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dc.contributor.authorGegeoglu, K.
dc.contributor.authorKahraman, M.
dc.contributor.authorÜçler, Çağlar
dc.contributor.authorKarabeyoglu, A.
dc.date.accessioned2020-10-22T09:16:16Z
dc.date.available2020-10-22T09:16:16Z
dc.date.issued2019
dc.identifier.isbn978-162410590-6
dc.identifier.urihttp://hdl.handle.net/10679/7038
dc.identifier.urihttps://arc.aiaa.org/doi/10.2514/6.2019-4124
dc.description.abstractIn small hybrid rockets, liquid oxidizer is fed into the combustion chamber by pressurizing the oxidizer tank to achieve the desired injector pressure. However, larger applications employ propellant pumps to keep the propellant tank mass at reasonable levels. Conventionally, pumps are implemented on rockets by means of turbopumps. However, turbopumps are complex systems with serious development time and costs. With the current advancements in batteries and electrical machinery, pumps driven by electric motors become viable actors. In the case of hybrid rockets, operation of a single liquid propellant with a single pump has significant advantages compared to their use in the bipropellant liquid engines. In this paper, an example case of an upper stage hybrid rocket system is introduced and a propellant pump is designed using CFD modeling. The advantage of using electric motor driven pumps has been established via weight analysis and a comparison between alternative feed systems. Turbopump system is not considered due to its complexity as an alternative system. Therefore, comparison is limited to the cold gas pressurization feed system. It has been shown that a significant advantage in total feed system weight is achieved not only with a high-head pump but also with a low-head pump with assistive pressurization. A 69.9 % mass reduction for double-stage pump system and a 45.2 % mass reduction for the single-stage pump system was calculated compared to the reference pressure-fed system.en_US
dc.language.isoengen_US
dc.publisherAmerican Institute of Aeronautics and Astronautics Inc, AIAAen_US
dc.relation.ispartofAIAA Propulsion and Energy Forum and Exposition
dc.rightsrestrictedAccess
dc.titleAssessment of using electric pumps on hybrid rocketsen_US
dc.typeConference paperen_US
dc.publicationstatusPublisheden_US
dc.contributor.departmentÖzyeğin University
dc.contributor.authorID(ORCID 0000-0003-4209-7915 & YÖK ID 32713) Üçler, Çağlar
dc.contributor.ozuauthorÜçler, Çağlar
dc.identifier.doi10.2514/6.2019-4124en_US
dc.identifier.scopusSCOPUS:2-s2.0-85084100906
dc.contributor.authorMale1
dc.relation.publicationcategoryConference Paper - International - Institution Academic Staff


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