Abstract
Currently, unmanned aerial vehicles are increasingly used to solve various problems. Analysis of the information shows that in our country there are a number of problems in the development and production of these devices. One of the most important problems is that until recently certain elements of drones were not produced in our country, but were imported from abroad, but due to external sanctions, there was a need to quickly organize the production of these components at Russian enterprises. However, for this, it is necessary to have techniques that allow the design of individual components taking into account the purpose of the unmanned aerial vehicle. Considering the fact that all components of an unmanned aerial vehicle are interconnected and mutually influence each other, as well as the flight performance characteristics of the device as a whole, the issue of developing requirements and criteria for selecting elements of the device depending on its purpose is an urgent task of the day. In order to optimally select a propeller and an electric motor for the propeller-motor group of an unmanned aerial vehicle, it is important to know the features and patterns of the processes of their mutual influence; in this regard, we propose a method for determining the electric motor parameters of the propeller-motor group of an unmanned quadcopter based on the basic principles of classical mechanics. During the research, an analysis was carried out of the electric motor parameters influence on the flight performance characteristics of an unmanned aerial vehicle, taking into account the purpose and operating characteristics of the quadcopter. The article also presents the results of experimental studies aimed at confirming the correctness of the proposed method for selecting an electric motor for a propeller pair.
Keywords
unmanned aerial vehicle, quadcopter, flight performance, thrust force, propeller group, electric motor
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