![]() The article is the first in the literature in terms of the problem obtained and the application of the AHP method to this problem. In this study, engine alternatives available in the market for UAVs with take-off weights of 750 to 800 grams were evaluated in terms of mechanical and physical criteria of engine systems, and as a result, the ideal engine model was determined by Analytical Hierarchy method for maximum stabilization and velocity purposes. The most important system affecting these performance criteria is the engine. The main ones of these performances are stabilization and engine power. UAV systems contain many electronic and mechanical systems and many performance criteria can be found for UAV systems. Furthermore, considering their hobby use, it is understood that UAVs have a large commercial market and a high economic value. UAVs are used extensively in many areas, especially in logistics processes, search and rescue activities, military operations, fight to forest fires, photography, monitoring and inspection of agricultural processes. Unmanned Aerial Vehicles are electronic systems that are used extensively in every field today and that develop and change very quickly with technology. ![]() Thus, the blade designed for high altitude SAR UAV is structurally safe to operate in 0-5,000 RPM range, and its use in search missions could save many lives in the Himalayas. The CFD analysis was performed in ANSYS CFX which gave a thrust value of 2.27 N for the same boundary conditions. The validation of experimental results has been done by the CFD analysis. The analytical solution for thrust with the same conditions was 1.7 N with 85.6% efficiency. Experimental analysis of the blade gave a thrust of 0.92 N at 2,697 RPM at 1,400 m. The modal analysis shows the first natural frequency occurs at around 12,000 RPM which is safe for operating the blade at 0-5,000 RPM. This stress is within the limit of yield strength of the aluminum alloy, 28 MPa. The geometry designed for an altitude range of 3,000-5,000 m faced the total stress of 6.0 MPa which was at 70% of the blade span. The blade element theory-based design and analysis code was developed, and user-friendly aerodynamic inputs were used to obtain the desired outputs. The property of aluminum alloy 1,060 being lightweight is chosen for designing and testing of blade. ![]() The objective of this research work is to design thrust optimized blade for an altitude range of 3,000–5,000 m with a density of air 0.7364 kg/m3, respectively, and perform thrust analysis. This is because as the altitude increases, the density of air decreases which affects the thrust generation of the UAV. The commercially available unmanned aerial vehicles are not good enough for search and rescue flight at high altitudes. ![]()
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