1. N. C. AJAY VISHWATH - Assistant Professor, Aeronautical Department, Parul University, Vadodara, India.
2. SUJEET KUMAR PANDEY - Assistant Professor, School of Engineering and Technology, Department of Aerospace Engineering, Sandip University, India.
3. MANSHA KUMARI B. PATEL - Assistant Professor, Aeronautical Department, Parul University, India.
4. Dr. VIJAY KUMAR PATIDAR - Head of the Department, Aeronautical Department, Parul University, Vadodara, India.
This research work focus on the stability part of a tilt rotor unmanned aerial vehicle and the different parameter requires operating the tilt rotor unmanned aerial vehicle during its different phases of flight. The work starts from the definition of tilt rotor mechanism and proceeding to the design of the same. Combination of a brushless DC motor with appropriate variable pitch propeller is used as a thruster which will produce necessary thrust in required direction to lift the whole body with electronic payload that is required to generate thrust. The thrusters being situated at the tips of the wing eases the process of tilting through servo motors. The combination of the rectangular wing and the tail consisting of vertical stabilizers as well as horizontal stabilizer will make sure the aircraft is stable during different phases of tilt rotor unmanned aerial vehicle’s flight. The ‘H-tail’ configured tail being tilted up and down with the servo motor helps the aircraft to arrest all the unnecessary disturbances by generating the moments about center of gravity in required angle. After defining the different flight conditions, i.e. hovering, climbing and forward motion, the research work proceeds to calculating the different parameters required in rotary aircrafts. These parameters will help us to understand the heat of the problems that will be associated by the tilt rotor mechanics. The results after the calculations are more satisfying. From the results, this research work will conclude that the design of tilt rotor unmanned aerial vehicle will operate in different phases of flight comfortably. The major step taken for the stability of the aircraft in helicopter mode, airplane mode as well as in the transition period is the design of the tail. The tail is designed in such a way that it can counteract any disturbances occurring in horizontal plain or vertical plane. The design of the tail makes this research paper work unique. Servos are used to tilt the whole tail which consists of horizontal stabilizer as well as vertical stabilizers. To define the stability this research work considered the contribution of the wing, fuselage and tail which together will define the longitudinal stability of the aircraft. The results after the stability calculations are more satisfying. From the results this research work concluding that the designed tilt rotor unmanned aerial vehicle will be stable in its flight.
Tilt Rotor, Stability, UAV, Different flight phases.