Abstract:

In this study, it is desired to achieve better autonomous performance as a result of the simultaneous design of lateral state-space model and air flow control system (active flow control mechanism) that prevents vortex via pressurized air flow by transferring the pressurized air through channels in the air tank, which is located in the UAVs body where the flow separation caused by swirling on the wing. For this purpose, four different blowing areas, symmetrically two for both wings, were determined by numerical analysis of the location and radius of the blowing areas according to both the wing veter line and the leading edges or trailing edges. After determining the optimum area and location of the blowing zones, the changes in the performance of the straight flight were analyzed in numerical terms according to the first performance of the UAVs. In order to improve autonomous performance by obtaining the state space model of UAV, we tried to improve the rise, settling time, overshoot by using variables P, I, D, and modeled with MATLAB / Simulink. Then, using these data, the flow control and autopilot system on the UAVs were simultaneously designed and the cost function was tried to be minimized by using SPSA which is an adaptive sophisticated optimization method. As a result, it has been observed that by changing the blowing location and radius, it is possible to improve the autonomous performance of the UAVs.

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