Design, fabrication and analysis of compact unmanned aerial vehicle

The compact unmanned aerial vehicle system is a vehicle that will fly in the air. The performance of the vehicle is controlled by the control unit. All the components are placed in the minimum system. The aim of the present study is to design and fabricate the components of the unmanned aerial vehicle system. The unmanned system contains a flight controller, electronic speed controller, motor, transmitter, receiver, folding propeller, power supply unit, and also a camera for visual mapping. A PPK module is also added to this vehicle as a payload. The designed values for the flight controller, electronic speed controller, motor, transmitter-receiver, and propeller are 1km range and 200m altitude, 22.5amp capacity ESC, 360 kV motor, transmitter range is 1km, 381mm diameter of propellers, and thrust to weight ratio 3.1, respectively. Finally, the four propellers are fixed in four different directions to the arms of the frame. The propeller has been made from carbon fibre. In addition to this, the stress analysis and deformation test at maximum thrust have been studied. The maximum stress and deformation for this analysis are 19.2 x 106 N/m2, and the deformation is 11.2mm. The performance of the compact unmanned aerial vehicle has been studied in the field to obtain surveying data with the help of a camera.