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dc.contributor.authorRangedera, Thilinien_US
dc.contributor.authorVanmali, Ravien_US
dc.contributor.authorShah, Nileshen_US
dc.contributor.authorZaidi, Waqaren_US
dc.contributor.authorKomerath, Narayanan Menonen_US
dc.date.accessioned2006-02-02T21:25:46Zen_US
dc.date.accessioned2006-03-03T21:13:32Z
dc.date.available2006-02-02T21:25:46Zen_US
dc.date.available2006-03-03T21:13:32Z
dc.date.issued2005-11-10en_US
dc.identifier.urihttp://hdl.handle.net/1853/8047
dc.descriptionThis conference features the work of authors from: Georgia Tech’s Space Systems Design Lab, Aerospace Systems Design Lab, School of Aerospace Engineering, Georgia Tech Research Institute; NASA’s Jet Propulsion Laboratory, Marshall Space Flight Center, Goddard Space Flight Center, Langley Research Center; and other aerospace industry and academic institutionsen_US
dc.description.abstractThis paper is an offshoot of a project to study means of forming massive radiationshielded structures using Near Earth Object (NEO) materials. The topic is the conceptual design of a solar-powered robotic craft to land on, attach to, and extract materials from, a typical NEO. A solar-powered trajectory to a candidate NEO is used to estimate requirements. A reconfigurable solar sail / collector is the primary propulsion and power source for the craft. Following a journey of nearly 5 years, the craft will use a unique pulsed plasmajet torque-hammer concept to attach to the NEO. The basic cutting tool element is a solar-powered Neodymium fiber laser beam sheathed in a plasma jet, expanded through a truncated aerospike nozzle. Two telescoping, rotating arms carrying a total of 60 such nozzles at the ends of "fingers" enable the craft to dig and "float" out NEO material at a rate adequate to build a 50m diameter, 50m-long, 2m thick, walled cylinder within 19 days. The system is also amenable to applications requiring excavation of a large mass of near-surface material for resource processing. The present design appears to close with a total payload to LEO of 37,500 kg, with a total mass of 30,000 kg including the sail/collector at earth escape. The primary consumables on the system are the plasma gas for cutting and maneuvering, and electrodes of the plasma cutters.en_US
dc.description.sponsorshipAIAA Space Systems Technical Committee ; AIAA Space Transportation Systems Technical Committee ; Space Technology Advanced Research Centeren_US
dc.format.extent216899 bytesen_US
dc.format.extent1905 bytes
dc.format.extent216899 bytes
dc.format.mimetypeapplication/pdfen_US
dc.format.mimetypetext/plain
dc.format.mimetypeapplication/pdf
dc.language.isoen_USen_US
dc.publisherGeorgia Institute of Technologyen_US
dc.relation.ispartofseriesSSEC05. Session F;GT-SSEC.F.3en_US
dc.subjectNear Earth Objectsen_US
dc.subjectNEOen_US
dc.subjectSolar-powered robotic craften_US
dc.subjectReconfigurable solar sail and collectoren_US
dc.subjectSolar-powered propulsion and power sourcesen_US
dc.subjectNEO material excavationen_US
dc.subjectNeodymium fiber laser beamen_US
dc.subjectNEO resource processingen_US
dc.titleA Solar-Powered Near Earth Object Resource Extractoren_US
dc.typePresentationen_US
dc.contributor.corporatenameGeorgia Institute of Technology. Space Systems Design Laben_US
dc.contributor.corporatenameGeorgia Institute of Technology. School of Aerospace Engineeringen_US


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