{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/110747"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/110747","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"Computational and experimental analysis of HIIPER MPD propulsion system","abstract":"Helicon Injected Inertial Plasma Electrostatic Rocket (HIIPER) is a deep space electric propulsion system developed on the principles of inertial electrostatic confinement (IEC) fusion and helicon plasma injection. It is a stepping stone towards a variable impulse pulsed fusion rocket. HIIPER involves a three-stage mechanism for propulsion – high-density ion generation in a helicon tube, extraction of these ions inside the fusion chamber using IEC cathode grids and finally expelling the plasma out of the system through a magnetic nozzle (MN). Currently, the first two stages are being studied experimentally and the third stage is in the design phase. Prior research has established HIIPER as an innovative concept for space propulsion with numerous advantages, some of them as follows – compatible with many propellants, high-density plasma plume and electrically neutral exhaust. The shortcomings of HIIPER, low thrust values recorded in the past, are a result of ion-wall collisions inside the helicon-IEC coupling. A possible solution to the low thrust problem is investigated for this thesis and future experiments will involve using it to rectify the issue and revaluating the performance of HIIPER. This study also involves validation of a numerical model of HIIPER using experimental results and computationally proving the advantages of a MN integrated with HIIPER. The model was then used to extrapolate the performance trends to optimize HIIPER and lay the foundation for future experimental work.","abstract_html":"Helicon Injected Inertial Plasma Electrostatic Rocket (HIIPER) is a deep space electric propulsion system developed on the principles of inertial electrostatic confinement (IEC) fusion and helicon plasma injection. It is a stepping stone towards a variable impulse pulsed fusion rocket. HIIPER involves a three-stage mechanism for propulsion – high-density ion generation in a helicon tube, extraction of these ions inside the fusion chamber using IEC cathode grids and finally expelling the plasma out of the system through a magnetic nozzle (MN). Currently, the first two stages are being studied experimentally and the third stage is in the design phase. Prior research has established HIIPER as an innovative concept for space propulsion with numerous advantages, some of them as follows – compatible with many propellants, high-density plasma plume and electrically neutral exhaust. The shortcomings of HIIPER, low thrust values recorded in the past, are a result of ion-wall collisions inside the helicon-IEC coupling. A possible solution to the low thrust problem is investigated for this thesis and future experiments will involve using it to rectify the issue and revaluating the performance of HIIPER. This study also involves validation of a numerical model of HIIPER using experimental results and computationally proving the advantages of a MN integrated with HIIPER. The model was then used to extrapolate the performance trends to optimize HIIPER and lay the foundation for future experimental work.","abstract_has_math":false,"creators":["Puri, Rohan"],"institution":"University of Illinois at Urbana-Champaign","degree_name":"M.S.","degree_level":"Thesis","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["Miley, George H."],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2021,"date_issued":"2021-09-17T02:34:49Z","date_published":"2021-09-17T02:34:49Z","updated_at":"2026-07-22T22:24:52Z","subjects":["Space Propulsion","Electric Propulsion","Helicon Thruster","HIIPER"],"languages":["en"],"rights":["Copyright 2021 Rohan Puri"],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/2142/110747","outbound_label":"Handle","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Miley, George H."]},{"key":"dc:creator","label":"Author","values":["Puri, Rohan"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2021-09-17T02:34:49Z","2023-09-17T02:34:57Z","2021-04-28","2021-05"]},{"key":"dc:type","label":"Dc Type","values":["text","Thesis"]},{"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":["Space Propulsion","Electric Propulsion","Helicon Thruster","HIIPER"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["en"]},{"key":"dc:rights","label":"Dc Rights","values":["Copyright 2021 Rohan Puri"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["http://hdl.handle.net/2142/110747"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["Helicon Injected Inertial Plasma Electrostatic Rocket (HIIPER) is a deep space electric propulsion system developed on the principles of inertial