An iterative method is described for determining the impulses and the times of the impulses which are needed to effect a prescribed orbit change for the case where the propulsion system orientation is given. The method makes use of an existing computer program and is demonstrated by two examples.
Stationkeeping of Geostationary Satellites Zur Positionshaltung Geostationaerer Satelliten
1976
20 pages
Report
Keine Angabe
Englisch
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