Rotorcraft fuselage/main rotor coupling dynamics modelling and analysis Articles uri icon

publication date

  • November 2020

start page

  • 317

end page

  • 340

issue

  • 3-4

volume

  • 22

International Standard Serial Number (ISSN)

  • 1565-1339

Electronic International Standard Serial Number (EISSN)

  • 2191-0294

abstract

  • This article presents the fuselage/main rotor coupling dynamics under a modal analysis to study the modes of oscillation. The authors provide a rotorcraft simulation model that captures complex dynamics, wherein the validation is done with existing theories. The model has been set up by using VehicleSim, software specialized in modelling mechanical systems composed by rigid bodies. It is presented a helicopter simulation framework, that allows to study the impact of the main rotor varying angular speed on the system. Moreover, the generated heterodyning behaviour and harmonics can be analysed on the fuselage. The detection of this performance is not a simple task, and this helicopter model provides an accurate system for its study using a short-time Fourier transform processing. The coupled dynamics observed between the fuselage and the main rotor indicate that the model can be a suitable tool to detect this type of performance.

keywords

  • fuselage; heterodyning; modal analysis; rotor