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Negative C3 Launch Options for Solar System ExplorationLow thrust trajectory analyses were used to examine the feasibility of using solar electronic propulsion for Earth escape from a negative C3 launch for deep space missions in order to significantly increase the net delivered mass capability of inexpensive launch vehicles.
Document ID
20060034743
Acquisition Source
Jet Propulsion Laboratory
Document Type
Conference Paper
External Source(s)
hdl:2014/20228
Authors
Leifer, S.
Noca, M.
Date Acquired
August 23, 2013
Publication Date
July 13, 1998
Subject Category
Spacecraft Propulsion And Power
Distribution Limits
Public
Copyright
Other
Keywords
negative C3 Solar System Exploration Earth mass comparison solar electronic
propulsion

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