Third order Cartesian relative motion perturbation solutions for slightly eccentric chief orbits

Eric A. Butcher, T. Alan Lovell, Andrew Harris

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

6 Scopus citations

Abstract

A perturbation method is used to obtain third order solutions for spacecraft relative motion in Cartesian coordinates for the case of a slightly eccentric chief orbit and a large chief/deputy separation distance. Both the chief eccentricity and the normalized separation are considered to be of order ϵ. The solution obtained includes as subsets both second order solutions for circular chief orbits previously obtained by perturbation and quadratic Volterra theory as well as a linear solution to third order in the chief eccentricity. Simulations confirm the improved accuracy of the third order solution.

Original languageEnglish (US)
Title of host publicationSpaceflight Mechanics 2016
EditorsMartin T. Ozimek, Renato Zanetti, Angela L. Bowes, Ryan P. Russell, Martin T. Ozimek
PublisherUnivelt Inc.
Pages3435-3454
Number of pages20
ISBN (Print)9780877036333
StatePublished - 2016
Event26th AAS/AIAA Space Flight Mechanics Meeting, 2016 - Napa, United States
Duration: Feb 14 2016Feb 18 2016

Publication series

NameAdvances in the Astronautical Sciences
Volume158
ISSN (Print)0065-3438

Other

Other26th AAS/AIAA Space Flight Mechanics Meeting, 2016
CountryUnited States
CityNapa
Period2/14/162/18/16

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

Fingerprint Dive into the research topics of 'Third order Cartesian relative motion perturbation solutions for slightly eccentric chief orbits'. Together they form a unique fingerprint.

Cite this