Low-thrust-enabled highly-non-Keplerian orbits in support of future Mars exploration

Macdonald, M., McKay, R. J., Vasile, M., De Frescheville, F. B., Biggs, J. and McInnes, C. (2011) Low-thrust-enabled highly-non-Keplerian orbits in support of future Mars exploration. Journal of Guidance, Control, and Dynamics, 34(5), pp. 1396-1411. (doi:10.2514/1.52602)

Macdonald, M., McKay, R. J., Vasile, M., De Frescheville, F. B., Biggs, J. and McInnes, C. (2011) Low-thrust-enabled highly-non-Keplerian orbits in support of future Mars exploration. Journal of Guidance, Control, and Dynamics, 34(5), pp. 1396-1411. (doi:10.2514/1.52602)

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Publisher's URL: http://dx.doi.org/10.2514/1.52602

Abstract

The technology of high-specific-impulse propulsion systems with low thrust is improving, opening up numerous possibilities for future missions applying continuous thrust to force a spacecraft out of a natural Keplerian orbit into a displaced non-Keplerian orbit. A systematic analysis is presented as to the applicability of highly-non-Keplerian orbits throughout the solar system. Thereafter, two applications of such orbits in support of future high-value-asset exploration of Mars are detailed: a novel concept for an Earth–Mars interplanetary communications relay, on which the paper largely focuses, and a solar storm warning mission. In the former the relay makes use of artificial equilibrium points, allowing a spacecraft to hover above the orbital plane of Mars and thus ensuring communications when the planet is occulted by the sun with respect to the Earth. The spacecraft’s power requirements and communications band used are taken into account to determine the relay architecture. A detailed contingency analysis is considered for recovering the relay after increasing periods of spacecraft propulsion failure, combined with a consideration of how to deploy the relay spacecraft to maximize propellant reserves and mission duration. For such a relay, a combination of solar sail and solar electric propulsion may prove to be advantageous, but only under specific circumstances of the relay architecture suggested. For highly-non-Keplerian orbits the dynamics of the spacecraft is also briefly extended to consider the elliptic restricted three-body problem and the effects of orbit eccentricity.

Item Type:Articles
Status:Published
Refereed:Yes
Glasgow Author(s) Enlighten ID:McInnes, Professor Colin and Vasile, Dr Massimiliano
Authors: Macdonald, M., McKay, R. J., Vasile, M., De Frescheville, F. B., Biggs, J., and McInnes, C.
College/School:College of Science and Engineering > School of Engineering > Systems Power and Energy
Journal Name:Journal of Guidance, Control, and Dynamics
Publisher:American Institute of Aeronautics and Astronautics
ISSN:0731-5090
ISSN (Online):1533-3884

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