A Single-Stage Reusable Launch Vehicle Concept
| dc.contributor.advisor | Lin, Kuen Y | en_US |
| dc.contributor.author | Yunusov, Abbos Muradovich | en_US |
| dc.date.accessioned | 2015-02-24T17:30:02Z | |
| dc.date.issued | 2015-02-24 | |
| dc.date.submitted | 2014 | en_US |
| dc.description | Thesis (Master's)--University of Washington, 2014 | en_US |
| dc.description.abstract | A 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.lift | 2016-02-24T17:30:02Z | |
| dc.embargo.terms | Restrict to UW for 1 year -- then make Open Access | en_US |
| dc.format.mimetype | application/pdf | en_US |
| dc.identifier.other | Yunusov_washington_0250O_14079.pdf | en_US |
| dc.identifier.uri | http://hdl.handle.net/1773/27386 | |
| dc.language.iso | en_US | en_US |
| dc.rights | Copyright is held by the individual authors. | en_US |
| dc.subject | Reusable launch vehicle; Single-stage to orbit; Space transportation | en_US |
| dc.subject.other | Aerospace engineering | en_US |
| dc.subject.other | aeronautics and astronautics | en_US |
| dc.title | A Single-Stage Reusable Launch Vehicle Concept | en_US |
| dc.type | Thesis | en_US |
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