Optimal impact strategies for asteroid deflection

Massimiliano Vasile, Camilla Colombo

Research output: Contribution to journalArticle

50 Citations (Scopus)
68 Downloads (Pure)

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.
Original languageEnglish
Pages (from-to)858-872
Number of pages14
JournalJournal of Guidance, Control and Dynamics
Volume31
Issue number4
DOIs
Publication statusPublished - Jul 2008

Fingerprint

Asteroids
asteroids
deflection
asteroid
Deflection
Spacecraft
Deviation
spacecraft
Motion
Formulation
deviation
formulations
Impulse
Global Optimization
Global optimization
Intersection
Orbit
intersections
Equations of motion
impulses

Keywords

  • optimal impact strategies
  • asteroid deflection

Cite this

@article{5790b48f5bec440eaad925ee39903dc7,
title = "Optimal impact strategies for asteroid deflection",
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.",
keywords = "optimal impact strategies, asteroid deflection",
author = "Massimiliano Vasile and Camilla Colombo",
note = "COPYRIGHT OWNED BY ALL AUTHORS",
year = "2008",
month = "7",
doi = "10.2514/1.33432",
language = "English",
volume = "31",
pages = "858--872",
journal = "Journal of Guidance, Control and Dynamics",
issn = "0731-5090",
number = "4",

}

Optimal impact strategies for asteroid deflection. / Vasile, Massimiliano; Colombo, Camilla.

In: Journal of Guidance, Control and Dynamics, Vol. 31, No. 4, 07.2008, p. 858-872.

Research output: Contribution to journalArticle

TY - JOUR

T1 - Optimal impact strategies for asteroid deflection

AU - Vasile, Massimiliano

AU - Colombo, Camilla

N1 - COPYRIGHT OWNED BY ALL AUTHORS

PY - 2008/7

Y1 - 2008/7

N2 - 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.

AB - 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.

KW - optimal impact strategies

KW - asteroid deflection

U2 - 10.2514/1.33432

DO - 10.2514/1.33432

M3 - Article

VL - 31

SP - 858

EP - 872

JO - Journal of Guidance, Control and Dynamics

JF - Journal of Guidance, Control and Dynamics

SN - 0731-5090

IS - 4

ER -