Design and performance analyses of a fixed wing battery VTOL UAV

Abstract

The objective of this paper is to explain the design steps and performance analyses including energy consumption of a fixed-wing (FW) vertical take-off and landing (VTOL) unmanned air vehicle (UAV). The vehicle is designed from the beginning with the goal for low take-off weight and high aerodynamic performance. Aerodynamic design steps and sizing of both wing and control surfaces are demonstrated and static stability is fulfilled by evaluating the center of gravity location with respect to neutral point. In addition, power requirements and energy consumptions for take-off, climbing, cruise and landing are evaluated in perspective of flight performances to find out the required endurance for each flight condition. In order to do that selected battery is modelled in Simulink and results are represented. In take-off and landing flight conditions, momentum theory is implemented for vertical flight while the cruise flight is utilized to find out the maximum endurance. Drag calculations in level flight are performed in detail to experience the drawbacks of multi-rotor system including propellers providing vertical flight. Finally, VTOL-FW concept having multi-rotor system with four extra propellers and only fixed wing (FW) concept are compared in terms of endurance. It is found that FW concept without multi-rotor system with four propellers have much more endurance compared to VTOL-FW concept. Manufacturing with three-dimensional printers and flight tests of VTOL-FW UAV will be performed as a future work.