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Electric Propulsion Options for Mars Cargo Missions

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dc.contributor.author Frisbee, Robert H. en_US
dc.contributor.author Hoffman, Nathan J. en_US
dc.date.accessioned 2004-09-30T22:23:06Z
dc.date.available 2004-09-30T22:23:06Z
dc.date.issued 1996-07-01 en_US
dc.identifier.citation Lake Buena Vista, FL en_US
dc.identifier.clearanceno 96-1039 en_US
dc.identifier.uri http://hdl.handle.net/2014/26026
dc.description.abstract This paper summarizes an evaluation of mission performance (in terms of vehicle mass and trip time of solar electric propulsion (SEP) and nuclear electric propulsion (NEP) operating at power levels on the order of 1.5 MW⊆ for Mars cargo missions. The SEP and NEP vehicles are both assumed to use lithium-propellant magnetoplasmadynamic (MPD) thrusters with an efficiency (electric-to-jet) of 60 percent at a specified nominal specific impulse. en_US
dc.format.extent 1049428 bytes
dc.format.mimetype application/pdf
dc.language.iso en_US
dc.subject.other SEP NEP solar electric propulsion nuclear electric propulsion Mars MPD magnetoplasmadynamic thrusters lithium SP-100 reactor cargo missions en_US
dc.title Electric Propulsion Options for Mars Cargo Missions en_US


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