Very often in the course of the Jupiter Orbiter-Satellite Tour mission it is desired to have the spacecraft re-encounter a satellite after one complete Jovicentric orbit whose period is resonant with that of the satellite for the purposes of orbit 'cranking' or 'pumping'. This paper develops the deterministic guidance strategy necessary for the implementation of such re-encounters (360 deg transfers). Both single impulse and fuel optimal multiple impulse guidance strategies are developed on the basis of which an estimate of the total navigational fuel cost for the mission is made.
The navigation of a satellite re-encounter in a Jupiter Orbiter mission
Astrodynamics Specialist Conference ; 1975 ; Nassau, Bahamas
01.07.1975
Aufsatz (Konferenz)
Keine Angabe
Englisch
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