Lunar gravity assist is a means to boost the energy and C3 of an escape trajectory. Trajectories with two lunar gravity assists are considered and analyzed. Two approaches are applied and tested for the design of missions aimed at Near-Earth asteroids. In the first method, indirect optimization of the heliocentric leg is combined to an approximate analytical treatment of the geocentric phase for short escape trajectories. In the second method, the results of pre-computed maps of escape C3 are employed for the design of longer Sun-perturbed escape sequences combined with direct optimization of the heliocentric leg. 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 Trajectories
J Astronaut Sci
The Journal of the Astronautical Sciences ; 67 , 4 ; 1374-1390
2020-12-01
17 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Optimization of Solar-Perturbed Double Lunar Swingby Escape Trajectories
British Library Conference Proceedings | 1998
|Jupiter gravity-assisted trajectories.
AIAA | 1969
|