Spherical coordinate perturbation solutions to relative motion equations: Application to double transformation spherical solution

Eric Butcher, T. Alan Lovell

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

2 Scopus citations

Abstract

Perturbation solutions are obtained in spherical coordinates for the spacecraft relative motion problem in the case of a slightly eccentric chief orbit. The use of spherical coordinates eliminates many of the secular terms in the Cartesian coordinate solution and extends the range of validity of these solutions to larger intrack separations. Both the chief eccentricity and the normalized separation are treated as order ϵ. Finally, the third order solution is used in the "double transformation" to improve the accuracy of the "approximate double transformation" Cartesian solution and as an alternative method to obtain the proposed third order spherical solution.

Original languageEnglish (US)
Title of host publicationSpaceflight Mechanics 2016
PublisherUnivelt Inc.
Pages3455-3474
Number of pages20
Volume158
ISBN (Print)9780877036333
StatePublished - 2016
Event26th AAS/AIAA Space Flight Mechanics Meeting, 2016 - Napa, United States
Duration: Feb 14 2016Feb 18 2016

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

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  • Cite this

    Butcher, E., & Lovell, T. A. (2016). Spherical coordinate perturbation solutions to relative motion equations: Application to double transformation spherical solution. In Spaceflight Mechanics 2016 (Vol. 158, pp. 3455-3474). Univelt Inc..