Get 20M+ Full-Text Papers For Less Than $1.50/day. Start a 14-Day Trial for You or Your Team.

Learn More →

A simulation investigation of helicopter ground resonance phenomenon

A simulation investigation of helicopter ground resonance phenomenon The purpose of this paper is to present a simulation method applied for investigation of helicopter ground resonance phenomenon.Design/methodology/approachThe considered physical model of helicopter standing on ground with rotating rotor consists of fuselage and main transmission gear treated as stiff bodies connected by elastic elements. The fuselage is supported on landing gear modeled by spring-damper units. The main rotor blades are treated as set of elastic axes with lumped masses distributed along blade radius. Due to Galerkin method, parameters of blades motion are assumed as a combination of bending and torsion eigen modes. A Runge–Kutta method is applied to solve equations of motions of rotor blades and helicopter fuselage.FindingsThe presented simulation method may be applied in preliminary stage of helicopter design to avoid ground resonance by proper selection of landing gear units and blade damper characteristics.Practical implicationsGround resonance may occur in form of violently increasing mutual oscillations of helicopter fuselage and lead-lag motion of rotor blades. According to changes of stiffness and damping characteristics, simulations show stable behavior or arising oscillations of helicopter. The effects of different blade balance or defect of blade damper are predicted.Originality/valueThe simulation method may help to determine the envelope of safe operation of helicopter in phase of take-off or landing. The effects of additional disturbances as results of blades pitch control as swashplate deflection are introduced. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

A simulation investigation of helicopter ground resonance phenomenon

Download PDF
14 pages

Loading next page...
 
/lp/emerald-publishing/a-simulation-investigation-of-helicopter-ground-resonance-phenomenon-90YExYodei
Publisher
Emerald Publishing
Copyright
© Emerald Publishing Limited
ISSN
1748-8842
DOI
10.1108/aeat-11-2017-0256
Publisher site
See Article on Publisher Site

Abstract

The purpose of this paper is to present a simulation method applied for investigation of helicopter ground resonance phenomenon.Design/methodology/approachThe considered physical model of helicopter standing on ground with rotating rotor consists of fuselage and main transmission gear treated as stiff bodies connected by elastic elements. The fuselage is supported on landing gear modeled by spring-damper units. The main rotor blades are treated as set of elastic axes with lumped masses distributed along blade radius. Due to Galerkin method, parameters of blades motion are assumed as a combination of bending and torsion eigen modes. A Runge–Kutta method is applied to solve equations of motions of rotor blades and helicopter fuselage.FindingsThe presented simulation method may be applied in preliminary stage of helicopter design to avoid ground resonance by proper selection of landing gear units and blade damper characteristics.Practical implicationsGround resonance may occur in form of violently increasing mutual oscillations of helicopter fuselage and lead-lag motion of rotor blades. According to changes of stiffness and damping characteristics, simulations show stable behavior or arising oscillations of helicopter. The effects of different blade balance or defect of blade damper are predicted.Originality/valueThe simulation method may help to determine the envelope of safe operation of helicopter in phase of take-off or landing. The effects of additional disturbances as results of blades pitch control as swashplate deflection are introduced.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Mar 13, 2019

Keywords: Helicopter; Ground resonance; Rotor blades

References

  • Analysis of steady-state response regimes of a helicopter ground resonance model including a non-linear energy sink attachment
    Bergeot, B.; Bellizzi, S.; Cochelin, B.
  • Passive suppression of helicopter ground resonance using nonlinear energy sinks attached on the helicopter blades
    Bergeot, B.; Bellizzi, S.; Cochelin, B.
  • Theory of Self-Excited mechanical oscillations of helicopter rotors with hinged blades
    Coleman, R.P.; Feingold, A.M.
  • Design, experiments and development of a polish unmanned helicopter ILX-27
    Gula, P.; Gorecki, T.
  • The influence of unsteady aerodynamics on hingeless rotor ground resonance
    Johnson, W.
  • Milestones in rotorcraft aeromechanics, NASA/TP-2011-215971
    Johnson, W.
  • Effect of free play in rotor blades hinges on the non-linear ground resonance of a helicopter
    Kowaleczko, G.; Dzygadlo, Z.
  • The support process, simulation research design and structure of the new helicopter’s construction schematic with special emphasis on ground resonance phenomenon
    Kowaleczko, G.; Gorecki, T.
  • Aeromechanical stability of soft inplane hingeless rotor helicopters
    Ormistone, R.A.
  • Active control of helicopter ground and air resonance
    Reichert, G.; Arnold, U.
  • Instability zones for isotropic and anisotropic multibladed rotor configurations
    Sanches, L.; Michon, G.; Berlioz, A.; Alazard, D.
  • Parametrically excited helicopter ground resonance dynamics with high blade asymmetries
    Sanches, L.; Michon, G.; Berlioz, A.; Alazard, D.
  • Simulation investigation on the helicopter ground resonance
    Szrajer, M.
  • Comparison of IBC with active controllers using a conventional swashplate to suppress ground and air resonance
    Tettenborn, G.; Kessler, C.; Reichert, G.
  • The ground resonance of a helicopter with a rotor of ideal and approximate symmetry considering the rotor blades vibration in the thrust plane
    Zerek, L.