### Abstract

Original language | English |
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Pages | AC-06-A3.5.8 |

Number of pages | 13 |

Publication status | Published - 2 Oct 2006 |

Event | AIAA 57th International Astronautical Congress - Valencia, Spain Duration: 2 Oct 2006 → 6 Oct 2006 |

### Conference

Conference | AIAA 57th International Astronautical Congress |
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Country | Spain |

City | Valencia |

Period | 2/10/06 → 6/10/06 |

### Fingerprint

### Keywords

- dangerous near earth objects
- solar collector
- nuclear blast
- kinetic impactor
- low thrust propulsion
- mass driver
- pareto optimal solutions

### Cite this

*A comparative assessment of different deviation strategies for dangerous NEO*. AC-06-A3.5.8 . Paper presented at AIAA 57th International Astronautical Congress, Valencia, Spain.

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**A comparative assessment of different deviation strategies for dangerous NEO.** / Colombo, Camilla; S. Cuartielles, Joan-Pau ; Vasile, Massimiliano; Radice, Gianmarco.

Research output: Contribution to conference › Paper

TY - CONF

T1 - A comparative assessment of different deviation strategies for dangerous NEO

AU - Colombo, Camilla

AU - S. Cuartielles, Joan-Pau

AU - Vasile, Massimiliano

AU - Radice, Gianmarco

PY - 2006/10/2

Y1 - 2006/10/2

N2 - In this paper a number of deviation strategies for dangerous Near Earth Objects (NEO) have been compared. For each strategy (i.e. Solar Collector, Nuclear Blast, Kinetic Impactor, Low-thrust Propulsion, Mass Driver) a multi criteria optimisation method has been used to reconstruct the set of Pareto optimal solutions minimising the mass of the spacecraft and the warning time, and maximising the deviation. Then, a dominance criterion has been defined and used to compare all the Pareto sets. The achievable deviation at the MOID, either for a low-thrust or for an impulsive variation of the orbit of the NEO, has been computed through a set of analytical formulas. The variation of the orbit of the NEO has been estimated through a deviation action model that takes into account the wet mass of the spacecraft at the Earth. Finally the technology readiness level of each strategy has been used to compute a more realistic value for the required warning time.

AB - In this paper a number of deviation strategies for dangerous Near Earth Objects (NEO) have been compared. For each strategy (i.e. Solar Collector, Nuclear Blast, Kinetic Impactor, Low-thrust Propulsion, Mass Driver) a multi criteria optimisation method has been used to reconstruct the set of Pareto optimal solutions minimising the mass of the spacecraft and the warning time, and maximising the deviation. Then, a dominance criterion has been defined and used to compare all the Pareto sets. The achievable deviation at the MOID, either for a low-thrust or for an impulsive variation of the orbit of the NEO, has been computed through a set of analytical formulas. The variation of the orbit of the NEO has been estimated through a deviation action model that takes into account the wet mass of the spacecraft at the Earth. Finally the technology readiness level of each strategy has been used to compute a more realistic value for the required warning time.

KW - dangerous near earth objects

KW - solar collector

KW - nuclear blast

KW - kinetic impactor

KW - low thrust propulsion

KW - mass driver

KW - pareto optimal solutions

M3 - Paper

SP - AC-06-A3.5.8

ER -