Abstract
Rideshares increase launch capabilities and decrease the launch costs. However, the range of orbits available for secondary payloads is dependent on launch constraints for the primary mission. Additionally, communications constraints and limited propellant options must be incorporated in the preliminary mission design strategy for secondary payloads. Ridesharing opportunities are now available for orbit destinations beyond Low Earth Orbit (LEO). In this investigation, transfers from Geosynchronous Transfer Orbits (GTO) to Sun-Earth libration point orbits are constructed by leveraging stable manifold structures and Poincaré maps.
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Acknowledgements
The authors thank Mr. Michael Mesarch for introducing this research topic. Assistance and guidance from colleagues in the Multi-Body Dynamics Research group at Purdue University is much appreciated as is the support of the Purdue University School of Aeronautics and Astronautics including access to the Rune and Barbara Eliasen Visualization Laboratory. This material is based upon work supported by the National Science Foundation Graduate Research Fellowship Program under Grant No. DGE-1333468. Any opinions, findings, and conclusions or recommendations expressed in this material are those of the author(s) and do not necessarily reflect the views of the National Science Foundation.
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A portion of this paper was presented during the AAS/AIAA Astrodynamics Specialist Conference in Portland, Maine in August 2019.
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Ojeda Romero, J., Howell, K.C. Transfers from Geosynchronous Transfer Orbits to Sun-Earth Libration Point Trajectories. J Astronaut Sci 69, 251–283 (2022). https://doi.org/10.1007/s40295-022-00308-0
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DOI: https://doi.org/10.1007/s40295-022-00308-0