Trajectory design for lEO to lunar halo orbits using manifold theory and fireworks optimization

Davide Conte, Guanwei He, David B. Spencer, Robert G. Melton

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Scopus citations

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.

Original languageEnglish (US)
Title of host publicationAAS/AIAA Astrodynamics Specialist Conference, 2018
EditorsPuneet Singla, Ryan M. Weisman, Belinda G. Marchand, Brandon A. Jones
PublisherUnivelt Inc.
Pages1335-1353
Number of pages19
ISBN (Print)9780877036579
StatePublished - Jan 1 2018
EventAAS/AIAA Astrodynamics Specialist Conference, 2018 - Snowbird, United States
Duration: Aug 19 2018Aug 23 2018

Publication series

NameAdvances in the Astronautical Sciences
Volume167
ISSN (Print)0065-3438

Conference

ConferenceAAS/AIAA Astrodynamics Specialist Conference, 2018
CountryUnited States
CitySnowbird
Period8/19/188/23/18

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

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    Conte, D., He, G., Spencer, D. B., & Melton, R. G. (2018). Trajectory design for lEO to lunar halo orbits using manifold theory and fireworks optimization. In P. Singla, R. M. Weisman, B. G. Marchand, & B. A. Jones (Eds.), AAS/AIAA Astrodynamics Specialist Conference, 2018 (pp. 1335-1353). (Advances in the Astronautical Sciences; Vol. 167). Univelt Inc..