Effect of Structural Parameters on the Flap-Lag Response of a Rotor Blade in Forward Flight.

Abstract

A study is made of the effect of structural coupling on the vibrations of rigid, centrally hinged rotor blades. In particular, if the parameter combinations that result in desirable stability characteristics might also result in good vibrational characteristics. In order to determine the stability and vibrations simultaneously, a new analytical method, based on eigenvalue and modal decoupling, is developed to solve for the eigenvalues and forced response of systems of equations with periodic coefficients. This method is then applied to the linearized equations of motion for rotor flap-lag in forward flight. Unlike conventional linear analyses, however, this analysis retains the nonlinear terms as added forcing functions.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1978
Accession Number
ADA060331

Entities

People

  • Daniel P. Schrage
  • David A. Peters

Organizations

  • University of Washington

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aerodynamic Forces
  • Aircraft Equipment
  • Aircrafts
  • Airframes
  • Computational Science
  • Computer Programs
  • Differential Equations
  • Eigenvalues
  • Equations
  • Equations Of Motion
  • Geometry
  • Helicopter Rotors
  • Helicopters
  • Military Research
  • Modal Analysis
  • Tail Rotors

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Statistical inference.