Trajectory and spacecraft design for a pole-sitter mission

Ceriotti, M. , Heiligers, J. and McInnes, C. R. (2014) Trajectory and spacecraft design for a pole-sitter mission. Journal of Spacecraft and Rockets, 51(1), pp. 311-326. (doi: 10.2514/1.A32477)

Abstract

This paper provides a detailed mission analysis and systems design of a pole-sitter mission. It considers a spacecraft that is continuously above either the North or South Pole and, as such, can provide real-time, continuous, and hemispherical coverage of the polar regions. Two different propulsion strategies are proposed, which result in a near-term pole-sitter mission using solar-electric propulsion and a far-term pole-sitter mission, in which the electric thruster is hybridized with a solar sail. For both propulsion strategies, minimum propellant pole-sitter orbits are designed. Optimal transfers from Earth to the pole sitter are designed, assuming Soyuz and Ariane 5 launch options, and a controller is shown to be able to maintain the trajectory under unexpected conditions, such as injection errors. A detailed mass budget analysis allows for a tradeoff between mission lifetime and payload mass capacity, and candidate payloads for a range of applications are investigated. This results in a payload of about 100 kg that can operate for approximately four years with the solar-electric spacecraft, whereas the hybrid-propulsion technology enables extending the missions up to seven years. Transfers between north and south pole-sitter orbits are also considered to observe either pole when illuminated by the sun.

• Item Type: Articles
• Status: Published
• Refereed: Yes
• Glasgow Author(s) Enlighten ID: Ceriotti, Dr Matteo and McInnes, Professor Colin
• Authors: Ceriotti, M., Heiligers, J., and McInnes, C. R.
• College/School: College of Science and Engineering > School of Engineering > Systems Power and Energy
• Journal Name: Journal of Spacecraft and Rockets
• Publisher: American Institute of Aeronautics and Astronautics
• ISSN: 0022-4650
• ISSN (Online): 1533-6794
• Copyright Holders: Copyright © 2013 The Authors
• First Published: First published in Journal of Spacecraft and Rockets
• Publisher Policy: Reproduced in accordance with the copyright policy of the publisher