VIBRATIONS OF A HELICOPTER ROTOR SYSTEM AND FUSELAGE INDUCED BY THE MAIN ROTOR BLADES IN FLIGHT

Abstract

Based on a simplified model of the hub-fuselage structure, a theoretical analysis is made of the response of the hub and fuselage of a helicopter in flight to harmonic forces transmitted by the rotor blades to the hub both in, and normal to, the plan of rotation. The assumed structure is in the form of a plane framework with masses concentrated at the joints. Simple expressions are derived for the vibration amplitudes of the mass points as functions of the masses and natural frequencies of the hub and the fuselage. The pertinent non-dimensional parameters are determined, and simple explicit conditions of resonance are derived. Numerical examples are given to illustrate the results.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1953
Accession Number
AD0021969

Entities

People

  • H. Reissner
  • Morris Morduchow
  • Shao W. Yuan

Organizations

  • New York University Tandon School of Engineering

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Airframes
  • Differential Equations
  • Equations
  • Equations Of Motion
  • Frequency
  • Fuselages
  • Helicopter Rotors
  • Helicopters
  • Linear Differential Equations
  • Resonance
  • Resonant Frequency
  • Structural Components
  • United States
  • Vibration

Fields of Study

  • Engineering
  • Physics

Readers

  • Aerodynamics.
  • Structural Dynamics.