Perturbation in orbital elements of a high elliptical orbit of satellite constellations

Osama Mostafa, Koki Fujita, Toshiya Hanada

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

Abstract

This work aim to study the effects of various perturbations on the motion of satellites constellation in high elliptical inclined orbit in order to make continuous coverage. A computational model developed at Space Systems Dynamics Laboratory, Kyushu University to study the effect of these perturbations on Molniya and Tundra satellite constellations for various periods one, five and 10 years. The equations of motion under effect of these perturbations forces are solved numerically using Gaussian equations. The results show that the satellites constellation in Molniya orbit have stability under effect of gravity of third body more than Tundra orbit in order to make a continuous coverage.

Original languageEnglish
Title of host publicationSpaceflight Mechanics 2017
EditorsJon A. Sims, Frederick A. Leve, Jay W. McMahon, Yanping Guo
PublisherUnivelt Inc.
Pages1733-1745
Number of pages13
ISBN (Print)9780877036371
Publication statusPublished - Jan 1 2017
Externally publishedYes
Event27th AAS/AIAA Space Flight Mechanics Meeting, 2017 - San Antonio, United States
Duration: Feb 5 2017Feb 9 2017

Publication series

NameAdvances in the Astronautical Sciences
Volume160
ISSN (Print)0065-3438

Other

Other27th AAS/AIAA Space Flight Mechanics Meeting, 2017
CountryUnited States
CitySan Antonio
Period2/5/172/9/17

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

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    Mostafa, O., Fujita, K., & Hanada, T. (2017). Perturbation in orbital elements of a high elliptical orbit of satellite constellations. In J. A. Sims, F. A. Leve, J. W. McMahon, & Y. Guo (Eds.), Spaceflight Mechanics 2017 (pp. 1733-1745). (Advances in the Astronautical Sciences; Vol. 160). Univelt Inc..