Evolved spacecraft trajectories for low earth orbit

@article{Hinckley2014EvolvedST,
  title={Evolved spacecraft trajectories for low earth orbit},
  author={D. Hinckley and Karol Zieba and D. Hitt and M. Eppstein},
  journal={Proceedings of the 2014 Annual Conference on Genetic and Evolutionary Computation},
  year={2014}
}
In this paper we use Differential Evolution (DE), with best evolved results refined using a Nelder-Mead optimization, to solve complex problems in orbital mechanics relevant to low Earth orbits (LEO. [...] Key Method We first validate that the method can recover known analytical solutions obtainable with the assumption of Keplerian motion.Expand
Evolved Non-Keplerian Spacecraft Trajectories for Near-Earth Orbital Maneuvers
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Differential Evolution is used, with best-evolved results refined using a Nelder-Mead optimization, to solve complex problems in orbital mechanics relevant to low Earth orbits (LEO) and within the Earth-Moon system. Expand
Evolutionary Approach to Lambert’s Problem for Non-Keplerian Spacecraft Trajectories
In this paper, we use differential evolution (DE), with best-evolved results refined using a Nelder–Mead optimization, to solve boundary-value complex problems in orbital mechanics relevant to lowExpand

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