Pareto-Optimal Parametric Programs for Spacecraft Relative Motion Control in Near-Circular Orbits

The problem of designing a set of nominal Pareto-optimal control programs for the relative motion of a spacecraft maneuvering in circular orbits relative to a passive target is considered. Motion is considered in an orbital cylindrical reference frame in variables characterizing secular and periodic motion in a dimensionless form that is invariant with respect to the magnitude of acceleration from the thrust of a maneuvering spacecraft and the height of the reference orbit. On the basis of analytical studies, areas of boundary conditions have been constructed that allow the use of simpler relative motion control programs with two active areas oriented in the transversal direction. The solution of a two-criterion parametric problem for the criteria is obtained: the motor operating time of the engine, and the total duration of the maneuver. The application of the Pareto optimality principle made it possible to simplify the numerical procedure for constructing the desired set of nonimproved solutions to the problem from the available sample satisfying the boundary conditions of the transfer.