Integrated Intelligent Structures for Suppressing Static Aerothermoelastic Deformation and Flutter of Panels.

Abstract

This document presents nonlinear panel flutter suppression study which has been accomplished by using both the finite element method and the classical continuum method. The results show that: (1) The bending moment is more effective than inplane force in active suppression using piezoelectric actuation. (2) The critical flutter dynamic pressure can be increased two to three times for the cases studied (3) With embedded shape memory alloy (SMA) fibers, the critical buckling temperature of the composite panel is increased 10 to 20 times that of the panel with no SMA, and the static aerothermoelastic deformation is eliminated. (4) Flutter stability region is enlarged significantly with SMA. (5) Panel flutter suppression for integrated composite structures can be achieved effectively by using piezoelectric materials at low temperatures and SMA at high temperatures.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1994
Accession Number
ADA290201

Entities

People

  • Li-chuan Chu

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Composite Materials
  • Computational Fluid Dynamics
  • Computational Science
  • Control Systems
  • Differential Equations
  • Dynamic Pressure
  • Equations Of Motion
  • Finite Element Analysis
  • High Temperature
  • Laminates
  • Low Temperature
  • Materials Laboratories
  • Materials Testing
  • Piezoelectric Effect
  • Piezoelectric Materials
  • Stresses

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Mechanical Engineering/Mechanics of Materials.
  • Microwave Engineering.