Satellite with periodical mass redistribution: relative equilibria and their stability
The dynamics of a spacecraft with variable mass distribution is considered, assuming a central Newtonian gravitational field. The equations of spatial attitude motion are derived within the framework of the so-called satellite approximation and examined via a Hamiltonian approach. The centre of mass of the satellite multibody system moves along an elliptic orbit of arbitrary eccentricity. For a prescribed attitude motion, control via the mass redistribution is determined. Various classes of relative equilibria are detected, and the respective control is obtained. The stability of the spacecraft spatial attitude motions is examined in detail.
KeywordsSpacecraft attitude control Attitude dynamics in elliptic orbit Variable mass distribution Spacecraft oscillations Conditions of stability
The paper has been prepared with help from project EMaDeS (Centro-01-0145-FEDER-000017), the Portuguese Foundation for Science and Technology via the Centre for Mechanical and Aerospace Science and Technologies, C-MAST (POCI-01-0145-FEDER-007718) for the second author, RFBR Project No. 16-01-00625a for the first author, and RSF Project No. 14-21-00068 for the third author at MAI.
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Conflict of interest
The authors certify that they have no conflict of interest to declare.
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