{"id":{"repo_id":"vt","oai_identifier":"oai:vtechworks.lib.vt.edu:10919/36063"},"canonical_url":"https://search.dev.ndltd.org/etd/vt/oai:vtechworks.lib.vt.edu:10919/36063","repository":{"repo_id":"vt","name":"Virginia Tech","base_url":"https://vtechworks.lib.vt.edu/oai/request"},"display":{"title":"Lunar Robotic Precursor Missions Using Electric Propulsion","abstract":"A trade study is carried out for the design of electric propulsion based lunar robotic precursor missions. The focus is to understand the relationships between payload mass delivered, electric propulsion power, and trip time. The results are compared against a baseline system using chemical propulsion with LOX/H2. The major differences between the chemical propulsion based and electric propulsion based systems are presented in terms of the payload mass and trip time. 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The focus is to understand the relationships between payload mass delivered, electric propulsion power, and trip time. The results are compared against a baseline system using chemical propulsion with LOX/H2. The major differences between the chemical propulsion based and electric propulsion based systems are presented in terms of the payload mass and trip time. It is shown that solar electric propulsion offers significant advantage over chemical propulsion in delivering non-time critical payloads to lunar orbit."]},{"key":"dc:description.degree","label":"Dc Description Degree","values":["Master of Science"]},{"key":"dc:title","label":"Title","values":["Lunar Robotic Precursor Missions Using Electric Propulsion"]}]}],"canonical_facts":{"dc:contributor.committeechair":["Wang, Joseph J."],"dc:contributor.committeemember":["Grossman, Bernard M.","Moses, Robert"],"dc:contributor.department":["Aerospace and Ocean Engineering"],"dc:creator":["Winski, Richard G."],"dc:date.accessioned":["2014-03-14T20:49:18Z"],"dc:date.available":["2014-03-14T20:49:18Z","2007-01-05"],"dc:date.issued":["2006-10-23"],"dc:description.abstract":["A trade study is carried out for the design of electric propulsion based lunar robotic precursor missions. The focus is to understand the relationships between payload mass delivered, electric propulsion power, and trip time. The results are compared against a baseline system using chemical propulsion with LOX/H2. The major differences between the chemical propulsion based and electric propulsion based systems are presented in terms of the payload mass and trip time. It is shown that solar electric propulsion offers significant advantage over chemical propulsion in delivering non-time critical payloads to lunar orbit."],"dc:description.degree":["Master of Science"],"dc:identifier.other":["etd-12112006-151141"],"dc:identifier.uri":["http://hdl.handle.net/10919/36063"],"dc:publisher":["Virginia Tech"],"dc:rights":["In Copyright"],"dc:rights.uri":["http://rightsstatements.org/vocab/InC/1.0/"],"dc:subject":["Lunar precursor","electric propulsion direct drive"],"dc:title":["Lunar Robotic Precursor Missions Using Electric Propulsion"],"dc:type":["Thesis"],"thesis:degree_discipline":["Aerospace and Ocean Engineering"],"thesis:degree_level":["masters"],"thesis:degree_name":["Master of Science"],"thesis:institution_name":["Virginia Polytechnic Institute and State University"]},"updated_at":"2026-07-22T22:19:15Z"}