Investigation of the Effect of Blade Sweep on Rotor Vibratory Loads.

Abstract

The effect of helicopter rotor blade planform sweep on rotor vibratory hub, blade, and control system loads has been analytically investigated. The importance of sweep angle, sweep initiation radius, flap bending stiffness and torsion bending stiffness is discussed. The mechanism by which sweep influences the vibratory hub loads is investigated. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1983
Accession Number
ADA135603

Entities

People

  • F. J. Tarzanin Jr.
  • R. R. Vlaminck

Organizations

  • Boeing Rotorcraft Systems

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircraft Equipment
  • Aircrafts
  • Airframes
  • Airspeed
  • Bending Moments
  • Blade Tips
  • Computer Programs
  • Computers
  • Control Systems
  • Couplings
  • Frequency
  • Geometry
  • Helicopter Rotors
  • Mach Number
  • Physical Properties
  • Resonant Frequency
  • Stiffness

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Materials Science (Mechanical Engineering).