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Multicriteria comparison among several mitigation strategies for dangerous near-Earth objects

Multicriteria comparison among several mitigation strategies for dangerous near-Earth objects
Multicriteria comparison among several mitigation strategies for dangerous near-Earth objects
In this paper, a comparative assessment of the effectiveness of different deviation methods for near-Earth objects is presented. Specifically, a solar collector, nuclear interceptor, kinetic impactor, low-thrust propulsion, mass driver, and gravity tug are modeled and compared. For each method, a mathematical model is developed to compute the achievable deviation. A multicriteria optimization method is then used to construct the set of Pareto-optimal solutions, minimizing the mass of the spacecraft at departure from the Earth and the warning time (i.e., the time from launch to the foreseen impact of the asteroid with the Earth), while maximizing the deviation. A dominance criterion is defined and used to compare all of the Pareto sets for all of the various mitigation strategies. Finally, a technology readiness level factor is associated with each strategy to estimate the required technological development
0731-5090
121-142
Sanchez, Joan Pau
5ef98f4c-a76c-4b41-9655-4670dc9548f6
Colombo, Camilla
595ced96-9494-40f2-9763-ad4a0f96bc86
Vasile, Massimiliano
de6550cb-82fc-49eb-b90b-dffa9787bf7d
Radice, Gianmarco
c9e2bab8-e37d-4bbd-8c00-4991856e0d2a
Sanchez, Joan Pau
5ef98f4c-a76c-4b41-9655-4670dc9548f6
Colombo, Camilla
595ced96-9494-40f2-9763-ad4a0f96bc86
Vasile, Massimiliano
de6550cb-82fc-49eb-b90b-dffa9787bf7d
Radice, Gianmarco
c9e2bab8-e37d-4bbd-8c00-4991856e0d2a

Sanchez, Joan Pau, Colombo, Camilla, Vasile, Massimiliano and Radice, Gianmarco (2009) Multicriteria comparison among several mitigation strategies for dangerous near-Earth objects. Journal of Guidance, Control, and Dynamics, 32 (1), 121-142. (doi:10.2514/1.36774).

Record type: Article

Abstract

In this paper, a comparative assessment of the effectiveness of different deviation methods for near-Earth objects is presented. Specifically, a solar collector, nuclear interceptor, kinetic impactor, low-thrust propulsion, mass driver, and gravity tug are modeled and compared. For each method, a mathematical model is developed to compute the achievable deviation. A multicriteria optimization method is then used to construct the set of Pareto-optimal solutions, minimizing the mass of the spacecraft at departure from the Earth and the warning time (i.e., the time from launch to the foreseen impact of the asteroid with the Earth), while maximizing the deviation. A dominance criterion is defined and used to compare all of the Pareto sets for all of the various mitigation strategies. Finally, a technology readiness level factor is associated with each strategy to estimate the required technological development

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Published date: 2009
Organisations: Astronautics Group

Identifiers

Local EPrints ID: 342356
URI: http://eprints.soton.ac.uk/id/eprint/342356
ISSN: 0731-5090
PURE UUID: 489136ae-4c16-47cd-99c4-ad4df7cf6ba5
ORCID for Camilla Colombo: ORCID iD orcid.org/0000-0001-9636-9360

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Date deposited: 24 Aug 2012 07:57
Last modified: 10 Dec 2019 02:03

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Contributors

Author: Joan Pau Sanchez
Author: Camilla Colombo ORCID iD
Author: Massimiliano Vasile
Author: Gianmarco Radice

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