Model 540 Rotor Blade Crack Propagation Investigation.

Abstract

The rate of crack propagation from an induced defect in a metal Bell Helicopter 540 main rotor blade was investigated. A controlled crack front was introduced into the top surface of the blade spar. Fatigue testing was conducted at maximum level flight loads and the crack growth was monitored. Experimental data was then comapred with analytical predictions to measure the ability to predict crack growth characteristics. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1979
Accession Number
ADA074734

Entities

People

  • Danny E. Good

Tags

DTIC Thesaurus Topics

  • Aluminum Alloys
  • Bending Moments
  • Centrifugal Force
  • Crack Propagation
  • Crack Tips
  • Engineering
  • Experimental Data
  • Fatigue Tests (Mechanics)
  • Flight Loads
  • Fracture (Mechanics)
  • Geometry
  • Level Flight
  • Materials
  • Mechanics
  • Stress Intensity Factors
  • Stresses
  • Test Equipment

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Materials Science (Mechanical Engineering).