Fuel-/Time-Optimal Relative Trajectories for a Satellite near a Perturbed, Elliptical Orbit

The problem of fuel/time trajectory optimization is considered for a spacecraft moving relative to another in a perturbed, elliptical orbit. The relative motion model for the deputy satellite with respect to the chief is assumed to be well-approximated using the Gim–Alfriend state transition matrix....

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Veröffentlicht in:	Journal of spacecraft and rockets 2016-09, Vol.53 (5), p.811-821
Hauptverfasser:	Rogers, Andrew, Woolsey, Craig, Black, Jonathan, McGwier, Robert
Format:	Artikel
Sprache:	eng
Schlagworte:	Elliptical orbits Fuels Genetic algorithms Inclination Orbital maneuvers Trajectory optimization
Online-Zugang:	Volltext
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