Satellite Formation Flying Maneuver Control

Abstract

A problem of a formation flying satellites maneuver control is presented. Among the most important criteria for satellite formation flying control system are active period maximization, precision of the configuration, secure motion (without collisions of satellites). Several methods for group configuration are presented: periodic impulse correction of each flying satellite position formation ("continuous order"); method of a satellite positioning on non-coplanar orbits ("variable order"). Other methods include combinations of methods mentioned above. Recommendations for their application are given. Two ideologies for satellite formation flying can be presented. The first one includes independent maintenance of each satellite a priori specified orbital parameters. The second one implies specialization of satellites: leaders provide orbital parameters for following satellites. Theory of the optimal control of multiobject multi-criteria systems is supposed to be rational for the maneuver control of a group of satellites. Based on this theory algorithm consists of the following phases. On the first phase current intergroup orbiting parameters are measured. On the second phase direction, capacity and duration of the control impulse are estimated based on the forecast of satellite orbital parameters and optimization criteria. On the last phase, the thrusters are used to issue a control impulse. In the presented paper such algorithm is adopted for a task of a formation flying control based on criterion, which consists of two parts. The first part is a configuration deformation minimization. The second one is a distance maximization near orbital node. Algorithm consists of three phases. On the first phase current intergroup orbiting parameters are measured. On the second phase orbital parameters in the "nodе" points are forecasted. On the third phase control parameters are estimated. A model example is given, computational complexity for different number of satellites is determined. Recommendations for practical application of the algorithm are given.