Structural comparison of vertical and horizontal layout of carrying arms of rotary-wing UAV with finite element analysis

Abstract

In this study, numerical analysis of the fuselage of a rotary wing unmanned aerial vehicle was conducted. A fuselage that is resistant to the loads on the fuselage and has maximum lightness has been designed. In this context, the fuselage design was conducted based on the loads that the aircraft's fuselage would be exposed to during landing and take-off, and a three-dimensional modeling was created. Numerical analyzes were carried out using the designed solid model finite element method. It has been observed that the obtained data can meet the loads on the airframe without any breakage in the specified configuration. The findings obtained at the end of the study were supported by graphics