SUPPRESSION OF TRANSMITTED HARMONIC ROTOR LOADS BY BLADE PITCH CONTROL

Abstract

A method is developed for computing the pitch angle inputs required to eliminate the transmission of harmonic vertical forces from a helicopter rotor to its driving shaft. The inertia and aerodynamic forces due to dynamic blade motions are taken into account in the computations. In finding the aerodynamic loads, a realistic model is used which represents the wake vorticity by a mesh of segmented vortex filaments. Results of computations for three flight conditions are presented for a rotor which is approximately the same as the UH-1A configuration except for assumed differences in pitch control.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1967
Accession Number
AD0665430

Entities

People

  • Hamilton Daughaday

Organizations

  • Calspan

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aerodynamic Forces
  • Aeronautical Laboratories
  • Aircrafts
  • Airfoils
  • Airframes
  • Army Aviation
  • Bending
  • Computer Programs
  • Control Systems
  • Dynamic Response
  • Equations Of Motion
  • Helicopter Rotors
  • Helicopters
  • Plastic Explosives
  • Schematic Diagrams
  • Vibration

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Control Systems Engineering.
  • Structural Dynamics.