Design And Analysis Of New Quad Tiltrotor Unmanned Aerial Vehicle

The new Quad Tiltrotor unmanned aerial vehicle is capable of vertical take-off, hovering, high-speed cruising, and functioning with a high payload capacity, while remaining efficient and stable. This could be used for airborne geophysical prospecting, air transport and air picturing or a related field. The new Quad Tiltrotor aircraft is on the basis of the traditional tiltrotor aircraft, however, two rotors have been installed on the head and the tail of the fuselage, which make the aircraft more secure and efficient in the switching process between helicopter mode and fixed-wing plane mode.The main purpose of the new Quad Tiltrotor unmanned aerial vehicles is for vertical flight. Therefore, the two rotors on both sides of the fixed wings are angled so that the plane of rotation is horizontal. The new Quad Tiltrotor aircraft lifts the same way a helicopter does, and then after take-off, the two rotors on the head and tail of the fuselage rotate, providing the aircraft with forward speed. When the velocity reaches a certain valve, the lift force that the fixed wings produce is equal to the gravity of the aircraft. At this moment, the two rotors on both sides of the fixed wings do not rotate until the tiltable devices make them turn forward 90 degrees to the vertical position. And at this moment, the four rotors are able to produce enough forward force that the aircraft can fly like a fixed-wing propeller aircraft which depends on the lift that is generated from the fixed wings. By controlling the rotational speed of the rotors and the ailerons, we can control the pitching, yawing and rolling of the aircraft. This also eliminates the need for the horizontal tail and vertical tail which reduces the weight of the structure, increases the payload, and improves the maneuverability and stealth performance.In this paper, the software CATIA is used to produce the three-dimensional model of the new Quad Tiltrotor unmanned aerial vehicle. Then the data of the aircraft is inputted into the software Gambit. Finally, the force a rotor generates, the lift coefficient, the drag coefficient and the pitching moment coefficient under the different flight states are calculated by the software FLUENT. The analysis of the numerical simulation on aerodynamic characteristics of the aircraft will certainly be a reference for the tiltrotor aircraft structure optimization in the future.