Archivio Istituzionale della RicercaLunar gravity assist is a means to boost the energy and C3 of an escape maneuver. Two approaches are applied and tested for the design of trajectories aimed at Near-Earth asteroids. Maneuvers with two lunar gravity assists are considered and analyzed. Indirect optimization of the heliocentric leg is combined to an approximate analytical treatment of the geocentric phase for short escape maneuvers. The results of pre-computed maps of escape C3 are used for the design of longer sun-perturbed escape sequences. Features are compared and suggestions about a combined use of the approaches are presented. The techniques are efficiently applied to the design of a mission to a near-Earth asteroid.
DESIGN OF LUNAR-GRAVITY-ASSISTED ESCAPE MANEUVERS / Casalino, Lorenzo; Lantoine, Gregory. - 162:(2018), pp. 663-676. (Intervento presentato al convegno AAS/AIAA Astrodynamics Specialist Conference tenutosi a Stevenson, WA, USA nel August 20-24, 2017).
DESIGN OF LUNAR-GRAVITY-ASSISTED ESCAPE MANEUVERS
CASALINO, LORENZO;
2018
Abstract
Lunar gravity assist is a means to boost the energy and C3 of an escape maneuver. Two approaches are applied and tested for the design of trajectories aimed at Near-Earth asteroids. Maneuvers with two lunar gravity assists are considered and analyzed. Indirect optimization of the heliocentric leg is combined to an approximate analytical treatment of the geocentric phase for short escape maneuvers. The results of pre-computed maps of escape C3 are used for the design of longer sun-perturbed escape sequences. Features are compared and suggestions about a combined use of the approaches are presented. The techniques are efficiently applied to the design of a mission to a near-Earth asteroid.
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https://hdl.handle.net/11583/2707348
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