{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/101103"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/101103","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"Aerodynamic stability analysis of a CubeSat in high-speed rarefied flow","abstract":"Small satellites, such as CubeSats and SmallSats, are seeing increased use in Low Earth Orbit, particularly at altitudes with measurable aerodynamic effects. It is important to design these spacecraft, which often have modest control authority, such that the resultant aerodynamic forces and moments do not cause unstable motion, which may lead to premature loss of mission. Building from free molecular pressure and shear equations for flat plates, an aerodynamic solver is designed to analyze the aerodynamic forces and moments on a 3U CubeSat with center of gravity offset, orbiting at altitudes from 80 to 200 km. The motion of this CubeSat is then simulated for a variety of initial conditions, both with and without active control, to determine its behavior. Inferences are made as to design rules that will lead to more stable small satellites.","abstract_html":"Small satellites, such as CubeSats and SmallSats, are seeing increased use in Low Earth Orbit, particularly at altitudes with measurable aerodynamic effects. It is important to design these spacecraft, which often have modest control authority, such that the resultant aerodynamic forces and moments do not cause unstable motion, which may lead to premature loss of mission. Building from free molecular pressure and shear equations for flat plates, an aerodynamic solver is designed to analyze the aerodynamic forces and moments on a 3U CubeSat with center of gravity offset, orbiting at altitudes from 80 to 200 km. The motion of this CubeSat is then simulated for a variety of initial conditions, both with and without active control, to determine its behavior. Inferences are made as to design rules that will lead to more stable small satellites.","abstract_has_math":false,"creators":["Williams, James Warren"],"institution":"University of Illinois at Urbana-Champaign","degree_name":"M.S.","degree_level":"Thesis","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["Putnam, Zachary R."],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2018,"date_issued":"2018-09-04T20:32:05Z","date_published":"2018-09-04T20:32:05Z","updated_at":"2026-07-22T22:24:38Z","subjects":["Stability CubeSat SmallSat Rarefied High Speed"],"languages":["en"],"rights":["Copyright 2018 James Williams"],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/2142/101103","outbound_label":"Handle","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Putnam, Zachary R."]},{"key":"dc:creator","label":"Author","values":["Williams, James Warren"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2018-09-04T20:32:05Z","2018-04-27","2018-05"]},{"key":"dc:type","label":"Dc Type","values":["text"]},{"key":"thesis:degree_discipline","label":"Discipline","values":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Thesis"]},{"key":"thesis:degree_name","label":"Degree Name","values":["M.S."]},{"key":"thesis:institution_name","label":"Thesis Institution Name","values":["University of Illinois at Urbana-Champaign"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["Stability CubeSat SmallSat Rarefied High Speed"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["en"]},{"key":"dc:rights","label":"Dc Rights","values":["Copyright 2018 James Williams"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["http://hdl.handle.net/2142/101103"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["Small satellites, such as CubeSats and SmallSats, are seeing increased use in Low Earth Orbit, particularly at altitudes with measurable aerodynamic effects. It is important to design these spacecraft, which often have modest control authority, such that the resultant aerodynamic forces and moments do not cause unstable motion, which may lead to premature loss of mission. Building from free molecular pressure and shear equations for flat plates, an aerodynamic solver is designed to analyze the aerodynamic forces and moments on a 3U CubeSat with center of gravity offset, orbiting at altitudes from 80 to 200 km. The motion of this CubeSat is then simulated for a variety of initial conditions, both with and without active control, to determine its behavior. Inferences are made as to design rules that will lead to more stable small satellites.","Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2018-08-31 without embargo terms","The student, James Williams, accepted the attached license on 2018-04-27 at 14:24.","The student, James Williams, submitted this Thesis for approval on 2018-04-27 at 14:34.","This Thesis was approved for publication on 2018-04-27 at 15:17.","DSpace SAF Submission Ingestion Package generated from Vireo submission #12544 on 2018-08-31 at 17:15:18","Made available in DSpace on 2018-09-04T20:32:05Z (GMT). No. of bitstreams: 2 WILLIAMS-THESIS-2018.pdf: 970260 bytes, checksum: 3e9df35e0532d9ee12f4c2332efd3b5c (MD5) LICENSE.txt: 4211 bytes, checksum: 67367c87604d1ca3ff7e121e0352b183 (MD5) Previous issue date: 2018-04-27"]},{"key":"dc:format","label":"Dc Format","values":["application/pdf"]},{"key":"dc:title","label":"Title","values":["Aerodynamic stability analysis of a CubeSat in high-speed rarefied flow"]}]}],"canonical_facts":{"dc:contributor":["Putnam, Zachary R."],"dc:creator":["Williams, James Warren"],"dc:date":["2018-09-04T20:32:05Z","2018-04-27","2018-05"],"dc:description":["Small satellites, such as CubeSats and SmallSats, are seeing increased use in Low Earth Orbit, particularly at altitudes with measurable aerodynamic effects. It is important to design these spacecraft, which often have modest control authority, such that the resultant aerodynamic forces and moments do not cause unstable motion, which may lead to premature loss of mission. Building from free molecular pressure and shear equations for flat plates, an aerodynamic solver is designed to analyze the aerodynamic forces and moments on a 3U CubeSat with center of gravity offset, orbiting at altitudes from 80 to 200 km. The motion of this CubeSat is then simulated for a variety of initial conditions, both with and without active control, to determine its behavior. Inferences are made as to design rules that will lead to more stable small satellites.","Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2018-08-31 without embargo terms","The student, James Williams, accepted the attached license on 2018-04-27 at 14:24.","The student, James Williams, submitted this Thesis for approval on 2018-04-27 at 14:34.","This Thesis was approved for publication on 2018-04-27 at 15:17.","DSpace SAF Submission Ingestion Package generated from Vireo submission #12544 on 2018-08-31 at 17:15:18","Made available in DSpace on 2018-09-04T20:32:05Z (GMT). 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