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dc.contributor.authorRomano, Francesco
dc.contributor.authorHerdrichd, Georg H.
dc.contributor.authorBoxberger, Adam
dc.contributor.authorRodríguez Donaire, Silvia
dc.contributor.authorGarcía-Almiñana, Daniel
dc.contributor.authorSureda Anfres, Miquel
dc.contributor.otherUniversitat Politècnica de Catalunya. Departament d'Enginyeria de Projectes i de la Construcció
dc.contributor.otherUniversitat Politècnica de Catalunya. Departament de Física
dc.identifier.citationRomano, F. [et al.]. Advances on the Inductive Plasma Thruster Design for an Atmosphere-Breathing EP System. A: International Astronautical Congress. "69th International Astronautical Congress (IAC 2018): Bremen, Germany 1-5 October 2018". International Astronautical Federation, 2018, p. 10686-10691.
dc.description.abstractChallenging space mission scenarios include those in very low Earth orbits, where the atmosphere creates significant drag to the S/C and forces their orbit to an early decay. For drag compensation, propulsion systems are needed, requiring propellant to be carried on-board. An atmosphere-breathing electric propulsion system (ABEP) ingests the residual atmosphere through an intake and uses it as propellant for an electric thruster. Theoretically applicable to any planet with atmosphere, the system might allow drag compensation for an unlimited time without carrying propellant. A new range of altitudes for continuous operation would become accessible, enabling new scientific missions while reducing the required effort for the launcher by achieving these low orbits. Preliminary studies have shown that the collectible propellant flow for an ion thruster in low Earth orbit (LEO) might not be enough, and that electrode erosion due to aggressive gases, such as atomic oxygen, will limit the thruster’s lifetime. In this paper we present the advances on the design of an inductive plasma thruster (IPT) for the ABEP. The IPT is based on a small-scale inductively heated plasma generator IPG6-S. IPG have the advantage of being electrodeless, and have already shown high electric-tothermal coupling efficiencies using O2 and CO2 as propellant. IPG6-S requires a scaling of the discharge channel to meet with power requirement and expected collected mass flows, as well as optimisation of the accelerating stage, to provide the required thrust to the spacecraft. Tests have been performed to verify some of the parameters and are as well presented within this paper.
dc.format.extent6 p.
dc.publisherInternational Astronautical Federation
dc.subjectÀrees temàtiques de la UPC::Aeronàutica i espai::Sistemes de propulsió
dc.subject.lcshSpace vehicles -- Propulsion systems
dc.subject.lcshElectric propulsion
dc.subject.lcshPlasma (Ionized gases)
dc.titleAdvances on the Inductive Plasma Thruster Design for an Atmosphere-Breathing EP System
dc.typeConference report
dc.subject.lemacVehicles espacials -- Sistemes de propulsió
dc.subject.lemacPropulsió elèctrica
dc.subject.lemacPlasma (Gasos ionitzats)
dc.contributor.groupUniversitat Politècnica de Catalunya. TUAREG - Turbulence and Aerodynamics in Mechanical and Aerospace Engineering Research Group
dc.contributor.groupUniversitat Politècnica de Catalunya. L'AIRE - Laboratori Aeronàutic i Industrial de Recerca i Estudis
dc.description.peerreviewedPeer Reviewed
dc.rights.accessOpen Access
dc.description.versionPostprint (published version)
dc.relation.projectidinfo:eu-repo/grantAgreement/EC/H2020/737183/EU/DISCOVERER – DISruptive teChnOlogies for VERy low Earth oRbit platforms/DISCOVERER
local.citation.authorRomano, F.; Herdrichd, G.; Boxberger, A.; Rodriguez-Donaire, S.; Garcia-Almiñana, Daniel; Sureda, M.
local.citation.contributorInternational Astronautical Congress
local.citation.publicationName69th International Astronautical Congress (IAC 2018): Bremen, Germany 1-5 October 2018

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