Optimization of transfers to Neptune
by
Antonio Fernando Bertachini de A. Prado
National Institute for Space Research - INPE - Brazil
Coauthors: Carlos Renato Huaura Solórzano, Alexander A. Sukhanov

The gravity assist is a proven technique in interplanetary exploration, as exemplified by the missions Voyager, Galileo, Cassini etc. NASA’s Solar System Exploration theme listed a Neptune mission as one of its top priorities for the mid-term (2008-2013). Here a mission to Neptune for the mid-term (2008-2018) is proposed. A direct transfer to Neptune is considered and also Venus, Earth, Jupiter, Saturn gravity assists are used for the trip to Neptune. Several mission options are analyzed, such as: Earth – Neptune (EN), Earth – Jupiter – Neptune (EJN), Earth – Saturn – Neptune (ESN), Earth – Jupiter – Saturn – Neptune (EJSN), Earth – Venus – Earth – Jupiter – Saturn – Neptune (EVEJSN). All the transfers are optimized in terms of minimum total V including the launch V in LEO and midcourse Vs. The goal of the study is to compare the mission options in order to find a good compromise between the V and time of flight to Neptune. The design of the trajectories is based on the patched conics approach and accomplished using several optimization techniques, they are used to undertake feasibility studies, and to determine trajectories characteristics as the sequence of flyby bodies.

Date received: February 25, 2004

Copyright © 2004 by the author(s). The author(s) of this document and the organizers of the conference have granted their consent to include this abstract in Atlas Conferences Inc. Document # cakt-70.