Survey of Army/NASA Rotorcraft Aeroelastic Stability Research

Abstract

Theoretical and experimental developments in the aeroelastic and aeromechanical stability of helicopters and tilt-rotor aircraft are addressed. Included are the underlying nonlinear structural mechanics of slender rotating beams, necessary for accurate modeling of elastic cantilever rotor blades, and the development of dynamic inflow, an unsteady aerodynamic theory for low- frequency aeroelastic stability applications. Analytical treatment of isolated rotor stability in hover and forward flight, coupled rotor-fuselage stability in hover and forward flight, and analysis of tilt-rotor dynamic stability are considered. Results of parametric investigations of system behavior are presented, and correlations between theoretical results and experimental data from small- and large-scale wind tunnel and flight testing are discussed.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1988
Accession Number
ADA233220

Entities

People

  • David A. Peters
  • Dewey H. Hodges
  • Robert A. Ormiston
  • William G. Warmbrodt

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeroelasticity
  • Aircraft Equipment
  • Aircraft Industry
  • Aircrafts
  • Airframes
  • Composite Materials
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Finite Element Analysis
  • Fluid Dynamics
  • Fuselages
  • Helicopter Rotors
  • Mechanics
  • Three Dimensional
  • Tilt Rotor Aircraft
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Computational Fluid Dynamics (CFD)