@inproceedings{oai:jaxa.repo.nii.ac.jp:00007269,
 author = {Campagnola, Stefano and Strange, Nathan and Russel, Ryan},
 book = {アストロダイナミクスシンポジウム講演後刷り集, The 20th Workshop on JAXA Astrodynamics and Flight Mechanics},
 month = {Mar},
 note = {第20回アストロダイナミクスシンポジウム (2010年7月26-27日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, The 20th Workshop on JAXA Astrodynamics and Flight Mechanics 2010 (July 26-27, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, The announced missions to the Saturn and Jupiter systems renewed the space community interest in simple design methods for gravity assist tours at plnetary moons. A key element in such trajectories are the V-Infinity Leveraging Transfers (VILT) which link simple impulsive maneuvers with two consecutive gravity assists at the same moon. VILTs typically include a tangent impulsive maneuver close to an apse location, yielding to a desired change in the excess velocity relative to the moon. In this paper we study the VILT solution space and derive a linear approximation which greatly simplifies the computation of the transfers, and is amenable to broad global searches. Usilng this approximation, Tisserand graphs, and heuristic optimization procedure we introduce a fast design method for multiple-VILT tours. We use this method to design a trajectory from a highly eccentric orbit around Saturn to a 200 km science orbit at Enceladus. The trajectory is then recomputed removing the linear approximation, showing a Delta v change of less than 4%. The trajectory is 2.7 years long and comprises 52 gravity assists at Titan, Rhea, Dione, Tethys, and Enceladus, and several deterministic maneuvers. Total Delta v is only 445 m/s, including the Enceladus orbit insertion, almost 10 times better then the 3.9 km/s of the Enceladus orbit insertion from the Titan-Enceladus Hohmann transfer. The new method and demonstrated results enable a new class of missions that tour and ultimately orbit small mass moons. Such missions were previously considered infeasible due to flight time and Delta v constraints., 資料番号: AA0065115022},
 pages = {120--135},
 publisher = {宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS), Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)},
 title = {Trajectory design for an Enceladus orbiter using non-tangent v-infinity leveraging transfers},
 volume = {20},
 year = {2011}
}