TY - GEN
T1 - Optimal two-impulse phasing for elliptical orbits
AU - Benavides, Julio Cesar
AU - Spencer, David Bradley
PY - 2008/12/1
Y1 - 2008/12/1
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
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M3 - Conference contribution
AN - SCOPUS:60349094922
SN - 9780877035442
T3 - Advances in the Astronautical Sciences
SP - 1521
EP - 1539
BT - Space Flight Mechanics 2008 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting
ER -