EFFECTS OF NONLINEAR DAMPING IN LANDING GEAR ON HELICOPTER LIMIT CYCLE RESPONSE IN GROUND RESONANCE.

Published

Journal Article

An approximate theoretical method is presented which predicts the limit cycle behavior of a simplified helicopter model in ground resonance, considering the effects of one or two nonlinear dampers in the landing gear. The relationship between lagging motion of the blades and fuselage motion during ground resonance is discussed. The theoretical predictions agree reasonably well with experimental results obtained for three model configurations selected to provide physical understanding of the dynamic phenomena involved.

Duke Authors

Cited Authors

  • Tang, DM; Dowell, EH

Published Date

  • January 1, 1987

Published In

Volume / Issue

  • 32 / 1

Start / End Page

  • 45 - 53

International Standard Serial Number (ISSN)

  • 0002-8711

Citation Source

  • Scopus