Using concentrated solar radiation to process orbital debris in low earth orbit

Persistent Link:
http://hdl.handle.net/10150/282829
Title:
Using concentrated solar radiation to process orbital debris in low earth orbit
Author:
Babin, Bruce Russell, 1966-
Issue Date:
1998
Publisher:
The University of Arizona.
Rights:
Copyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction or presentation (such as public display or performance) of protected items is prohibited except with permission of the author.
Abstract:
Orbital debris is a growing concern for all space applications. Specifically, the ASPOD concept has been proposed to help eliminate the debris population. This dissertation focuses on the characterization and feasibility of processing (cutting) structural metals in low earth orbit using concentrated solar energy as they pertain to the ASPOD concept. In characterizing the process, both experimental and analytical techniques were utilized. Analytically, a non-linear explicit finite difference model was created that examined how the heat transfer and physical parameters affect metal processing in low earth orbit. In addition, the model was used to develop a thermal criterion under which processing of aluminum debris can be accomplished with concentrated solar radiation. The experimental investigation entailed designing and constructing two experimental apparatuses. The first experimental apparatus was utilized to demonstrate the control of radiative surface properties on simulated orbital debris and to allow for the conceptual testing of physical parameters. The second experimental apparatus was constructed to demonstrate the entire cutting process. The feasibility of cutting structural members in low earth orbit with concentrated solar is discussed and demonstrated. Finally, the effect of these results on the ASPOD concept and threat of orbital debris is addressed.
Type:
text; Dissertation-Reproduction (electronic)
Keywords:
Engineering, Aerospace.; Engineering, Mechanical.
Degree Name:
Ph.D.
Degree Level:
doctoral
Degree Program:
Graduate College; Aeorspace and Mechanical Engineering
Degree Grantor:
University of Arizona
Advisor:
Ramohalli, Kumar

Full metadata record

DC FieldValue Language
dc.language.isoen_USen_US
dc.titleUsing concentrated solar radiation to process orbital debris in low earth orbiten_US
dc.creatorBabin, Bruce Russell, 1966-en_US
dc.contributor.authorBabin, Bruce Russell, 1966-en_US
dc.date.issued1998en_US
dc.publisherThe University of Arizona.en_US
dc.rightsCopyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction or presentation (such as public display or performance) of protected items is prohibited except with permission of the author.en_US
dc.description.abstractOrbital debris is a growing concern for all space applications. Specifically, the ASPOD concept has been proposed to help eliminate the debris population. This dissertation focuses on the characterization and feasibility of processing (cutting) structural metals in low earth orbit using concentrated solar energy as they pertain to the ASPOD concept. In characterizing the process, both experimental and analytical techniques were utilized. Analytically, a non-linear explicit finite difference model was created that examined how the heat transfer and physical parameters affect metal processing in low earth orbit. In addition, the model was used to develop a thermal criterion under which processing of aluminum debris can be accomplished with concentrated solar radiation. The experimental investigation entailed designing and constructing two experimental apparatuses. The first experimental apparatus was utilized to demonstrate the control of radiative surface properties on simulated orbital debris and to allow for the conceptual testing of physical parameters. The second experimental apparatus was constructed to demonstrate the entire cutting process. The feasibility of cutting structural members in low earth orbit with concentrated solar is discussed and demonstrated. Finally, the effect of these results on the ASPOD concept and threat of orbital debris is addressed.en_US
dc.typetexten_US
dc.typeDissertation-Reproduction (electronic)en_US
dc.subjectEngineering, Aerospace.en_US
dc.subjectEngineering, Mechanical.en_US
thesis.degree.namePh.D.en_US
thesis.degree.leveldoctoralen_US
thesis.degree.disciplineGraduate Collegeen_US
thesis.degree.disciplineAeorspace and Mechanical Engineeringen_US
thesis.degree.grantorUniversity of Arizonaen_US
dc.contributor.advisorRamohalli, Kumaren_US
dc.identifier.proquest9912136en_US
dc.identifier.bibrecord.b39124381en_US
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