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Abstract
In this paper we consider periodic orbits of a solar sail in the EarthSun restricted threebody problem. In particular, we consider orbits which are high above the ecliptic plane, in contrast to the classical Halo orbits about the collinear equilibria. We begin with the Circular Restricted ThreeBody Problem (CRTBP) where periodic orbits about equilibria are naturally present at linear order. Using the method of LindstedtPoincaré, we construct nth order approximations to periodic solutions of the nonlinear equations of motion. In the second part of the paper we generalize to the Elliptic Restricted Three Body Problem (ERTBP). A numerical continuation, with the eccentricity, e, as the varying parameter, is used to find periodic orbits above the ecliptic, starting from a known orbit at e = 0 and continuing to the required eccentricity of e = 0:0167. The stability of these periodic orbits is investigated.
Original language  English 

Number of pages  11 
Publication status  Published  Jul 2008 
Event  2nd Conference on Nonlinear Science and Complexity  Porto, Portugal Duration: 28 Jul 2008 → 31 Jul 2008 
Conference
Conference  2nd Conference on Nonlinear Science and Complexity 

City  Porto, Portugal 
Period  28/07/08 → 31/07/08 
Keywords
 periodic orbits
 solar sail
 elliptic three body problem
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Dive into the research topics of 'New periodic orbits in the solar sail restricted three body 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