Optimal two-impulse phasing for elliptical orbits

Julio Cesar Benavides, David Bradley Spencer

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

Abstract

This study analyzes optimal mission velocity change magnitudes required to perform a co-orbital phasing maneuver within an elliptical orbit. Analytical velocity change expressions are derived in terms of the chase vehicle's initial classical orbital elements. The results demonstrate that for sufficiently large times of flight, the minimum velocity change converges to a value that is a function of eccentricity and initial chase satellite true anomaly regardless of the initial phase angle. The equations derived in this investigation are used to analyze phasing maneuvers for geosynchronous, low eccentricity, and Molniya orbits.

Original languageEnglish (US)
Title of host publicationSpace Flight Mechanics 2008 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting
Pages1521-1539
Number of pages19
StatePublished - Dec 1 2008

Publication series

NameAdvances in the Astronautical Sciences
Volume130 PART 2
ISSN (Print)0065-3438

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

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  • Cite this

    Benavides, J. C., & Spencer, D. B. (2008). Optimal two-impulse phasing for elliptical orbits. In Space Flight Mechanics 2008 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting (pp. 1521-1539). (Advances in the Astronautical Sciences; Vol. 130 PART 2).