Rotorcraft aeroelastic stability using robust analysis

Giuseppe Quaranta, Aykut Tamer, Vincenzo Muscarello, Pierangelo Masarati, Massimo Gennaretti, Jacopo Serafini, Marco Molica Colella

Research output: Contribution to journalArticlepeer-review

21 Citations (SciVal)


This paper discusses the impact of different models of aerodynamic loads on rotorcraft-pilot couplings stability using a robust stability analysis approach. The aeroelasticity of the main rotor of a helicopter is formulated using aerodynamic models based on the blade element/momentum theory and boundary element method coupled to a finite element model of the blade. The resulting linearized models are used to determine stability limits according to the generalized Nyquist criterion, associated with the accelerations of the pilot’s seat caused by the involuntary action of the pilot on the control inceptors. The resulting stability curves are discussed considering examples of involuntary pilot transfer functions from the literature.

Original languageEnglish
Pages (from-to)29-39
Number of pages11
JournalCEAS Aeronautical Journal
Issue number1
Early online date9 Aug 2013
Publication statusPublished - 31 Mar 2014

Bibliographical note

Publisher Copyright:
© Deutsches Zentrum für Luft- und Raumfahrt e.V. 2013


  • Robust stability
  • Rotorcraft aeroelasticity
  • Rotorcraft-pilot couplings

ASJC Scopus subject areas

  • Transportation
  • Aerospace Engineering


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