Design and Aerodynamic Analysis of Vertical Take-Off and Landing Solar Powered UAV

Abstract

This paper presents a conceptual design process for designing and improving the M Solar-X fixed-wing solar-powered unmanned aerial vehicle to have vertical take-off and landing capability (VTOL). The separate lift and thrust vertical take-off and landing is selected for design system. The proposed conceptual design process is simple and not complicated because this type of vertical take-off and landing system has a forward propulsion system and a vertical take-off and landing propulsion system. The function areas of these propulsion systems are clearly separated. In addition, the process of analyzing aerodynamic characteristics using Computational Fluid Dynamics (CFD) is introduced into the design process to verify and validate the design principles. Results from the design process found that the M Solar - X VTOL has a final total weight of 18.9 kilograms, which is an increase of 57.5 percent from the original (fixed-wing). In addition, from the aerodynamic analysis, it is found that vertical take-off and landing propulsion systems installed on fixed wing unmanned aerial vehicles have slightly effect on the lift coefficient, while it will significantly affect the drag coefficient (approximately 20 percent higher at all angles of attack). From the results of preliminary aircraft performance calculations, it is found that the vertical take-off and landing of the solar-powered unmanned aerial vehicle (M Solar-X VTOL) has a stall speed of 13.4 m/s. And the maximum flight endurance performance is 2.21 hours or 2 hours 13 minutes, which satisfy the mission requirements.