@inproceedings{56fc9c7600514b5e91734789c93066e6,
title = "Third order Cartesian relative motion perturbation solutions for slightly eccentric chief orbits",
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.",
author = "Butcher, {Eric A.} and Lovell, {T. Alan} and Andrew Harris",
note = "Funding Information: EB was a 2015 Summer Faculty Fellow at the Air Force Research Laboratories, Space Vehicle Directorate, and AH was a Space Scholar at AFRL during the same period. Additional financial support from AFRL under contract FA9453-14-1-1350 is gratefully acknowledged.; 26th AAS/AIAA Space Flight Mechanics Meeting, 2016 ; Conference date: 14-02-2016 Through 18-02-2016",
year = "2016",
language = "English (US)",
isbn = "9780877036333",
series = "Advances in the Astronautical Sciences",
publisher = "Univelt Inc.",
pages = "3435--3454",
editor = "Ozimek, {Martin T.} and Renato Zanetti and Bowes, {Angela L.} and Russell, {Ryan P.}",
booktitle = "Spaceflight Mechanics 2016",
}