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Celestial Mechanics and Dynamical Astronomy

, Volume 120, Issue 3, pp 309–336 | Cite as

Combined low-thrust propulsion and invariant manifold trajectories to capture NEOs in the Sun–Earth circular restricted three-body problem

  • G. MingottiEmail author
  • J. P. Sánchez
  • C. R. McInnes
Original Article

Abstract

In this paper, a method to capture near-Earth objects (NEOs) incorporating low-thrust propulsion into the invariant manifolds technique is investigated. Assuming that a tugboat-spacecraft is in a rendez-vous condition with the candidate asteroid, the aim is to take the joint spacecraft-asteroid system to a selected periodic orbit of the Sun–Earth restricted three-body system: the orbit can be either a libration point periodic orbit (LPO) or a distant prograde periodic orbit (DPO) around the Earth. In detail, low-thrust propulsion is used to bring the joint spacecraft-asteroid system from the initial condition to a point belonging to the stable manifold associated to the final periodic orbit: from here onward, thanks to the intrinsic dynamics of the physical model adopted, the flight is purely ballistic. Dedicated guided and capture sets are introduced to exploit the combined use of low-thrust propulsion with stable manifolds trajectories, aiming at defining feasible first guess solutions. Then, an optimal control problem is formulated to refine and improve them. This approach enables a new class of missions, whose solutions are not obtainable neither through the patched-conics method nor through the classic invariant manifolds technique.

Keywords

Near-Earth object capture Invariant manifolds Low-thrust propulsion Special dedicated sets Optimal control problem Libration point periodic orbit (LPO) Distant prograde periodic orbit (DPO) Easily retrievable objects (EROs) Asteroid retrieval candidates 

Notes

Acknowledgments

This research was performed in the framework of the project supported by the European Research Council Advanced Investigator Grant—227571: VISIONSPACE, Orbital Dynamics at Extremes of Spacecraft Length-Scale. J.P. Sánchez is supported by the European Commission under the Marie Curie Grant 330649 (AsteroidRetrieval). Part of the work described in this paper has been presented at the Sixth Meeting on Celestial Mechanics–CELMEC VI, San Martino al Cimino (VT), Italy, 1–7 September 2013.

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© Springer Science+Business Media Dordrecht 2014

Authors and Affiliations

  1. 1.Advanced Space Concepts Laboratory, Department of Mechanical and Aerospace EngineeringUniversity of StrathclydeGlasgowUK
  2. 2.Departament de Matemàtica Aplicada IUniversitat Politècnica de CatalunyaBarcelonaSpain

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