Nonlinear Aeroelastic Study for Folding Wing Structures

Abstract

A folding wing structure consisting of three components: fuselage, inboard wing and outboard wing, is modeled computationally using a geometrically nonlinear structural dynamics theory based upon von Karman strains and at three-dimensional nonlinear potential flow aerodynamic model. The structural dynamic equations of motion are discretized in space using a discrete Ritz basis derived from finite element analysis and component synthesis and the aerodynamic model is discretized using a vortex lattice. Results from the computational model are compared to those from experiments designed and tested in the Duke University wind tunnel for three folding wing configurations. It is found that limit cycle oscillation magnitude and frequency results from theory compare well with those measured in the experiment. Also it appears that structural nonlinearities are stronger than aerodynamic nonlinearities for the cases studied.

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Document Details

Document Type
Technical Report
Publication Date
Mar 29, 2010
Accession Number
ADA519459

Entities

People

  • Deman Tang
  • Earl H. Dowell
  • Peter Attar

Organizations

  • Duke University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aircrafts
  • Coordinate Systems
  • Discrete Fourier Transforms
  • Dynamic Response
  • Engineering
  • Equations
  • Equations Of Motion
  • Finite Element Analysis
  • Folding Wings
  • Frequency
  • Geometry
  • Materials
  • Materials Science
  • Mechanical Engineering
  • Modal Analysis
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Aerodynamics/Aeronautics.
  • Structural Dynamics.

Technology Areas

  • Space