A fast tour design method using non-tangent v-infinity leveraging transfer

Details A fast tour design method using non-tangent v-infinity leveraging transfer A fast tour design method using non-tangent v-infinity leveraging transfer

Oct 2010

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2010cemda.108..165c&link_type=abstract

Celestial Mechanics and Dynamical Astronomy, Volume 108, Issue 2, pp.165-186

Astronomy and Astrophysics

Astronomy

N-Body, Resonance, Enceladus Orbiter, Vilt, Gravity Assists, Artificial Satellites

Scientific paper

The announced missions to the Saturn and Jupiter systems renewed the space community interest in simple design methods for gravity assist tours at planetary 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. Using 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 Δ v change of <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 Δ 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 Δ v constraints.

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