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Published 2003 | Accepted Version
Book Section - Chapter Open

Design of a Multi-Moon Orbiter


The Multi-Moon Orbiter concept is introduced, wherein a single spacecraft orbits several moons of Jupiter, allowing long duration observations. The ΔV requirements for this mission can be low if ballistic captures and resonant gravity assists by Jupiter's moons are used. For example, using only 22 m/s, a spacecraft initially injected in a jovian orbit can be directed into a capture orbit around Europa, orbiting both Callisto and Ganymede enroute. The time of flight for this preliminary trajectory is four years, but may be reduced by striking a compromise between fuel and time optimization during the inter-moon transfer phases.

Additional Information

© 2003 Published for the American Astronautical Society by Univelt. This work is supported in part by the Caltech's President's Fund. This work was carried out in part at the Jet Propulsion Laboratory and California Institute of Technology under a contract with the National Aeronautics and Space Administration.

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Accepted Version - RoKoLoMa2003.pdf


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August 19, 2023
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