Orbiting Satellite Influenced by Gravity Gradient and Aerodynamic Torques

  • Peter Sagirow
Part of the International Centre for Mechanical Sciences book series (CISM, volume 57)


Let x, y, z denote the principal axes of inertia and A, B, C the corresponding principal moments of inertia of a rigid satellite in circular orbit (Fig. 3.1).


Circular Orbit Stability Domain Gravity Gradient Pitch Motion External Torque 
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Copyright information

© Springer-Verlag Wien 1970

Authors and Affiliations

  • Peter Sagirow
    • 1
  1. 1.Stuttgart UniversityGermany

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