In this paper we incorporate the low‐thrust propulsion in the stable manifold technique to design transfer trajectories to the halo orbits around L1 and L2 of the Earth‐Moon system. The problem is stated in an optimal control scheme and solved using direct transcription and collocation; the dynamics is discretized over an uniform time grid using a sixth‐order linear multi‐point method. The resulting transfers are made up by a spiral arc that targets a piece of the stable manifold associated to the final orbit. Thanks to the generality of this approach, halo‐to‐Moon transfers are also computed combining unstable manifolds and low‐thrust. Furthermore, complete Earth‐to‐Moon transfers via halos can also be constructed. Results show the feasibility of this kind of transfers requiring moderate propellant mass fractions and feasible times of flight.
Combined Optimal Low‐Thrust and Stable‐Manifold Trajectories to the Earth‐Moon Halo Orbits
NEW TRENDS IN ASTRODYNAMICS AND APPLICATIONS III ; 2006 ; Princeton, New Jersey (USA)
AIP Conference Proceedings ; 886 , 1 ; 100-112
2007-02-07
13 pages
Conference paper
Electronic Resource
English
Optimal Low-Thrust Trajectories to Earth-Moon L2 Halo Orbits (Circular Problem) (AAS 97-714)
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