Spacecraft trajectories to the L3 point of the Sun–Earth three-body problem-Reference-Cited by-同舟云学术

Spacecraft trajectories to the L3 point of the Sun–Earth three-body problem

Published:2010-07-30 Issue:3 Volume:108 Page:215-232
ISSN:0923-2958
Container-title:Celestial Mechanics and Dynamical Astronomy
language:en
Short-container-title:Celest Mech Dyn Astr

Author:

Tantardini Marco,Fantino Elena,Ren Yuan,Pergola Pierpaolo,Gómez Gerard,Masdemont Josep J.

Publisher

Springer Science and Business Media LLC

Subject

Space and Planetary Science,Astronomy and Astrophysics,Applied Mathematics,Computational Mathematics,Mathematical Physics,Modelling and Simulation

Link

http://link.springer.com/content/pdf/10.1007/s10569-010-9299-x.pdf

Reference13 articles.

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3. Font, J.: The Role of Homoclinic and Heteroclinic Orbits in Two-Degrees of Freedom Hamiltonian Systems. Ph.D. Dissertation, Departament de Matematica. Aplicada i Analisi, Universitat de Barcelona (1990)

4. Gill P.E., Murray W., Saunders M.A.: Snopt: an sqp algorithm for large-scale constrained optimization. SIAM J. Optim. 12, 979–1006 (2002)

5. Gómez G., Koon W.S., Lo M.W., Marsden J., Masdemont J., Ross S.D.: Connecting orbits and invariant manifolds in the spatial three-body problem. Nonlinearity 17, 1571 (2004)

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