@inproceedings{e50b66bcd263474b8d0abc8c031079f8,
title = "Low-thrust trajectory optimization with gravity assist in a full ephemeris model",
abstract = "Significant propellant mass saving can be obtained with the use of complex multiple intermediate flyby maneuvers for electric propulsion system. A two-body model can no longer satisfy the accuracy requirements in the practical engineer. This paper presents a full ephemeris model which introduces the third body's gravity, especially the GA planet's gravity, in a dynamic equation. At the same time, this paper built a set of position and velocity constraint at the perigee time relative to GA planet to guide the spacecraft fly through the sphere of influence of GA planet to get GA.",
author = "Xingshan Cai and Junfeng Li and Xiangyuan Zeng",
year = "2014",
language = "English",
series = "Advances in the Astronautical Sciences",
publisher = "Univelt Inc.",
pages = "1617--1626",
editor = "Mackison, \{Donald L.\} and Ossama Abdelkhalik and Wilson, \{Roby S.\} and Renato Zanetti",
booktitle = "Advances In The Astronautical Sciences",
address = "United States",
note = "24th AAS/AIAA Space Flight Mechanics Meeting, 2014 ; Conference date: 26-01-2014 Through 30-01-2014",
}