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Abstract
Due to the noncentral nature of the force on a solar sail, there exist equilibrium points of the equations of motion out of the ecliptic plane in the SunEarthSail circular restricted 3body 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.
Original language  English 

Publication status  Published  2007 
Event  AAS/AIAA Space Flight Mechanics Conference  Sedona, Arizona Duration: 28 Jan 2007 → 1 Feb 2007 
Conference
Conference  AAS/AIAA Space Flight Mechanics Conference 

City  Sedona, Arizona 
Period  28/01/07 → 1/02/07 
Keywords
 solar sails
 flight
 space flight
 orbits
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Dive into the research topics of 'Periodic orbits high above the ecliptic plane in the solar sail 3body problem'. Together they form a unique fingerprint.Projects
 1 Finished

Dynamics, Stability and Control of Highly NonKeplerian Orbits
McInnes, C.
EPSRC (Engineering and Physical Sciences Research Council)
1/10/05 → 31/05/09
Project: Research