| Due to the conventional four rotor aircraft yawing manipulation is controlled by changing the size of rotor speed, the big speed of rotor is bound to make the body produce a tilting moment, the moment will make the body to tilt toward the direction of small speed rotor, often control direction means need regular inclination of the fuselage.Regular replacement of inclined plane for the need in the normal state of cruising plane filming UAV and can’t make it to reach very high shooting requirements. Secondly,vehicle forward power must also from the fuselage roll rotor of the horizontal component. This means that is no motivation to move forward when the vehicle is in a horizontal state, and it only in a hover state. And in this paper, a distributed independent control of multi rotor aircraft can produce before flying tension without roll body of flight, greatly improving the aerodynamic performance of the aircraft.Distributed independent control of multi rotor aircraft is a combination of a rotor and mechanical aircraft, it consists of six rotor, including to provide propulsion of front and rear rotors, vertical force of four vertical rotor, six rotor are evenly distributed on the circumference of a butterfly shaped rotary table, butterfly shaped rotary internal gear mounting, through the device body within the active gear disc drive turntable rotation,which can drive the rotor to rotate around the axis of the body, which can control the direction of the aircraft without roll body of flight.The thesis makes a detailed introduction to the structural design of distributed independent-control multi-rotors aircrafts and establishes a 3D calculating model with the help of CATIA. Then the profile data of the aircraft is input into Gambit to conduct aerodynamic gird division and set up terminal conditions. At last, aerodynamic calculation and analysis are made by the Fluent. The paper presents a comparative analysis between distributed independent-control multi-rotors aircrafts and ordinary quad-copters in aerodynamic performance on occassions of listing by angles of twenty,fourty and sixty degrees respectively when they are flying. Besides, a comparative analysis is also made to examine wind-resistant performance of the distributed independent-control multi-rotor aircrafts under its different flight modes as well as the impact of rotors’ speed on overall aerodynamic performance. Then the speed of 6m/s is picked out to calculate out needed rotors’ rotational speed under different flight modes of the aircraft. What’s more, the paper is also designs a structure of the sampleaircraft and selects materials that about to use to make the sample. According to the result of numerical simulation, the distributed independent-control multi-rotors aircraft is superior than ordinary quad-copters in aerodynamic performance and it can achieve coupled flight in a way with no need to list its body to obttain propulsion power but still has a certain degree of wind-resistant ability. The result of the the study might provide reference for result optimization and aerodynamic analysis of further studies of rotor-machine combined aircrafts. |
