ΔV-optimal rendezvous maneuvers in CIS-lunar Halo orbits around EML2

Davide Conte, David B. Spencer

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

1 Scopus citations

Abstract

This paper presents solution techniques for finding Δv-optimal maneuvers to rendezvous with a target spacecraft in cis-lunar halo orbits around the Earth-Moon Lagrange point 2 (EML2). This family of orbits was chosen due to the rising interest in cis-lunar space for human and robotic exploration. The dynamics and the stability of relative motion in the Circular Restricted Three-Body Problem (CR3BP) are analyzed using Floquet theory. In order to determine optimal maneuvers that the chaser spacecraft needs to accomplish to rendezvous with the target vehicle, simplified models of the relative motion in the CR3BP are explored and utilized, and compared to the full non-linear CR3BP model.

Original languageEnglish (US)
Title of host publicationASTRODYNAMICS 2017
EditorsJohn H. Seago, Nathan J. Strange, Daniel J. Scheeres, Jeffrey S. Parker
PublisherUnivelt Inc.
Pages3151-3166
Number of pages16
ISBN (Print)9780877036456
StatePublished - Jan 1 2018
EventAAS/AIAA Astrodynamics Specialist Conference, 2017 - Stevenson, United States
Duration: Aug 20 2017Aug 24 2017

Publication series

NameAdvances in the Astronautical Sciences
Volume162
ISSN (Print)0065-3438

Other

OtherAAS/AIAA Astrodynamics Specialist Conference, 2017
Country/TerritoryUnited States
CityStevenson
Period8/20/178/24/17

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

Fingerprint

Dive into the research topics of 'ΔV-optimal rendezvous maneuvers in CIS-lunar Halo orbits around EML2'. Together they form a unique fingerprint.

Cite this