Abstract
This article presents the strength analysis of various drive shaft concepts for the test stand for research of aircraft’s main rotors. The results of stress analysis for conceptual shaft models are presented. A technological solution was developed on the basis of the obtained results to meet the design requirements and reduce the impact of maximum stress to a minimum. The aim of the study was to develop a design solution for a propulsion shaft research allowing for the most optimal way of conducting the research installation from a stationary to a rotary system (data and power collector system).
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