Strathprints logo
Strathprints Home | Open Access | Browse | Search | User area | Copyright | Help | Library Home | SUPrimo

Design of trajectories for continuous polar Earth observation in the Earth-Moon system

Ceriotti, Matteo and McInnes, Colin (2012) Design of trajectories for continuous polar Earth observation in the Earth-Moon system. In: 63rd International Astronautical Congress, 2012-10-01 - 2012-10-05, Naples.

[img] PDF
Ceriotti_M_McInnes_CR_Pure_Design_of_trajectories_for_continuous_polar_Earth_observation_in_the_Earth_Moon_system_Oct_2012.pdf - Draft Version

Download (767kB)


This paper investigates orbits and transfer trajectories for continuous polar Earth observation in the Earth-Moon system. The motivation behind this work is to complement the services offered by polar-orbiting spacecraft, which offer high resolution imaging but poor temporal resolution, due to the fact that they can only capture one narrow swath at each polar passage. Conversely, a platform for high-temporal resolution imaging can enable a number of applications, from accurate polar weather forecasting to Aurora study, as well as direct-link telecommunications with high-latitude regions. Such a platform would complement polar orbiters. In this work, we make use of resonant gravity swing-by manoeuvres at the Moon in order to design trajectories that are suitable for quasi-continuous polar observation. In particular, it is shown that the Moon can flip the line of apsides of a highly eccentric, highly inclined orbit from north to south, without the need for thrust. In this way, a spacecraft can alternatively hover for an extended period of time above the two poles. In addition, at the lunar encounter it is possible to change the period of time spent on each pole. In addition, we also show that the lunar swing-by can be exploited for transfer to a so-called pole-sitter orbit, i.e. a spacecraft that constantly hovers above one of the Earth’s poles. It is shown that, by using the Moon’s gravity to change the inclination of the transfer trajectory, the total Δv is less than using a trajectory solely relying on high-thrust or low-thrust, therefore enabling the launchers to inject more mass into the target pole-sitter position.

Item type: Conference or Workshop Item (Paper)
ID code: 41268
Keywords: earth orbit, transfer trajectories, polar-sitter orbit, Earth-Moon system, Mechanical engineering and machinery, Motor vehicles. Aeronautics. Astronautics, Aerospace Engineering, Control and Systems Engineering
Subjects: Technology > Mechanical engineering and machinery
Technology > Motor vehicles. Aeronautics. Astronautics
Department: Faculty of Engineering > Mechanical and Aerospace Engineering
Technology and Innovation Centre > Advanced Engineering and Manufacturing
Depositing user: Pure Administrator
Date Deposited: 28 Sep 2012 08:16
Last modified: 24 Jul 2015 13:22
Related URLs:

Actions (login required)

View Item View Item