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Design of a Multi-Moon Orbiter

Ross, S. D. and Koon, W. S. and Lo, M. W. and Marsden, J. E. (2003) Design of a Multi-Moon Orbiter. In: Spaceflight Mechanics 2003. Advances in the Astronautical Sciences. No.114. American Astronautical Society , San Diego, pp. 669-683. ISBN 978-0-87703-504-6.

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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.

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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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Caltech President’s FundUNSPECIFIED
Series Name:Advances in the Astronautical Sciences
Issue or Number:114
Record Number:CaltechAUTHORS:20101007-131136558
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:20340
Deposited By: Tony Diaz
Deposited On:22 Nov 2010 23:46
Last Modified:03 Oct 2019 02:08

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