Electric Propulsion Options for Mars Cargo Missions

Frisbee, Robert H.; Hoffman, Nathan J.

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&sube; 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