Pole-sitters are a novel satellite concept following a non-Keplerian orbit along a planetary rotation axis to allow continuous and hemispherical coverage of the planet's Polar Regions. Station-keeping of such a pole-sitter orbit can be achieved through the use of solar electric propulsion (SEP) or a hybridization of SEP and solar sail propulsion. This paper extends previous work on Earth pole-sitters to pole-sitters at the other inner Solar System planets, allowing a range of novel extra-terrestrial mission applications and investigating the general physical principles behind pole-sitters. To minimize SEP propellant consumption, optimal pole-sitter trajectories are found through a direct multiple shooting approach. Furthermore, to achieve a realistic estimate of the mission objectives in terms of mission lifetime and/or payload mass, the effect of solar sail degradation is investigated and its impact on the mission is quantified. Finally, a parametric analysis is conducted to investigate the link between planetary variables and mission objectives. It is shown that planetary mass is the key parameter in determining fuel efficiency, with axial tilt being significant only for high mass planets.
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