| Intake system of piston UAV (unmanned aerial vehicle) engine is like the artery of heart, providing clean air and fuel for the engine. The mixture of oil and gas is finished in this region. In this project, an in-flight icing phenomenon is occurred in the engine intake system. As the main source of icing accidents in this system, the icing phenomenon is one of the most important factor affect the aircraft performance and flight safety.This research is based on the two main conditions of icing:the material and temperature, according to the mechanism of icing. Equations of fluid motion is established, combined the theory of describing fluid motion in fluid dynamics. Turbulence modeling of intake system is completed by using numerical simulation. The trajectory and captured position distribution on the tube wall of intake system of droplet are got, by establishing discrete phase model and simulating the motion of droplet. After the physical model is changed of intake system, the motion of droplet in different sized structures and deposition law on tube wall is obtained. The influence of carburetor to intake system cooling, during flight, ground test and heat up environment etc, is simulated by establishing spray model, and de-icing method is concluded based on this.The result of intake icing research is the same as the data of experiment during flight and on ground. It well proved the physical model of this paper can accurately reflect the real situation. Intake icing problem can be analyzed using CFD numerical simulation accurately. The work of this paper explore a better method for the deep research of intake icing in future. |
