Linearized relative orbital motion model about an oblate body without averaging

Ethan R. Burnett, Eric Butcher, Andrew J. Sinclair, T. Alan Lovell

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

1 Scopus citations

Abstract

A new linearized differential equation model and solution for spacecraft relative motion about an oblate body is obtained without averaging the perturbing acceleration, and presented for the case of near-zero chief orbit eccentricity. The model is stand-alone and does not require integration of the chief orbit, while the time-explicit solution depends only on initial chief orbital elements, time since epoch and node crossing, and the deputy’s initial conditions in the chief Hill frame. The resulting model outperforms previous models obtained via averaging, and has a similar error to the GA-STM for zero initial chief orbit eccentricity.

Original languageEnglish (US)
Title of host publicationAAS/AIAA Astrodynamics Specialist Conference, 2018
EditorsRyan M. Weisman, Puneet Singla, Belinda G. Marchand, Brandon A. Jones
PublisherUnivelt Inc.
Pages691-710
Number of pages20
ISBN (Print)9780877036579
StatePublished - Jan 1 2018
EventAAS/AIAA Astrodynamics Specialist Conference, 2018 - Montreal, Canada
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
CountryCanada
CityMontreal
Period8/19/188/23/18

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

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