Other
Scientific paper
Dec 2008
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2008agufm.p13d..08s&link_type=abstract
American Geophysical Union, Fall Meeting 2008, abstract #P13D-08
Other
5499 General Or Miscellaneous, 6281 Titan, 6299 General Or Miscellaneous
Scientific paper
In 2007 NASA's Science Mission Directorate (SMD), in efforts to start an outer solar system flagship mission in the near future, commissioned studies of mission concepts for four high-priority outer solar system destinations: Europa, the Jovian system, Titan, and Enceladus. Follow-on studies begun in 2008, jointly conducted with ESA and incorporating the selection of the LaPlace and TandEM Cosmic Vision study proposals, combine the Europa and Jupiter system mission concepts into a single mission, and the Titan and Enceladus mission concepts, along with related Saturn system science, into a single mission. The 2007 studies of Titan and Enceladus missions allowed each mission concept to focus on a single destination. The 2008 study must address both Titan and Enceladus exploration with a single mission. This raises significant challenges to mission designers but also presents opportunities. Challenges stem from Titan's and Enceladus' very different locations within Saturn's gravity well, and from the different natures of the two satellites. With current or even envisioned propulsion systems, delta-V requirements prohibit a spacecraft that inserts into orbit at one from subsequently escaping and inserting into orbit at the other. Missions that perform interlaced flybys of the two bodies are limited to relatively high flyby speeds. "Pumping down" flyby speeds at one of them terminates, at least temporarily, flybys of the other, and for Enceladus requires significant time and delta-V. But despite their obvious differences, such as Titan's thick and Enceladus' almost non-existent atmospheres, a science payload designed for Titan can perform excellent science at Enceladus as well. It might be possible to have a single mission target separate orbiters to the two destinations, but this architecture would likely require a launch vehicle significantly larger than is required for a mission that orbits only one body. This paper will discuss these challenges and opportunities.
Spilker Thomas Richard
Strange Nathan J.
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