INVESTIGATION OF GENERALIZED METHODS FOR USE OF EXCITATION PANELS TO PRODUCE HELICOPTER ROTOR BLADE FLIGHT FATIGUE LOADS DURING WHIRL TEST.

Abstract

To supplement previous data obtained with three blades, rotors with two and four blades were whirl tested using the excitation panel technique. Rotor blades were tested having two different chord widths. A survey was made of the transient pressures produced on the excitation panels by the rotor blades. The resonant frequency of the third bending mode of the rotor blade was shifted from below the normal operating range to the maximum continuous power-on rpm by adding external weights to the blade leading edge. The use of a counterweight to replace a fatigue-damaged rotor blade during whirl testing was studied and rejected as being overly complicated. (Author)

Document Details

Document Type
Technical Report
Publication Date
Aug 16, 1966
Accession Number
AD0641030

Entities

People

  • J. D. Eakin
  • K. B. Amer

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Excitation
  • Frequency
  • Helicopter Rotors
  • Helicopters
  • Leading Edges
  • Resonant Frequency
  • Rotary Wing Aircraft
  • Vehicles

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Applied Combinatorial Optimization and Logic Circuit Design.