Article ID | Journal | Published Year | Pages | File Type |
---|---|---|---|---|
1715995 | Acta Astronautica | 2010 | 10 Pages |
Abstract
Application of electric propulsion system (EPS) requires spacecraft (SC) equipping with large solar panels (SP) for the power supply to electric propulsions. This makes the problem of EPS-equipped SC control at the insertion stage more difficult to solve than in the case of SC equipped with chemical engines, because in addition to the SC attitude control associated with the mission there appears necessity in keeping SP orientation to Sun that is necessary for generation of electric power sufficient for the operation of service systems, purpose-oriented equipment, and EPS. The theoretical study of the control problem is the most interesting for a non-coplanar transfer from high elliptic orbit (HEO) to geostationary orbit (GSO).
Related Topics
Physical Sciences and Engineering
Engineering
Aerospace Engineering
Authors
V.A. Obukhov, A.I. Pokryshkin, G.A. Popov, N.V. Yashina,