The co-simulation method in the composite analysis of the rotor enables connection between Multi Body Dynamics (MBD), Finite Element Method (FEM) and Computational Fluid Dynamics (CFD) by using MATLAB code control algorithms. The idea of unidirectional analysis assumes the use of a rigid rotor model with implemented flexible elements of specific mass-rigidity properties, a special Modal Natural Frequency matrix. In this paper, the MBD model complemented with flexible elements was loaded with inertial forces and additional aerodynamic forces. These aerodynamic forces were determined from CFD analyses considering the aeroelasticity of the rotor blade (static and dynamic characteristics appropriate for a given aerodynamic airfoil). The validation of the computational model was performed on the basis of Virtual Blade Model analyses of the rotor, completed with additional algorithms based on the Blade Element Theory method.

The paper presents selected aspects of numerical analyses on the assessment of the helicopter’s main rotor operational stability, presents key issues for stability assessment, and discusses the application of the co-simulation methodology for helicopter’s main rotor exampled by a prototype unmanned aerial vehicle rotor. The presented approach enables the analysis and mapping of the rotor’s operation taking into account the effects of the aeroelasticity of the blade itself. The impact of wind on the tested structure is presented for two cases and thrust force for the cases of starting the rotor for front and crosswind was evaluated. The transition of the rotor between the idle and working revolutions at a small collective angle does not generate unstable states independently in the wind direction.

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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