In this article, simultaneous longitudinal and lateral flight control systems design for both passive and active morphing tactical unmanned aerial vehicles (TUAVs) is first time applied for autonomous flight performance maximization in the literature. For this purpose longitudinal and lateral dynamics modelling of TUAVs produced in Erciyes University, Faculty of Aeronautics and Astronautics, Model Aircraft Laboratory are considered in order to obtain simulation environments. Our produced TUAV is called as ZANKA-III which has weight of 50 kg, range of around 3000 km, endurance of around 28 hour, and ceiling altitude of around 12500 m. Von-Karman turbulence modelling is used in order to model atmospheric turbulence during flight in both longitudinal and lateral simulation environments. A stochastic optimization method called as simultaneous perturbation stochastic approximation (i.e. SPSA) is also first time applied in order to obtain optimum dimensions of morphing parameters (i.e. extension ratios of wingspan and tailspan, assembly positions of wing and tailplane to fuselage) and optimum magnitudes of longitudinal and lateral controllers’ gains (i.e. P, I and D gains) while minimizing cost index capturing terms about both longitudinal and lateral autonomous flight performances and there exists lower and upper constraints on all optimization variables in the literature.DOI: http://dx.doi.org/10.5755/j01.eie.23.5.19238

In this study, it is examined that simultaneous flight control system and lateral and longitudional state-space model of a Unmanned Aerial Vehicle (UAV) and real time application. For this purpose an UAV whose wing and tail unit can be assembled to fuselage from different points in a prescribed interval and whose wing and tail can move forward and backward independently in tail to nose direction is manufactured. Following this, an autopilot is purchased and it lets change of P, I, D coefficients in certain intervals. First, dynamic model, and longitudinal and lateral state space models of UAV are obtained and then simulation model of UAV is reached. At the same time block diagram of autopilot system and modeling of it in MATLAB/Simulink environment are found. After these, using these two models and also benefiting and adaptive stochastic optimization method namely SPSA, simultaneous design of UAV and autopilot is done in order to minimize a cost function consisting of rise time, settling time and maximum overshoot. Therefore, primarily autonomous performance is maximized in computer environment. Moreover, high performance is observed by looking at simulation responses and real-time flights.

Unmanned aerial vehicles (UAVs) are air vehicles that can fly remotely or autonomously fly over a certain flight route by themselves. "Unmanned aerial vehicles", which were first produced as military vehicles and then started to be used by civilians, nowadays can easily be bought by everyone. Unmanned aerial vehicles, which can be purchased and made accessible by all, have brought legal disputes and legal regulations together with these disputes. Abuse is obvious because there is a legal vacuum in the field of unmanned aerial vehicles. Of course, it is important for Turkey to work integratedly with the fourth industrial revolution. It is necessary to work like a lucky artificial intelligence, intelligent systems without ignoring the most precious being. In this study, the development process of unmanned aerial vehicles will be examined in terms of the availability of unmanned civil aircraft in air vehicles, the use and flight conditions, the availability of law in the technological development of unmanned aerial vehicles, and the ethical problem of the production and use of these vehicles.

In this article, numerical and experimental analyzes were made by adding winglet and endless blade to the tip of the airfoil to improve the wind turbine blade performance. Similarly, the change in performance was investigated by making notches at different sizes and distances on the trailing edge of the wing structure, inspired by the creatures in nature. First of all, the designed wing structures were analyzed by numerical analysis as a fixed wing, and the lift and drag forces were examined and the aerodynamic performance parameters were examined. Then, the winglet, endless wing and trailing edge notch were mounted to the wing structure cast from a 3D printer, and the energy parameters produced by each design in the wind tunnel were examined. In curved wings, the stress values produced depending on the size of the endless wing structure added to the wing tip have changed and up to 15% aerodynamic performance improvement has been observed in the designed wing structure. In addition, the design was experimentally examined on conventional fixed blades, and up to 6% improvement was observed on fixed blades.

In this study, an unmanned aerial vehicle (UAV) with passive pre-flight and active in-flight morphing capability was designed and manufactured. First of all, conceptual design work was done. Wing and tail, which are the main carriers, were selected to ensure maximum liftt, minimum drag and stability of the UAV. Liquid fuel engines were preferred due to their high power and airtime. The engine, which enables the controlled and uncontrolled flight of the UAV, has been run-in to make it safer and more efficient before being used in real-time flights. Profiles were selected by analyzing the tail set consisting of the rudder and the elevator. The nose cone of the unmanned aerial vehicle was produced by improving the aerodynamic performance. In the aircraft geometry, the passive morphing mechanism, which is performed once before the flight, and the active morphing mechanism, which is performed continuously during the flight, are manufactured using servo motors. This improved the flight performance and made it possible to fly in some unfavorable conditions. The most basic superior feature of the manufactured UAV from the existing UAVs is its ability to morphing.