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How to maneuver around in eccentricity vector space

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dc.contributor.author Sweetser, Theodore H.
dc.date.accessioned 2015-04-22T17:19:10Z
dc.date.available 2015-04-22T17:19:10Z
dc.date.issued 2010-08-02
dc.identifier.citation AIAA Guidance, Navigation, and Control Conference 2010, Toronto, Ontario, August 2-5, 2010 en_US
dc.identifier.clearanceno 10-2624
dc.identifier.uri http://hdl.handle.net/2014/45144
dc.description.abstract The GRAIL mission to the Moon will be the first time that two separate robotic orbiters will be placed into formation in orbit around a body other than Earth. The need to design an efficient series of maneuvers to shape the orbits and phasing of the two orbiters after arrival presents a significant challenge to mission designers. This paper presents a simple geometric method for relating in-plane impulsive maneuvers to changes in the eccentricity vector, which determines the shape and orientation of an orbit in the orbit plane. Examples then show how such maneuvers can accommodate desired changes to other orbital elements such as period, incination, and longitude of the ascending node. en_US
dc.description.sponsorship NASA/JPL en_US
dc.language.iso en_US en_US
dc.publisher Pasadena, CA : Jet Propulsion Laboratory, National Aeronautics and Space Administration, 2010 en_US
dc.subject orbit maneuvers en_US
dc.subject orbit maintenance en_US
dc.subject epicycles en_US
dc.subject equant en_US
dc.title How to maneuver around in eccentricity vector space en_US
dc.type Preprint en_US


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