Orbiting Satellite Influenced by Gravity Gradient and Aerodynamic Torques
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).
KeywordsCircular 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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© Springer-Verlag Wien 1970