electrostatic confinement (IEC) fusion and helicon plasma injection. It is a stepping stone towards a variable impulse pulsed fusion rocket. HIIPER involves a three-stage mechanism for propulsion – high-density ion generation in a helicon tube, extraction of these ions inside the fusion chamber using IEC cathode grids and finally expelling the plasma out of the system through a magnetic nozzle (MN). Currently, the first two stages are being studied experimentally and the third stage is in the design phase. Prior research has established HIIPER as an innovative concept for space propulsion with numerous advantages, some of them as follows – compatible with many propellants, high-density plasma plume and electrically neutral exhaust. The shortcomings of HIIPER, low thrust values recorded in the past, are a result of ion-wall collisions inside the helicon-IEC coupling. A possible solution to the low thrust problem is investigated for this thesis and future experiments will involve using it to rectify the issue and revaluating the performance of HIIPER. This study also involves validation of a numerical model of HIIPER using experimental results and computationally proving the advantages of a MN integrated with HIIPER. The model was then used to extrapolate the performance trends to optimize HIIPER and lay the foundation for future experimental work.","Submission published under a 24 month embargo labeled 'U of I Access', the embargo will last until 2023-05-01","The student, Rohan Puri, accepted the attached license on 2021-04-27 at 12:38.","The student, Rohan Puri, submitted this Thesis for approval on 2021-04-27 at 15:13.","This Thesis was approved for publication on 2021-04-28 at 14:46.","DSpace SAF Submission Ingestion Package generated from Vireo submission #16583 on 2021-09-16 at 17:06:06","Made available in DSpace on 2021-09-17T02:34:49Z (GMT). No. of bitstreams: 2 PURI-THESIS-2021.pdf: 2760170 bytes, checksum: 094bfbc9095efb89411fb71703e02c2b (MD5) LICENSE.txt: 4207 bytes, checksum: 444c3ba650df3320147011a26a6e47d9 (MD5) Previous issue date: 2021-04-28","Embargo set by: Seth Robbins for item 118590 Lift date: 2023-09-17T02:34:57Z Reason: Author requested U of Illinois access only (OA after 2yrs) in Vireo ETD system","Author requested U of Illinois access only (OA after 2yrs) in Vireo ETD system","U of I Only"]},{"key":"dc:format","label":"Dc Format","values":["application/pdf"]},{"key":"dc:title","label":"Title","values":["Computational and experimental analysis of HIIPER MPD propulsion system"]}]}],"canonical_facts":{"dc:contributor":["Miley, George H."],"dc:creator":["Puri, Rohan"],"dc:date":["2021-09-17T02:34:49Z","2023-09-17T02:34:57Z","2021-04-28","2021-05"],"dc:description":["Helicon Injected Inertial Plasma Electrostatic Rocket (HIIPER) is a deep space electric propulsion system developed on the principles of inertial electrostatic confinement (IEC) fusion and helicon plasma injection. It is a stepping stone towards a variable impulse pulsed fusion rocket. HIIPER involves a three-stage mechanism for propulsion – high-density ion generation in a helicon tube, extraction of these ions inside the fusion chamber using IEC cathode grids and finally expelling the plasma out of the system through a magnetic nozzle (MN). Currently, the first two stages are being studied experimentally and the third stage is in the design phase. Prior research has established HIIPER as an innovative concept for space propulsion with numerous advantages, some of them as follows – compatible with many propellants, high-density plasma plume and electrically neutral exhaust. The shortcomings of HIIPER, low thrust values recorded in the past, are a result of ion-wall collisions inside the helicon-IEC coupling. A possible solution to the low thrust problem is investigated for this thesis and future experiments will involve using it to rectify the issue and revaluating the performance of HIIPER. This study also involves validation of a numerical model of HIIPER using experimental results and computationally proving the advantages of a MN integrated with HIIPER. The model was then used to extrapolate the performance trends to optimize HIIPER and lay the foundation for future experimental work.","Submission published under a 24 month embargo labeled 'U of I Access', the embargo will last until 2023-05-01","The student, Rohan Puri, accepted the attached license on 2021-04-27 at 12:38.","The student, Rohan Puri, submitted this Thesis for approval on 2021-04-27 at 15:13.","This Thesis was approved for publication on 2021-04-28 at 14:46.","DSpace SAF Submission Ingestion Package generated from Vireo submission #16583 on 2021-09-16 at 17:06:06","Made available in DSpace on 2021-09-17T02:34:49Z (GMT). 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