Formulations of the Equations of Motion of an Elastic Aircraft for Stability and Control and Flight Control Applications

Abstract

This technical memorandum presents a derivation of the equations of motion for large and small disturbance perturbations from a reference state of motion. The small perturbation equations of motion are then generalized to include the effects of atmospheric turbulence and gusts on the controls-free elastic aircraft. The resulting equations are termed the EXACT formulation. These EXACT equations may be used to evaluate the stability and performance of integrated flight control systems of the Control Configured Vehicle (CCV) type. The equations are unique in that they describe a highly damped system using motion coordinates referenced to a body fixed, 'mean', non-inertial axis.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1972
Accession Number
ADA006391

Entities

People

  • Robert C. Schwanz

Organizations

  • Flight Dynamics Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Aerodynamic Control Surfaces
  • Aerodynamic Forces
  • Aerospace Industry
  • Aircrafts
  • Airframes
  • Atmospheric Motion
  • Computational Science
  • Computers
  • Control Surfaces
  • Control Systems
  • Control Systems Engineering
  • Engineering
  • Equations Of Motion
  • Flight Control Systems
  • Flight Simulators
  • Military Aircraft
  • Vehicles

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Control Systems Engineering.