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Georgia Tech's Institutional Repository >
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Space Systems Engineering Conference >
Space Systems Engineering Conference (1st - Atlanta - 2005) >
SSEC05. Session F: University Session II >
Please use this identifier to cite or link to this item:
http://hdl.handle.net/1853/8047
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| Title: | A Solar-Powered Near Earth Object Resource Extractor |
| Authors: | Rangedera, Thilini Vanmali, Ravi Shah, Nilesh Zaidi, Waqar Komerath, Narayanan Menon Georgia Institute of Technology. Space Systems Design Lab Georgia Institute of Technology. School of Aerospace Engineering |
| Subjects : | Near Earth Objects NEO Solar-powered robotic craft Reconfigurable solar sail and collector Solar-powered propulsion and power sources NEO material excavation Neodymium fiber laser beam NEO resource processing |
| Issue Date: | 10-Nov-2005 |
| Publisher: | Georgia Institute of Technology |
| Series/Report no.: | SSEC05. Session F;GT-SSEC.F.3 |
| Abstract: | This 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. |
| Description: | This 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 institutions |
| Type: | Presentation |
| URI: | http://hdl.handle.net/1853/8047 |
| Appears in Collections: | SSEC05. Session F: University Session II Space Systems Engineering Conference (1st - Atlanta - 2005)
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