Refined analysis of the piezoelectric Pseudo-active control for helicopter blades vibration

Lucian N. Iorga, Haim Baruh, Ioan Ursu

Research output: Contribution to journalConference article

Abstract

In this paper we extend the analysis of a closed-loop control law for vibration reduction in helicopter blades using piezoelectric fiber composites that provide both bending and torsional actuation capabilities. A simple aeroelastic model incorporating lead-lag, napping and torsional degrees of freedom is chosen to evaluate a reduced-state sequential velocity feedback control law. The gain switching logic destined to reduce the transmitted force is complemented by a floating-point genetic algorithm optimization procedure that ensures that optimal values of the control gains are chosen. The control law is shown to be able to generate significant reductions in the harmonics of interest of the blade loads, but inclusion of the higher frequencies in the control synthesis introduces high frequency components in the control inputs.

Original languageEnglish (US)
Pages (from-to)5541-5555
Number of pages15
JournalCollection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Volume8
Publication statusPublished - Dec 19 2005
Event46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference - Austin, TX, United States
Duration: Apr 18 2005Apr 21 2005

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All Science Journal Classification (ASJC) codes

  • Architecture
  • Materials Science(all)
  • Aerospace Engineering
  • Mechanics of Materials
  • Mechanical Engineering

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