Effect analysis and compensation for orbit perturbation of spacecraft using momentum management control

This paper uses inertial momentum management control method for long-term on-orbit working stability of large spacecraft which only has small difference in three-axis main inertia. To avoid the accumulation of gravity gradient torque, it should be guaranteed that one inertia axis of spacecraft is strictly perpendicular to its orbital plane. Then, an inertial reference coordinate system for momentum management is established. It is observed that the drift of ascending node right ascension and along-track angle of orbit caused by orbit perturbation has an approximate linear relation to time. This leads to a linear increase of the momentum and causes divergences of attitude and angular momentum. We render analysis to the problem and augment the long-period orbit factors in state equation on the basis of internal model principle in order to compensate the perturbation. Finally, semi-physical simulations are setup to validate the approach. It shows that the compensation method is feasible and long-term stability of attitude and momentum is achieved.