Fast nonresonant rotations of a spacecraft in conditionally periodic orbits in the restricted three-body problem

Details Fast nonresonant rotations of a spacecraft in conditionally periodic orbits in the restricted three-body problem Fast nonresonant rotations of a spacecraft in conditionally periodic orbits in the restricted three-body problem

Mar 1984

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1984kosis..22..171k&link_type=abstract

Kosmicheskie Issledovaniia (ISSN 0023-4206), vol. 22, Mar.-Apr. 1984, p. 171-180. In Russian.

Computer Science

Celestial Mechanics, Satellite Rotation, Spacecraft Motion, Three Body Problem, Eccentricity, Gravitational Effects, Hamiltonian Functions, Kinetic Energy, Nonresonance, Precession

Scientific paper

The fast nonresonant rotations of a satellite with respect to the center of mass in an elliptical restricted three-body problem are analyzed under the assumption that the spacecraft orbit is described by conditionally periodic functions of time. Gravity moments cause an evolution of the kinetic energy T(I1, I2) of the unperturbed relative motion of the satellite. The rotation of the satellite around the kinetic-moment vector I2 is the Euler-Poinceau motion of a certain rigid body whose main central moments of inertia depend on the initial conditions and the orbit of the satellite center of mass. For small eccentricities of the relative elliptical motion of finite bodies, the rotations are accompanied by slow displacement of I2 along the trajectories of 'split' precession. Also constructed is a qualitative pattern of the motions of this vector for plane orbits when the eccentricity of relative motion of the main bodies is arbitrary.

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