PREDICTION OF ROTOR INSTABILITY AT HIGH FORWARD SPEEDS. VOLUME 1. STEADY FLIGHT DIFFERENTIAL EQUATIONS OF MOTION FOR A FLEXIBLE HELICOPTER BLADE WITH CHORDWISE MASS UNBALANCE

Abstract

The differential equations of motion for a linearly twisted rotor blade having chordwise mass unbalance and operating under steady flight conditions are derived. The motions include flapping and lagging for the articulated blade, as well as flatwise, edgewise, and torsional deformations for the articulated and nonarticulated blades. The fully coupled aerodynamic forcing functions are based on quasi-steady theory. The differential equations of motion are expanded in terms of the uncoupled vibratory modes of the blade in order to facilitate their numerical solution on a digital computer.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1969
Accession Number
AD0685860

Entities

People

  • Peter J. Arcidiacono

Organizations

  • United Technologies Corporation

Tags

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Aircrafts
  • Army Aviation
  • Center Of Gravity
  • Computational Fluid Dynamics
  • Control Systems
  • Differential Equations
  • Equations
  • Equations Of Motion
  • Frequency
  • Helicopter Rotors
  • Lead Angle
  • Mechanics
  • Modulus Of Elasticity
  • Resonant Frequency
  • Two Dimensional
  • Vibration

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)