Waters, T. and McInnes, C.R. (2007) Periodic orbits high above the ecliptic plane in the solar sail 3-body problem. In: AAS/AIAA Space Flight Mechanics Conference, 2007-01-28 - 2007-02-01.
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Due to the non-central nature of the force on a solar sail, there exist equilibrium points of the equations of motion out of the ecliptic plane in the Sun-Earth-Sail circular restricted 3-body problem, in contrast with the classical Lagrange points. Analogous to the 'halo' orbits, we construct large amplitude periodic orbits about these equilibria. By timing the period of the orbit we may negate the seasonal effects of the variation in the Earth's axis of rotation, and thus the sail's position when viewed from the pole subtends a much smaller angle (around 8 deg rather than 46 deg). These orbits are of practical interest with regards to communication with, and constant imaging of, the poles.
|Item type:||Conference or Workshop Item (Paper)|
|Keywords:||solar sails, flight, space flight, orbits, Mechanical engineering and machinery, Motor vehicles. Aeronautics. Astronautics|
|Subjects:||Technology > Mechanical engineering and machinery
Technology > Motor vehicles. Aeronautics. Astronautics
|Department:||Faculty of Engineering > Mechanical and Aerospace Engineering|
|Depositing user:||Strathprints Administrator|
|Date Deposited:||12 Aug 2008|
|Last modified:||03 Apr 2017 20:01|