutral point estimation, and propulsion system design. We have fabricated a UAV that can actually takeoff and land vertically and checked its flight performance through real flight tests. An aerodynamic analysis is performed using XFLR5. The E-107 and NACA0012 airfoils were selected as the airfoils for the main wing and tail wings, respectively, and it is designed as H-Tail type for good structural strength. The quad-copter is arranged such that the center of gravity (CG) of the quad-copter motors passes through the neutral point (NP) of the aircraft.
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