Mass Driver Design Traveling Earth to the Moon

dc.authorscopusid 6507947540
dc.contributor.author Inger, Erk
dc.contributor.author Inger, Erk
dc.contributor.other Airframe and Powerplant Maintenance
dc.date.accessioned 2024-07-05T15:27:57Z
dc.date.available 2024-07-05T15:27:57Z
dc.date.issued 2019
dc.department Atılım University en_US
dc.department-temp [Inger, Erk] Atilim Univ, Airframe & Powerplant Maintenance Dept, TR-06830 Ankara, Turkey en_US
dc.description.abstract In this article, the flight of a mass driver was designed for launch from the Earth with Electro Magnetic Space Launching System (EMSLS). Then the orbit exit from the Earth at 185 km and orbit entry the Moon at 100kmwere examined with respect to change of trajectories by using chemical fuel and the engine in the mass driver. Electromagnetically launched mass drivers should orbit with a specified orbital velocity at a designated altitude. In this paper, the energy is transferred externally to a mass driver throughout the flight path the electromagnetic coil system called multistage (EMSLS) designated in order to achieve the specified orbital velocity. The mass driver is synchronously accelerated by a voltage through the capacitors which are used for storing energy. This energy is transferred through a switching inductor to the circuit of the mass driver so that the mass driver is launched into the orbit with a muzzle velocity. However, this fact creates high air drag energy losses due to atmospheric conditions and high velocity obtained in EMSLS. Thus, in the mass driver at 21km altitude an engine starts to increase the velocity of the system to reach orbital velocity. The final aim of this article is to capture the transfer of $\Delta \text{v}$ cost for traveling to the Moon. At any given arrival time in order to guide the system, designers only consider the gravity of the Earth and gravity of the Moon by using a Direct Lunar Transfer Trajectory for the Earth to the Moon approach. Finally, EMSLS was evaluated as a more advantageous and complimentary alternative to chemical propulsion systems for space transportation. en_US
dc.identifier.citationcount 1
dc.identifier.doi 10.1109/ACCESS.2019.2950882
dc.identifier.endpage 161039 en_US
dc.identifier.issn 2169-3536
dc.identifier.scopus 2-s2.0-85078008068
dc.identifier.scopusquality Q1
dc.identifier.startpage 161034 en_US
dc.identifier.uri https://doi.org/10.1109/ACCESS.2019.2950882
dc.identifier.uri https://hdl.handle.net/20.500.14411/2740
dc.identifier.volume 7 en_US
dc.identifier.wos WOS:000497167600166
dc.identifier.wosquality Q2
dc.institutionauthor İnger, Erk
dc.language.iso en en_US
dc.publisher Ieee-inst Electrical Electronics Engineers inc en_US
dc.relation.publicationcategory Makale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanı en_US
dc.rights info:eu-repo/semantics/openAccess en_US
dc.scopus.citedbyCount 1
dc.subject Moon en_US
dc.subject Earth en_US
dc.subject Space vehicles en_US
dc.subject Planetary orbits en_US
dc.subject Fuels en_US
dc.subject Trajectory en_US
dc.subject Mass driver en_US
dc.subject electro magnetic space launching system (EMSLS) en_US
dc.subject muzzle velocity en_US
dc.subject lunar transfer trajectory from earth en_US
dc.subject useful payload en_US
dc.subject Delta V cost en_US
dc.subject perigee en_US
dc.subject apogee en_US
dc.title Mass Driver Design Traveling Earth to the Moon en_US
dc.type Article en_US
dc.wos.citedbyCount 1
dspace.entity.type Publication
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relation.isOrgUnitOfPublication.latestForDiscovery 0ad0b148-c2aa-44e7-8f0a-53ab5c8406d5

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