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

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• 作者：Jeannette Heiligers ; ^{jeannette.heiligers@strath.ac.uk}  ; [Author Vitae] ; Matteo Ceriotti¹ ; ^{matteo.ceriotti@strath.ac.uk}  ; [Author Vitae] ; Colin R. McInnes² ; ^{colin.mcinnes@strath.ac.uk}  ; [Author Vitae] ; James D. Biggs³ ; ^{james.biggs@strath.ac.uk}  ; [Author Vitae]
• 关键词：Pole-sitter ; Trajectory optimization ; Solar electric propulsion ; Low-thrust propulsion ; Soyuz launch ; Orbital averaging ; Low-thrust spiral
• 刊名：Acta Astronautica
• 出版年：2012
• 期刊代码：1_00945765
• 类别：et
• 出版时间：October-November, 2012
• 卷：79
• 期：Complete
• 页码：253-268
• 文件大小：2236 K

摘要

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.