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Semi-analytical solution for the optimal low-thrust deflection of near-Earth objects

Semi-analytical solution for the optimal low-thrust deflection of near-Earth objects
Semi-analytical solution for the optimal low-thrust deflection of near-Earth objects
This paper presents a semi-analytical solution of the asteroid deviation problem when a low-thrust action, inversely proportional to the square of the distance from the sun, is applied to the asteroid. The displacement of the asteroid at the minimum orbit interception distance from the Earth’s orbit is computed through proximal motion equations as a function of the variation of the orbital elements. A set of semi-analytical formulas is then derived tocompute the variation of the elements: Gauss planetary equations are averaged over one orbital revolution to give the secular variation of the elements, and their periodic components are approximated through a trigonometric expansion. Two formulations of the semi-analytical formulas, latitude and time formulation, are presented along with their accuracy against a full numerical integration of Gauss equations. It is shown that the semi-analytical approach provides a significant savings in computational time while maintaining a good accuracy. Finally, some examples of deviation missions are presented as an application of the proposed semi-analytical theory. In particular,the semi-analytical formulas are used in conjunction with a multi-objective optimization algorithm to find the set of Pareto-optimal mission options that minimizes the asteroid warning time and the spacecraft mass while maximizing the orbital deviation
0731-5090
796-809
Colombo, Camilla
595ced96-9494-40f2-9763-ad4a0f96bc86
Vasile, Massimiliano
de6550cb-82fc-49eb-b90b-dffa9787bf7d
Radice, Gianmarco
c9e2bab8-e37d-4bbd-8c00-4991856e0d2a
Colombo, Camilla
595ced96-9494-40f2-9763-ad4a0f96bc86
Vasile, Massimiliano
de6550cb-82fc-49eb-b90b-dffa9787bf7d
Radice, Gianmarco
c9e2bab8-e37d-4bbd-8c00-4991856e0d2a

Colombo, Camilla, Vasile, Massimiliano and Radice, Gianmarco (2009) Semi-analytical solution for the optimal low-thrust deflection of near-Earth objects. Journal of Guidance, Control, and Dynamics, 32 (3), 796-809. (doi:10.2514/1.40363).

Record type: Article

Abstract

This paper presents a semi-analytical solution of the asteroid deviation problem when a low-thrust action, inversely proportional to the square of the distance from the sun, is applied to the asteroid. The displacement of the asteroid at the minimum orbit interception distance from the Earth’s orbit is computed through proximal motion equations as a function of the variation of the orbital elements. A set of semi-analytical formulas is then derived tocompute the variation of the elements: Gauss planetary equations are averaged over one orbital revolution to give the secular variation of the elements, and their periodic components are approximated through a trigonometric expansion. Two formulations of the semi-analytical formulas, latitude and time formulation, are presented along with their accuracy against a full numerical integration of Gauss equations. It is shown that the semi-analytical approach provides a significant savings in computational time while maintaining a good accuracy. Finally, some examples of deviation missions are presented as an application of the proposed semi-analytical theory. In particular,the semi-analytical formulas are used in conjunction with a multi-objective optimization algorithm to find the set of Pareto-optimal mission options that minimizes the asteroid warning time and the spacecraft mass while maximizing the orbital deviation

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Published date: 2009
Organisations: Astronautics Group

Identifiers

Local EPrints ID: 342325
URI: http://eprints.soton.ac.uk/id/eprint/342325
ISSN: 0731-5090
PURE UUID: 22dce664-74cb-40ce-8864-8a7e85a963aa
ORCID for Camilla Colombo: ORCID iD orcid.org/0000-0001-9636-9360

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Date deposited: 22 Aug 2012 10:40
Last modified: 05 Nov 2019 02:14

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