### 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 language | English (US) |
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Title of host publication | Space Flight Mechanics 2008 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting |

Pages | 1521-1539 |

Number of pages | 19 |

Volume | 130 PART 2 |

State | Published - 2008 |

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### All Science Journal Classification (ASJC) codes

- Aerospace Engineering
- Space and Planetary Science

### Cite this

*Space Flight Mechanics 2008 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting*(Vol. 130 PART 2, pp. 1521-1539)

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*Space Flight Mechanics 2008 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting.*vol. 130 PART 2, pp. 1521-1539.

**Optimal two-impulse phasing for elliptical orbits.** / Benavides, Julio Cesar; Spencer, David Bradley.

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

TY - GEN

T1 - Optimal two-impulse phasing for elliptical orbits

AU - Benavides, Julio Cesar

AU - Spencer, David Bradley

PY - 2008

Y1 - 2008

N2 - 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.

AB - 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.

UR - http://www.scopus.com/inward/record.url?scp=60349094922&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=60349094922&partnerID=8YFLogxK

M3 - Conference contribution

SN - 9780877035442

VL - 130 PART 2

SP - 1521

EP - 1539

BT - Space Flight Mechanics 2008 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting

ER -