Investigation of the Effect of Torsional Natural Frequency on Stall- Induced Dynamic Loading

Abstract

For helicopter flight conditions at high blade loadings or airspeeds, the rotor control system experiences a rapid load growth resulting from stall- induced blade torsional moments. These loads frequently grow so large that the aircraft flight envelope is restricted. This report describes an analytical study that determined the effect of changing blade torsional properties on control loads for a wide range of flight conditions.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1974
Accession Number
AD0776415

Entities

People

  • F. J. Tarzanin
  • Joseph Ranieri

Organizations

  • Boeing Rotorcraft Systems

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircraft Industry
  • Aircrafts
  • Airframes
  • Center Of Gravity
  • Control Systems
  • Dynamic Loads
  • Dynamic Response
  • Geometry
  • Helicopter Rotors
  • Helicopters
  • Mach Number
  • Measurement
  • Physical Properties
  • Resonant Frequency
  • Two Dimensional
  • Waveforms
  • Wind Tunnel Tests

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Control Systems Engineering.