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Abstract
Unmanned Aerial Vehicle (UAV) Vertical Takeoff Landing (VTOL) or UAV VTOL is designed to have the capacity to carry cargo. The cargo box is an important component with the aim of being able to withstand the load while also maintaining stability or center of gravity on the UAV VTOL and ensuring safety during transportation. This study used an experimental method, by modeling and simulating using a tool, namely Solidworks. The problems that occur in this study are safe design, selection of strong and light materials for use in UAV VTOL cargo boxes. The 3D design modeling of the cargo box on the UAV VTOL is rectangular in shape, with dimensions of Length (W) x Width (W) x Height (T), which is 260 mm x 248 mm x157 mm with a material thickness of 2 mm. The parameter data is adjusted to the height and width of the fuselage. The design and modeling of the UAV VTOL cargo box consists of several components, namely the cargo box, cargo box cover, closing hinges, toogel latches as cover locks and brackets and midlocks as locks for the stability of the cargo box during flight, each part is designed based on geometry and dimensions which has been specified. The locking mechanism of the cargo box cover using toggle latches and the stability of the cargo box in the fuselage with brackets attached to the floor of the fuselage and the midlock lock is an effective combination to secure the payload and maintain the stability of the VTOL UAV during flight. Toggle latches provide convenience and speed in accessing cargo, while brackets and midlock locks ensure the cargo box remains stable and properly locked during flight. Analysis performed on the structure of the cargo box using finite element analysis. The results obtained are the maximum stress that occurs, displacement and safety factor. Cargo box testing was carried out on material and load variations where the material used was aluminum alloy 6061, carbon fiber, fiberglass, also loading variations on the cargo box with a load of 25 kg and 50 kg with a material thickness of 2 mm. For carbon fiber material, the loading of 25 kg results from a stress analysis of 5.1 MPa, a displacement of 0.008 mm while the value of the safety factor is 107, at a loading of 50 kg the results of a stress analysis are 10.2 MPa, a displacement of 0.01 mm while the safety factor value is 53 for carbon fiber material. For the aluminum alloy 6061 material, the loading of 25 kg resulted in a stress analysis of 5 MPa, a displacement of 0.12 mm while the safety factor value was 11, at a loading of 50 kg the result of a stress analysis was 10 MPa, a displacement of 0.24 mm while the safety factor value is 5.5 for aluminum alloy 6061 material. In carbon fiber material, the cargo box has a lighter weight of 0.64 kg than the aluminum alloy cargo box which weighs 1.22 kg and fiberglass. So carbon fiber is lighter and has a stronger structure, but based on the factor of safety all materials are said to be safe based on each SOF standard that is set.