A Perturbation Solution of Rotor Flapping Stability

Abstract

The stability of the flapping motion of a single blade of a helicopter rotor is examined using the techniques of perturbation theory. The equation of motion studied is linear, with periodic aerodynamic coefficients due to the forward speed of the rotor. Blade pitch feedback proportional to both flapping displacement and flapping rate is included. Four cases are CONSIDERED: small and large advance ratio, and small and large Lock number. The solution of this problem demonstrates the information which may be obtained using perturbation techniques.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1972
Accession Number
ADA022866

Entities

People

  • Wayne Johnson

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Complex Numbers
  • Differential Equations
  • Eigenvalues
  • Equations
  • Equations Of Motion
  • Frequency
  • Helicopters
  • Mathematical Analysis
  • Nonlinear Differential Equations
  • Numbers
  • Numerical Analysis
  • Partial Differential Equations
  • Perturbation Theory
  • Perturbations
  • Resonant Frequency

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Calculus or Mathematical Analysis
  • Tribology (the study of the boundary interaction between sliding surfaces, lubrication, wear and friction).