Limiting Performance of Nonlinear Systems with Applications to Helicopter Vibration Control.

Abstract

Several problems concerning the vibration control of helicopters were studied. A method for introducing structural modifications leading to vibration reduction has been developed. In particular, a formulation for attaching appendages to continuous structural members was completed and applied to a two-beam helicopter model. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1985
Accession Number
ADA161457

Entities

People

  • W. D. Pilkey

Organizations

  • University of Virginia

Tags

Communities of Interest

  • Air Platforms
  • Human Systems
  • Space

DTIC Thesaurus Topics

  • Abstracts
  • Aircrafts
  • Applied Mechanics
  • Classification
  • Eigenvalues
  • Equations
  • Frequency
  • Frequency Response
  • Helicopters
  • Linear Systems
  • Mechanical Structure
  • Military Research
  • Nonlinear Systems
  • Resonant Frequency
  • Scientists
  • Universities
  • Vibration

Readers

  • Aerospace Engineering
  • Optical Physics and Photonics.
  • Systems Analysis and Design