Design of optimal earth pole-sitter transfers using low-thrust propulsion

Heiligers, J., Ceriotti, M. , McInnes, C.R. and Biggs, J.D. (2012) Design of optimal earth pole-sitter transfers using low-thrust propulsion. Acta Astronautica, 79, pp. 253-268. (doi:10.1016/j.actaastro.2012.04.025)

68860.pdf - Accepted Version


Publisher's URL:


Recent studies have shown the feasibility of an Earth pole-sitter mission using low-thrust propulsion. This mission concept involves a spacecraft following the Earth's polar axis to have a continuous, hemispherical view of one of the Earth's poles. Such a view will enhance future Earth observation and telecommunications for high latitude and polar regions. To assess the accessibility of the pole-sitter orbit, this paper investigates optimum Earth pole-sitter transfers employing low-thrust propulsion. A launch from low Earth orbit (LEO) by a Soyuz Fregat upper stage is assumed after which solar electric propulsion is used to transfer the spacecraft to the pole-sitter orbit. The objective is to minimize the mass in LEO for a given spacecraft mass to be inserted into the pole-sitter orbit. The results are compared with a ballistic transfer that exploits manifold-like trajectories that wind onto the pole-sitter orbit. It is shown that, with respect to the ballistic case, low-thrust propulsion can achieve significant mass savings in excess of 200 kg for a pole-sitter spacecraft of 1000 kg upon insertion. To finally obtain a full low-thrust transfer from LEO up to the pole-sitter orbit, the Fregat launch is replaced by a low-thrust, minimum time spiral, which provides further mass savings, but at the cost of an increased time of flight.

Item Type:Articles
Glasgow Author(s) Enlighten ID:Ceriotti, Dr Matteo and McInnes, Professor Colin
Authors: Heiligers, J., Ceriotti, M., McInnes, C.R., and Biggs, J.D.
College/School:College of Science and Engineering > School of Engineering > Systems Power and Energy
Journal Name:Acta Astronautica
Published Online:29 May 2012
Copyright Holders:Copyright © 2012 Elsevier
First Published:First published in Acta Astronautica 79:253-268
Publisher Policy:Reproduced in accordance with the copyright policy of the publisher

University Staff: Request a correction | Enlighten Editors: Update this record