A Single-Stage Reusable Launch Vehicle Concept

dc.contributor.advisorLin, Kuen Yen_US
dc.contributor.authorYunusov, Abbos Muradovichen_US
dc.date.accessioned2015-02-24T17:30:02Z
dc.date.issued2015-02-24
dc.date.submitted2014en_US
dc.descriptionThesis (Master's)--University of Washington, 2014en_US
dc.description.abstractA reusable VTVL (vertical take-off, vertical landing), all-rocket SSTO (single-stage-to-orbit) launch vehicle is proposed to reduce the cost of space transportation. The concept vehicle is based on presently-existing or near-term technology, and incorporates several features to improve performance, including all-composite construction, lightweight pressure-stabilized tankage, and the use of a HIAD (hypersonic inflatable aerodynamic decelerator) - an inflatable heatshield - to return from orbit. Several different types of main engines, consuming various fuels, are considered. An ad-hoc MATLAB code is used to predict the empty mass of the vehicle, quantify the sensitivity of the design to empty mass growth, and the system life-cycle cost. A vehicle powered by tripropellant engines based on RD-701/RD-704 technology consuming liquid oxygen and liquid hydrogen and methane fuels is identified as the best performer.en_US
dc.embargo.lift2016-02-24T17:30:02Z
dc.embargo.termsRestrict to UW for 1 year -- then make Open Accessen_US
dc.format.mimetypeapplication/pdfen_US
dc.identifier.otherYunusov_washington_0250O_14079.pdfen_US
dc.identifier.urihttp://hdl.handle.net/1773/27386
dc.language.isoen_USen_US
dc.rightsCopyright is held by the individual authors.en_US
dc.subjectReusable launch vehicle; Single-stage to orbit; Space transportationen_US
dc.subject.otherAerospace engineeringen_US
dc.subject.otheraeronautics and astronauticsen_US
dc.titleA Single-Stage Reusable Launch Vehicle Concepten_US
dc.typeThesisen_US

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