HEAVY-LIFT TIP TURBOJET ROTOR SYSTEM. VOLUME 6. DYNAMIC AND AEROELASTIC STUDIES

Abstract

The studies pertain to dynamic and aeroelastic phenomena of the rotor system for a heavy-lift helicopter employing turbojet engines mounted at the tips of the rotor blades. A majority of the rotor blade frequency and blade flutter boundary work was accomplished using a lumped mass rotor blade simulation on a direct analog computer. The important results of these studies as well as other dynamic investigations which are necessary to insure adequate helicopter performance are included.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1965
Accession Number
AD0624764

Tags

DTIC Thesaurus Topics

  • Aircrafts
  • Analog Computers
  • Blade Tips
  • Boundaries
  • Center Of Gravity
  • Computers
  • Dynamic Response
  • Engines
  • Equations
  • Frequency
  • Helicopters
  • Jet Aircraft
  • Resonant Frequency
  • Simulations
  • Turbines
  • Turbojet Engines
  • Vibration

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Control Systems Engineering.