Airplane Basic Equations of Motion and Open-Loop Dynamics

  • I. A. Raptis
  • K. P. Valavanis
Part of the Intelligent Systems, Control and Automation: Science and Engineering book series (ISCA, volume 33)


The goal of this Chapter is to present fundamental background information related to the derivation of the basic equations of motion of a traditional airplane, explain how the airplane’s position and orientation are determined with respect to a reference frame (Earth-fixed inertia reference frame), derive the aerodynamic forces that act on the airplane, define the corresponding control angles, and conclude with derivation of the open-loop dynamics. The material included in this Chapter is a very concise version of what may be found in any related textbook, and follows the same notation and derivation approach described in the references.


Reference Frame Aerodynamic Force Sideslip Angle Inertial Reference Frame Stability Derivative 
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    Anderson J. D., Introduction to Flight, McGraw-Hill, 1989.Google Scholar
  2. 2.
    Babister A. W., Aircraft Dynamic Stability and Response, Pergamon Press, 1980.Google Scholar
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    Blakelock J. H., Automatic Control of Aircraft and Missiles, John Wiley & Sons, 1991.Google Scholar
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    Etkin B., Dynamics of Flight: Stability and Control, John Wiley & Sons, 1959.Google Scholar
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    McCormick B. W., Aerodynamics Aeronautics and Flight Mechanics, John Willey & Sons, 1995.Google Scholar
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    Perkins C. D., Hage R. E., Airplane Performance Stability and Control, John Wiley & Sons, 1965.Google Scholar
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    Seckel E., Stability and Control of Airplanes and Helicopters, Academic Press, 1964.Google Scholar
  8. 8.
    Williams J. H., Fundamentals of Applied Dynamics, John Wiley & Sons, 1996.Google Scholar

Copyright information

© Springer. Printed in the Netherlands 2007

Authors and Affiliations

  • I. A. Raptis
    • 1
  • K. P. Valavanis
    • 1
  1. 1.Department of Computer Science and Engineering University of South FloridaUnmanned Systems LaboratoryTampaUSA

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