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Orbiting Satellite Influenced by Gravity Gradient and Aerodynamic Torques

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

Abstract

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).

Keywords

Circular Orbit Stability Domain Gravity Gradient Pitch Motion External Torque 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer-Verlag Wien 1970

Authors and Affiliations

  • Peter Sagirow
    • 1
  1. 1.Stuttgart UniversityGermany

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