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Optimal impact strategies for asteroid deflection

Optimal impact strategies for asteroid deflection
Optimal impact strategies for asteroid deflection
This paper presents an analysis of optimal impact strategies to deflect potentially dangerous asteroids. To compute the increase in the minimum orbit intersection distance of the asteroid due to an impact with a spacecraft, simple analytical formulas are derived from proximal motion equations. The proposed analytical formulation allows for an analysis of the optimal direction of the deviating impulse transferred to the asteroid. This ideal optimal direction cannot be achieved for every asteroid at any time; therefore, an analysis of the optimal launch opportunities for deviating a number of selected asteroids was performed through the use of a global optimization procedure. The results in this paper demonstrate that the proximal motion formulation has very good accuracy in predicting the actual deviation and can be used with any deviation method because it has general validity. Furthermore, the characterization of optimal launch opportunities shows that a significant deviation can be obtained even with a small spacecraft
0731-5090
858-872
Vasile, Massimiliano
de6550cb-82fc-49eb-b90b-dffa9787bf7d
Colombo, Camilla
595ced96-9494-40f2-9763-ad4a0f96bc86
Vasile, Massimiliano
de6550cb-82fc-49eb-b90b-dffa9787bf7d
Colombo, Camilla
595ced96-9494-40f2-9763-ad4a0f96bc86

Vasile, Massimiliano and Colombo, Camilla (2008) Optimal impact strategies for asteroid deflection. Journal of Guidance, Control, and Dynamics, 31 (4), 858-872. (doi:10.2514/1.33432).

Record type: Article

Abstract

This paper presents an analysis of optimal impact strategies to deflect potentially dangerous asteroids. To compute the increase in the minimum orbit intersection distance of the asteroid due to an impact with a spacecraft, simple analytical formulas are derived from proximal motion equations. The proposed analytical formulation allows for an analysis of the optimal direction of the deviating impulse transferred to the asteroid. This ideal optimal direction cannot be achieved for every asteroid at any time; therefore, an analysis of the optimal launch opportunities for deviating a number of selected asteroids was performed through the use of a global optimization procedure. The results in this paper demonstrate that the proximal motion formulation has very good accuracy in predicting the actual deviation and can be used with any deviation method because it has general validity. Furthermore, the characterization of optimal launch opportunities shows that a significant deviation can be obtained even with a small spacecraft

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Published date: July 2008
Organisations: Astronautics Group

Identifiers

Local EPrints ID: 342324
URI: http://eprints.soton.ac.uk/id/eprint/342324
ISSN: 0731-5090
PURE UUID: 059e96f6-4f72-4a91-b0e4-f6cf088584f0
ORCID for Camilla Colombo: ORCID iD orcid.org/0000-0001-9636-9360

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Date deposited: 22 Aug 2012 10:30
Last modified: 10 Dec 2019 02:03

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