The implementation of morphing wing applications in aircraft design has sparked significant interest as it enables the dimensional properties of the aircraft to be modified during flight. By allowing manipulation of the 2D and 3D parameters on the aircraft’s wings, tail surfaces, or fuselage, a variety of possibilities have arisen. Two primary schools of thought have emerged in the field of morphing wing applications: the mechanisms school and the smart surfaces approach that uses shape-memory materials and smart actuators. Among the research in this field, the Fishbone Active Camber (FishBAC) approach has emerged as a promising avenue for controlling the deflection of the wing’s trailing edge. This study revisits previous research on morphing wings and the FishBAC concept, evaluates the current state of the field, and presents an original design process flow that includes the design of a unique and innovative UAV called the Stingray within the scope of the study. A novel morphing concept developed for the Stingray UAV, Rear Spar Articulated Wing Camber (RSAWC), employs a fishbone-like morphing wing rib design with rear spar articulation in a cost-effective manner. The design process and flight tests of the RSAWC are presented and directly compared with a conventional wing. Results are evaluated based on performance, weight, cost, and complexity. Semi-empirical data from the flight testing of the concept resulted in approximately a 19% flight endurance increment. The study also presents future directions of research on the RSAWC concept to guide the researchers.

Solar energy is a source of alternative energy for fossil fuels. The importance of solar energy is due to its qualities. It is both unlimited and nondestructive to nature. It also has zero emissions and limitations unlike fossil fuels. In this study, the conceptual design of a solar-powered unmanned aerial vehicle (UAV), with six hours of endurance, is performed. An evaluation of the literature and powertrain architecture design is carried out. Components, such as solar panels, battery, and Maximum Power Point Tracking (MPPT) are evaluated. The city of Eskisehir in Turkey is selected as a flight region with a continental climate. Flight environment and solar energy generation efficiency are investigated. Monthly sunshine times are calculated and compared with the semi empirically calculated power requirement of the UAV. It has been found that the UAV that is the subject of this study can achieve six hours of solar flight during the period between the fourth and the tenth months in Eskisehir, with 472.29 Wh of electrical energy required to be generated within a 1.084 m² wing area.