Abstract
A method of general perturbations, based on the use of Lie series to generate approximate canonical transformations, is applied to study the long-term effects of gravity-gradient torque and orbital evolution on the rotational motion of a triaxial, rigid satellite. The center of mass of the satellite is constrained to move in an elliptic orbit about an attracting point mass. The orbit, which has a constant inclination, is constrained to precess and spin with constant rates. The method of general perturbations is used to obtain the Hamiltonian for the nonresonant secular and long-period rotational motion of the satellite to second order in n/ω0, where n is the orbital mean motion of the center of mass and ω0 is a reference value of the magnitude of the satellite’s rotational angular velocity. The differential equations derivable from the transformed Hamiltonian are integrable and the solution for the long-term motion may be expressed in terms of Jacobian elliptic functions and elliptic integrals. Geometrical aspects of the long-term rotational motion are discussed and a comparison of theoretical results with observations is made.
This paper is a slightly modified version of a previously published paper (Cochran, 1972) by the author.
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© 1973 D. Reidel Publishing Company, Dordrecht-Holland
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Cochran, J.E. (1973). Long-Term Motion in a Restricted Problem of Rotational Motion. In: Tapley, B.D., Szebehely, V. (eds) Recent Advances in Dynamical Astronomy. Astrophysics and Space Science Library, vol 39. Springer, Dordrecht. https://doi.org/10.1007/978-94-010-2611-6_40
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DOI: https://doi.org/10.1007/978-94-010-2611-6_40
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