Examination of performance of engines used in mini unmanned aerial vehicles and optimization.

Unmanned aerial vehicle (UAV), which first began to be used as a balloon in the 19th century, seems to be large enough to ignore the advantages that today's technology has when it examines areas of use. Especially after the 1990s, high-acceleration developments in technology have caused countries to repeat military strategies. The day has begun to take lighter, faster and more effective tools to replace heavy industrial products. One of these developments is space studies and unmanned aerial vehicles, especially for intelligence purposes. Unmanned aerial vehicles have reached the capacity to do missions that the human body can not tolerate. The performance of these tasks depends on the character and performance of the vehicle designed. The relative performance of an unmanned aerial vehicle depends on many variables. In the design phase, the task to be performed by the vehicle must be considered and all parts of the vehicle must be optimized accordingly. In this context, the most critical part among the parts of the vehicle is the motive. It is a condition that the criteria of the motor should be well defined and its performance should be examined very carefully in the course of the selection or design of the vehicle's engine. In this study, the performance of the model was evaluated by taking into consideration the values of the model of a UAV and the current UAVs and motors such as thrust, weight, speed, wing clearance and duration of the air. In particular, the performance comparison of micro jet engines with other unmanned aerial vehicle engines, which have recently become a focus of attention, has been made. In this study, the behavior of the wings of a radial flow micro jet engine turbine intended for use in the UAV was investigated by the COMSOL computer analysis program, while the model UAV was continuing to examine the engine performance. In order to examine the effect of the change of temperature on the wing, three different heat transfer coefficients were calculated taking into consideration the 7 different flight real conditions of the UAV. The heat transfer coefficients for the turbine outer surface, turbine outer and side surfaces, turbine outer and side surfaces and the central portion were defined in the system and temperature analysis on the blade was made and evaluated. It has been observed that as the speed and height increase, the value of h increases and the effect of cooling increases. Keywords: UAV, jet engine, radial inflow micro jet engine turbine, COMSOL, convection heat transfer coefficient