An Integrated Design Procedure for Aircraft Structure Including the Influence of Flight Control System on Aircraft Flutter

Abstract

Modern fighter aircraft are using high sophisticated power control and automatic flight control systems, which basically are designed to maneuver the airplane and to provide sufficient damping for the rigid body modes. Since the sensors are attached to the flexible structure, motions of the elastic aircraft will be measured and may influence the control system. In order to avoid instabilities it is necessary to predict the response of the aircraft with the control system and to correlate with flight test data. An analytical approach for the complete system including flight mechanics and unsteady aerodynamic forces is presented. The elastic structure is described by a set of normal modes which have been updated by results of ground resonance survey tests. Flutter calculations in open and closed loop on different flight conditions as well as incidence variations are demonstrated as common flutter plots. For the flutter analysis a set of notch filter is required, which should be determined in an integrated design step.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
May 01, 2000
Accession Number
ADP010480

Entities

People

  • John V. Becker
  • W. Luber

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Aircrafts
  • Airframes
  • Control Surfaces
  • Control Systems
  • Control Systems Engineering
  • Damping
  • Differential Equations
  • Equations
  • Fighter Aircraft
  • Flight Control Systems
  • Fluid Dynamics
  • Frequency
  • Frequency Shift
  • Inertial Measurement Units
  • Mach Number
  • Military Aircraft

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Aerospace Test and Evaluation