INHERENT VIBRATION DAMPING OF HELICOPTER BLADES.

Abstract

Results are presented of extensive experiments on damping of vibrations in helicopter main rotor blades and compare these results with theoretical and semiempirical methods of predicting blade damping. The feasibility of numerical solution of blade vibration equations which include complex damping effects is demonstrated. Air damping is shown to be relatively unimportant for all but the fundamental bending vibration mode. Structural damping is essentially independent of amplitude but varies significantly with frequency. For much of the experimental data, internal damping of the blade material is the primary source of damping. (Author)

Document Details

Document Type
Technical Report
Publication Date
May 01, 1969
Accession Number
AD0687313

Entities

People

  • Wilfred E. Baker

Organizations

  • Southwest Research Institute

Tags

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Amplitude
  • Doppler Effect
  • Equations
  • Experimental Data
  • Frequency
  • Frequency Shift
  • Helicopter Rotors
  • Helicopters
  • Materials
  • Rotary Wing Aircraft
  • Vehicles
  • Vibration

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Structural Dynamics.