A Fundamental Study in Nonlinear Aeroelastic Phenomena in Flapping Wing Micro Air Vehicles

Abstract

This report describes the development of an aeroelastic model capable of representing in an approximate manner the fundamental nonlinear aeroelastic behavior of flapping wing micro air vehicles in hover. The approximate nature of the model is due to an approximate nonlinear two dimensional unsteady aerodynamic model based on a vortex approach that accounts for the leading edge vortex shed from the leading edge of the flapping wing. This approximate aerodynamic model is coupled with a nonlinear structural dynamic model based on the MARC analysis package that is part of the NASTRAN code. The aeroelastic response solution is obtained from an updated Lagrangian approach for flapping wings with prescribed root motion that resembles insect or hummingbird wing flapping motion. It is shown that wing flexibility modifies the aeroelastic response of the wing, however these changes are relatively modest.

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Document Details

Document Type
Technical Report
Publication Date
Nov 30, 2008
Accession Number
ADA498271

Entities

People

  • Peretz P. Friedmann
  • Wei Shyy

Organizations

  • University of Michigan

Tags

Communities of Interest

  • Air Platforms
  • Autonomy

DTIC Thesaurus Topics

  • Aeroelasticity
  • Aircrafts
  • Birds
  • Computational Fluid Dynamics
  • Equations
  • Equations Of Motion
  • Flow
  • Flow Separation
  • Fluid Dynamics
  • Fluid Flow
  • Leading Edges
  • Mechanical Properties
  • Micro Air Vehicles
  • Resilience
  • Reynolds Number
  • Two Dimensional
  • Vehicles

Fields of Study

  • Physics

Readers

  • Aerial Unmanned Vehicle Swarm Micro Periodontal Dentistry.
  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.