New generation electric tail rotor performance analyses

The electric tail rotor is an anti-torque system used to balance the torque effect created by the main rotor of rotary-wing aircraft and is provided its power requirement from batteries. Tail rotors used in conventional helicopters are not electric, and power transmission is made with the shaft system connected to the main rotor in a certain gear ratio. The new generation electric tail rotors have many differences. Drive system, exposed loudness and power consumption are some of the differences between the two rotor systems. The electric tail rotor can be dimensionally diversified as regards to need and can be used more than once in various configurations. Therefore, the volume occupied by the tail rotor may differ compared to conventional tail rotors. When the results of the volumetric difference are examined, it is seen that there are differences in power consumption. Considering all these differences, the tail rotor performance data of UH-60 helicopter having the conventional tail rotor were examined. At the same time, the performance review was repeated by applying the innovative electric tail rotor conceptual design to the UH-60 helicopter. Blade Element Momentum Theory was used to make the necessary performance calculations. By considering nonlinear effects due to viscous flow, profile drag effects in blade section and tip losses, the formulation was modified to give results closer to the experimental data. Calculus model was created to observe from root to end the change in thrust and power consumption of blade. With the help of the calculus model, the power consumption and thrust generation values of the two rotor systems were compared and the relevant results were presented in various tables and graphics.