Design, build and test a UAV

• Main Author: Faheem Fawzi
• Other Authors: Basman Elhadidi
• Format: Final Year Project
• Language: English
• Published: Nanyang Technological University 2021
• Subjects: Engineering::Aeronautical engineering
• Online Access: https://hdl.handle.net/10356/150886
• Institution: Nanyang Technological University

The future of vertical take-off and landing (VTOL) aerial vehicles looks promising with various companies having to develop these machines for air transport as well as air deliveries. A lot more tasks can be done by VTOL compared to a helicopter or a fixed-wing aircraft. VTOLS are designed to take off and land on limited amount of space as well as being able to fly as fast as fixed-wing aircrafts. This report consists of the development of a VTOL model that was based on previously developed model. The report will be focusing on the design and manufacturing of the model. A tilt rotor model canard structure was designed and manufactured. To maintain low structural weight, a classical semi-monocoque structure using plywood and balsa was used. Monokote film skin and fibreglass foam core wings were also used. The total weight of the VTOL model was 590 grams including batteries and electronic components. Structural simulation and structural testing were conducted to validate on how good and bad the comparisons are to each other. The structural simulation was conducted through Ansys Structural Simulation while the structural testing was conducted on a manufactured test rig whereby a laser measuring device was used to measure the amount of the deflection. Lastly, flight testing was conducted whereby the VTOL model were put through for different sequence of flight. The first flight test was hovering, followed by tilting of the rotor. Results shows that the VTOL model requires less power when the rotors are tilted as the wings are generating lift.