@inproceedings{c28f96bdbbba485da93e4ec11ed325d7,
title = "Trajectory design for lEO to lunar halo orbits using manifold theory and fireworks optimization",
abstract = "In this paper a simple and efficient way of computing impulsive maneuver transfers from a user-defined Low Earth Orbit (LEO) to a desired lunar halo orbit around the Earth-Moon Lagrange point 2 (EML2) utilizing a heuristic optimization method is presented. The dynamical framework utilized is the Circular Restricted Three-Body Problem (CR3BP). Sample LEO to lunar halo trajectories along with their required 'V costs and Time-of-Flight (TOF) are provided and compared to known numerical techniques to assert the validity of the proposed method. The obtained results are close in both 'V and TOF to what the existing literature reports.",
author = "Davide Conte and Guanwei He and Spencer, {David B.} and Melton, {Robert G.}",
note = "Publisher Copyright: {\textcopyright} 2018 Univelt Inc. All rights reserved.; AAS/AIAA Astrodynamics Specialist Conference, 2018 ; Conference date: 19-08-2018 Through 23-08-2018",
year = "2018",
language = "English (US)",
isbn = "9780877036579",
series = "Advances in the Astronautical Sciences",
publisher = "Univelt Inc.",
pages = "1335--1353",
editor = "Puneet Singla and Weisman, {Ryan M.} and Marchand, {Belinda G.} and Jones, {Brandon A.}",
booktitle = "AAS/AIAA Astrodynamics Specialist Conference, 2018",
address = "United States",
}