Topological optimization of a ducted propeller of UAV

• Published in: Avìacìjno-kosmìčna tehnìka ì tehnologìâ no. 4
• Main Authors: Anton Balalaiev, Kateryna Balalaieva, Grygoriy Golembiyevskyy, Andrii Melchenko, Vyacheslav Usenko
• Format: Journal Article
• Language: English
• Published: National Aerospace University «Kharkiv Aviation Institute 01.08.2025
• Subjects: бпла; капот; маса; напружено-деформаний стан; повітряний гвинт; статична міцність; топологічна оптимізація; числове моделювання
• ISSN: 1727-7337; 2663-2217
• DOI: 10.32620/aktt.2025.4.04

The subject of this study is the minimization of the duct mass for a ducted propeller of UAV. The object of this study is a two-bladed ducted quadcopter propeller. The peripheral diameter of the propeller is 128 mm, and the hood is 2 mm thick. The propeller rotates along with the duct. The purpose of this study is to analyze the design of the ducted propeller of UAV in terms of reducing the mass by applying topological optimization methods. The following tasks were performed to achieve the set goal: the stress-strain state of the ducted propeller of UAV was calculated under static strength conditions; topological optimization of the ducted propeller of UAV was performed; and a model of the ducted propeller was built considering topological optimization. The study used numerical experiment and topological optimization methods. The calculations were performed in the Ansys Workbench software environment; the Geometry, Static Structural, and Structural Optimization modules were used for the selected problem. Results: The results of the analysis of the design of the ducted propeller of UAV are presented to reduce the mass by applying topological optimization methods. Based on the results of calculating the stress-strain state of the UAV ducted propeller under static strength conditions, the hood was topologically optimized. The results of topological optimization made it possible to lighten the duct design by adding holes in the form of oval - round windows in the lower part of the duct and changing the shape of the wavy upper edge of the duct. Based on the topological optimization results, an updated model of the ducted propeller of UAV was built. The ducted propeller has a less weight of 20.23 % and has the necessary safety margin. These studies assess the aerodynamic characteristics of a ducted propeller with an updated duct shape. Scientific novelty and practical significance of the work: new data were obtained on the analysis of the design of the ducted propeller of UAV by applying topological optimization. The obtained results can be used in the development of promising UAV propellers.