NDLI: Lunar cube transfer trajectory options (Document No: 20150020472)

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Lunar cube transfer trajectory options (Document No: 20150020472)

Content Provider	NASA Technical Reports Server (NTRS)
Author	Howell, Kathleen Folta, David Clark, Pamela E. Haapala, Amanda Dichmann Sr., Donald James
Copyright Year	2015
Description	Numerous Earth-Moon trajectory and lunar orbit options are available for Cubesat missions. Given the limited Cubesat injection infrastructure, transfer trajectories are contingent upon the modification of an initial condition of the injected or deployed orbit. Additionally, these transfers can be restricted by the selection or designs of Cubesat subsystems such as propulsion or communication. Nonetheless, many trajectory options can b e considered which have a wide range of transfer duration, fuel requirements, and final destinations. Our investigation of potential trajectories highlights several options including deployment from low Earth orbit (LEO) geostationary transfer orbits (GTO) and higher energy direct lunar transfer and the use of longer duration Earth-Moon dynamical systems. For missions with an intended lunar orbit, much of the design process is spent optimizing a ballistic capture while other science locations such as Sun-Earth libration or heliocentric orbits may simply require a reduced Delta-V imparted at a convenient location along the trajectory.
File Size	1809749
Page Count	18
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20150020472
Archival Resource Key	ark:/13960/t25b5403b
Language	English
Publisher Date	2015-01-11
Access Restriction	Open
Subject Keyword	Libration Orbits Dynamical System Earth-moon Low Earth Orbits Lunar Trajectories Transfer Orbits Propulsion Trajectories Geosynchronous Orbits Libration Dynamical Systems Earth-moon Trajectories Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Presentation

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