### 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.

Language | English |
---|---|

Pages | 309-336 |

Number of pages | 28 |

Journal | Celestial Mechanics and Dynamical Astronomy |

Volume | 120 |

Issue number | 3 |

Early online date | 5 Oct 2014 |

DOIs | |

Publication status | Published - Nov 2014 |

### Fingerprint

### Keywords

- asteroid retrieval candidates
- distant prograde periodic orbit (DPO)
- easily retrievable objects (EROs)
- invariant manifolds
- libration point periodic orbit (LPO)
- low-thrust propulsion
- near earth object capture
- optimal control problem
- special dedicated sets

### Cite this

*Celestial Mechanics and Dynamical Astronomy*,

*120*(3), 309-336. https://doi.org/10.1007/s10569-014-9589-9

}

*Celestial Mechanics and Dynamical Astronomy*, vol. 120, no. 3, pp. 309-336. https://doi.org/10.1007/s10569-014-9589-9

**Combined low-thrust propulsion and invariant manifold trajectories to capture NEOs in the Sun–Earth circular restricted three-body problem.** / Mingotti, G.; Sánchez, J. P.; McInnes, C. R.

Research output: Contribution to journal › Article

TY - JOUR

T1 - Combined low-thrust propulsion and invariant manifold trajectories to capture NEOs in the Sun–Earth circular restricted three-body problem

AU - Mingotti, G.

AU - Sánchez, J. P.

AU - McInnes, C. R.

PY - 2014/11

Y1 - 2014/11

N2 - 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.

AB - 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.

KW - asteroid retrieval candidates

KW - distant prograde periodic orbit (DPO)

KW - easily retrievable objects (EROs)

KW - invariant manifolds

KW - libration point periodic orbit (LPO)

KW - low-thrust propulsion

KW - near earth object capture

KW - optimal control problem

KW - special dedicated sets

UR - http://www.scopus.com/inward/record.url?scp=84912022074&partnerID=8YFLogxK

U2 - 10.1007/s10569-014-9589-9

DO - 10.1007/s10569-014-9589-9

M3 - Article

VL - 120

SP - 309

EP - 336

JO - Celestial Mechanics and Dynamical Astronomy

T2 - Celestial Mechanics and Dynamical Astronomy

JF - Celestial Mechanics and Dynamical Astronomy

SN - 0923-2958

IS - 3

ER -