| Popis: |
This paper deals with the conceptual design of fixed wing Vertical Take-Off and Landing (VTOL) Unmanned Aerial Vehicle (UAV) of mini category. The UAV is designed as per the mission requirement including wing, fuselage, empennage and tilt-rotor mechanism. The UAV is then analysed for its aerodynamic, performance and stability analysis. Wing, fuselage, empennage and tilt-rotor mechanism is designed and modelled in OpenVSP and the whole UAV is analysed in VSPAero. The UAV designed has payload carrying capacity of 2kg – 4kg, range of 90 km (with 2 kg payload), stall speed of 11.8m/s (without payload), 13.8m/s (with 2 kg payload) and endurance of 1.52 hrs (with 2 kg payload). The UAV being a fixed wing -VTOL system has better reach to geographically challenging areas than the fixed wing counterparts (like UAV Factory Penguin C/B/BE UAVs) and also less power consumption, higher speed and high payload carrying capacity compared to rotary wing counterparts (like DJI drones). |
