Terminal control of the trajectory and rotational motion of an active spacecraft during a rendezvous with a passive spacecraft

In this work, the problem of a spacecraft’s rendezvous is considered in the radial coordinate system, taking into consideration the effect of the difference gravitational acceleration, using a control algorithm with the prediction model based on the minimization of the generalized work functional. The analytical formulas have been derived to compute the control actions when the motion of the center of mass and the motion about the center of mass, when solving the parametric optimization problem, are considered in a unified terminal formulation. The analytical solution is based on a special prediction model that has an analytical solution in the advanced modeling of the rendezvous process. The results of modeling a spacecraft’s rendezvous are presented.