Effect of aerodynamics on the perturbations of a space vehicle orbit

dc.contributor.authorMayo, Alton Parkeren
dc.contributor.departmentAeronautical Engineeringen
dc.date.accessioned2022-06-29T19:26:41Zen
dc.date.available2022-06-29T19:26:41Zen
dc.date.issued1961en
dc.description.abstractThe present study was undertaken to determine the effects of the aerodynamics on a close earth orbit and reentry trajectory. The aerodynamic influence is compared to the effects of the earth’s oblateness, the sun, and the moon. In order to obtain maximum accuracy and computational speed Encke’s perturbative procedures were used during orbital periods and Cowell’s integration procedures during thrust and reentry periods.en
dc.description.degreeM.S.en
dc.format.extent64 pages, 2 unnumbered leavesen
dc.format.mimetypeapplication/pdfen
dc.identifier.urihttp://hdl.handle.net/10919/110993en
dc.language.isoenen
dc.publisherVirginia Polytechnic Instituteen
dc.relation.isformatofOCLC# 07233527en
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subject.lccLD5655.V855 1961.M39en
dc.subject.lcshDrag (Aerodynamics)en
dc.subject.lcshPerturbation (Mathematics)en
dc.subject.lcshSpace vehicles -- Atmospheric entryen
dc.titleEffect of aerodynamics on the perturbations of a space vehicle orbiten
dc.typeThesisen
dc.type.dcmitypeTexten
thesis.degree.disciplineAeronautical Engineeringen
thesis.degree.grantorVirginia Polytechnic Instituteen
thesis.degree.levelmastersen
thesis.degree.nameM.S.en

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