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The vibration parameters of a bi-copter-type unmanned aerial vehicle is optimized by considering operational vibration with payloads. The double electric ducted fan loads, which transmit excitations to the fuselage, are predicted and compared using optimization methods. While the minimum vibration amplitude for stress will be achieved at 7.69 Hz, it will be 9.80 Hz. for minimum deformation without sacrificing safety factor requirement. It ensures sensitive vertical acceleration. It is not seen significant differences on results from screening and genetic algorithm methods. Correlations between frequencies and structural responses are determined. It is observed that the stress and deformation amplitudes of the structure decreases at increasing frequencies up to the next natural frequency. While the highest amplitude is seen at the first frequency, it decreases in increasing modes. The airframe structural model’s operational frequency must be 7.69 or 9.80 Hz to achieve sensitive vertical acceleration. Subsequently, it is aimed to develop an autonomous task by the implemented system controlled by various algorithm as a future work.

Parameter Optimization of a Bi-copter Type Unmanned Aerial Vehicle to Avoid Propeller-induced Vibrations During Hovering