Conceptual Design and Optimization of Hybrid Rockets
| dc.contributor.advisor | Johansen, Craig T. | |
| dc.contributor.author | Messinger, Troy Leonard | |
| dc.contributor.committeemember | Wood, David H. | |
| dc.contributor.committeemember | Greatrix, David R. | |
| dc.date | 2021-06 | |
| dc.date.accessioned | 2021-01-25T22:19:27Z | |
| dc.date.available | 2021-01-25T22:19:27Z | |
| dc.date.issued | 2021-01-14 | |
| dc.description.abstract | A framework was developed to perform conceptual multi-disciplinary design parametric and optimization studies of single-stage sub-orbital flight vehicles, and two-stage-to-orbit flight vehicles, that employ hybrid rocket engines as the principal means of propulsion. The framework was written in the Python programming language and incorporates many sub-disciplines to generate vehicle designs, model the relevant physics, and analyze flight performance. The relative performance (payload fraction capability) of different vehicle masses and feed system/propellant configurations was found. The major findings include conceptually viable pressure-fed and electric pump-fed two-stage-to-orbit configurations taking advantage of relatively low combustion pressures in increasing overall performance. The smallest launch vehicles assessed had lower payload fractions compared to larger vehicles. The vehicle configurations resulting in the highest performance used liquid oxygen and paraffin wax propellants. The smallest viable orbital launch vehicle, the vehicle with the highest payload fraction for the smallest payload considered, was a liquid oxygen and paraffin-wax-based launcher. The highest payload fraction found for the smallest payload class was 0.60 % of gross mass for a 10 kg payload delivered to 500 km Sun-synchronous orbit. The highest payload fraction for the investigated 150 kg payload class for the same Sun-synchronous orbit was found to be 1.2 %. | en_US |
| dc.identifier.citation | Messinger, T. L. (2021). Conceptual Design and Optimization of Hybrid Rockets (Master's thesis, University of Calgary, Calgary, Canada). Retrieved from https://prism.ucalgary.ca. | en_US |
| dc.identifier.doi | http://dx.doi.org/10.11575/PRISM/38579 | |
| dc.identifier.uri | http://hdl.handle.net/1880/113011 | |
| dc.publisher.faculty | Schulich School of Engineering | en_US |
| dc.publisher.institution | University of Calgary | en |
| dc.rights | University of Calgary graduate students retain copyright ownership and moral rights for their thesis. You may use this material in any way that is permitted by the Copyright Act or through licensing that has been assigned to the document. For uses that are not allowable under copyright legislation or licensing, you are required to seek permission. | en_US |
| dc.subject.classification | Engineering | en_US |
| dc.title | Conceptual Design and Optimization of Hybrid Rockets | en_US |
| dc.type | master thesis | en_US |
| thesis.degree.discipline | Engineering – Mechanical & Manufacturing | en_US |
| thesis.degree.grantor | University of Calgary | en_US |
| thesis.degree.name | Master of Science (MSc) | en_US |
| ucalgary.item.requestcopy | true | en_US |