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).
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© 1970 Springer-Verlag Wien
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Sagirow, P. (1970). Orbiting Satellite Influenced by Gravity Gradient and Aerodynamic Torques. In: Stochastic Methods in the Dynamics of Satellites. International Centre for Mechanical Sciences, vol 57. Springer, Vienna. https://doi.org/10.1007/978-3-7091-2870-1_3
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DOI: https://doi.org/10.1007/978-3-7091-2870-1_3
Publisher Name: Springer, Vienna
Print ISBN: 978-3-211-81092-7
Online ISBN: 978-3-7091-2870-1
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