The stationkeeping of symmetric Walker constellations is analyzed in this chapter by considering the perturbations arising from a high order and degree Earth gravity field, and the solar radiation pressure. These perturbations act differently on each group of spacecraft flying in a given orbital plane, causing a differential drift effect that would disrupt the initial symmetry of the constellation. The analysis is based on the consideration of a fictitious set of rotating reference frames that move with the spacecraft in the mean sense, but drift at a rate equal to the average drift rate experienced by all the vehicles over an extended period. The frames are also allowed to experience the J2-precession, such that each vehicle is allowed to drift in 3D relative to its frame. A two-impulse rendezvous maneuver is then constructed to bring each vehicle to the center of its frame as soon as a given tolerance deadband is about to be violated. This chapter illustrates the computations associated with the stationkeeping of a generic Walker constellation, by maneuvering each leading spacecraft within an orbit plane, and calculating the associated velocity changes required for controlling the in-plane motions in an exacting sense, at least for the first series of maneuvers. The analysis can be easily extended to lower flying constellations, which experience additional perturbations due to drag.
The Analysis and Implementation of In-Plane Stationkeeping of Continuously Perturbed Walker Constellations
Space Technology Library
2021-04-13
28 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
British Library Conference Proceedings | 2009
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