CD Skripsi
Rancang Bangun Struktur Rangka Multicopter Tipe Empat Baling-Baling (Quadcopter) Untuk Kebutuhan Pemetaan Udara
Quadcopter is an unmanned flying vehicle whose lift force is produced by the rotation of the driving motor. One type of multicopter that is widely used to conduct aerial mapping missions is the quadcopter type. In this study the design of the quadcopter frame structure was able to fly for more than 20 minutes with a MTOW quadcopter flying vehicle of 5 kg with a payload of 1.5 kg. The purpose of this study is to produce a design and prototype of a quadopteral frame and to analyze the strength of the skeletal structure with the Finite Element Method using Ansys 16.0 Software. The resulting quadcopter frame dimensions of 790 mm were obtained based on the motor and propeller used. For the material used on the middle plate and quadcopter arm, carbonfiber material is chosen because it has a low density with high Ultimate Tensile Strength and Young's Modulus. Then the quadcopter frame is carried out static structural simulation to analyze the strength of the frame structure, in the loading simulation given to the mounting motor of 2.5 kg and the type of Remote Displacement pedestal at the center of gravity of the lower center plate. Simulation results in the form of voltage, deflection and safety factors. The maximum stress is 34.90 MPa, the maximum deflection is 3.67 and the safety factor is 13.61. For validation, the simulation deflection results are compared with the actual deflection and theoretical calculations and the simulation voltage results are compared with the theoretical calculation voltage results. The result of simulation and actual deflection has the highest percent error of 8.62%. While the percent error on the simulation voltage results with a theoretical voltage is 2.95%.
Keywords: Quadcopter Framework, Static Structural simulation, Carbon Fiber, Ansys Software 16.0
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