Abstract
This work aims at finding an analytic solution corresponding to the attitude evolution in space of a satellite submitted to disturbing torques. This paper presents a basic frame applicable to any perturbed rotation satellite, and a method of resolution leading to a formal solution which is given here to the first order. Thus, the main problem is the slow rotation of a body with three unequal axes of inertia, essentially submitted to a dominant solar radiation pressure torque, with the axis pointing far away from a position of equilibrium. The comparison of the results with a numerical integration based upon a HIPPARCOS model is convincing.
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Bois, E. First-order theory of satellite attitude motion application to HIPPARCOS. Celestial Mechanics 39, 309–327 (1986). https://doi.org/10.1007/BF01230479
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DOI: https://doi.org/10.1007/BF01230479