Active Control of Forward Swept Wings with Divergence and Flutter Aeroelastic Instabilities.

Abstract

Active feedback control is applied to cantilever forward-swept wings (FSW) providing significant increases in the critical airspeeds of aeroelastic flutter and divergence. Feedback compensation improves the critical airspeed for a divergence critical FSW by 25% and improves the critical airspeed for a flutter critical FSW example by 30%. These improvements are limited by the emergence as most critical, instabilities that were only secondary without feedback. The method of analysis is linear control theory in the Laplace domain. A significant improvement is made in the Pade Approximant method for calculating damped unsteady aerodynamic forces in the Laplace domain. Keywords: Aeroelasticity, Swept forward wings, Aerodynamics, Feedback control. (Theses)

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1984
Accession Number
ADA168373

Entities

People

  • Kenneth E. Griffin

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Sensors
  • Space

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aerodynamic Control Surfaces
  • Aerodynamic Forces
  • Air Force
  • Aircraft Wings
  • Aircrafts
  • Composite Materials
  • Computer Programs
  • Control Surfaces
  • Control Systems
  • Control Systems Engineering
  • Leading Edge Flaps
  • Measurement
  • Plastic Explosives
  • Spars
  • Swept Wings
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Calculus or Mathematical Analysis
  • Robotics and Automation.