Computer Science
Scientific paper
Sep 1972
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1972cemec...6..127c&link_type=abstract
Celestial Mechanics, Volume 6, Issue 2, pp.127-150
Computer Science
8
Scientific paper
A method of general perturbations, based on the use of Lie series to generate approximate canonical transformations, is applied to study the effects of gravity-gradient torque 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 free to precess and spin. 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 inn/ω0, wheren is the orbital mean motion of the center of mass andω0 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.
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