Full Text Available
Note: Clicking the button above will open the full text document at the original institutional repository in a new window.
Preliminary design of a 1 kN liquid propellant rocket engine testing platform
This work presents a preliminary design of a liquid rocket engine test platform to support research into liquid propulsion systems and rocket engine components, including injectors, ignition systems, combustion chambers and engine cooling systems. The liquid propellants, specifically liquid oxygen a...
Saved in:
| Main Author: | |
|---|---|
| Other Authors: | |
| Format: | Thesis |
| Language: | English |
| Published: |
Department of Electrical Engineering
2022
|
| Subjects: | |
| Tags: |
No Tags, Be the first to tag this record!
|
| _version_ | 1867613145991741440 |
|---|---|
| access_status_str | Open Access |
| author | Ringas, Nicolas Donovan |
| author2 | Martinez, Peter |
| author_browse | Martinez, Peter Ringas, Nicolas Donovan |
| author_facet | Martinez, Peter Ringas, Nicolas Donovan |
| author_sort | Ringas, Nicolas Donovan |
| collection | Thesis |
| description | This work presents a preliminary design of a liquid rocket engine test platform to support research into liquid propulsion systems and rocket engine components, including injectors, ignition systems, combustion chambers and engine cooling systems. The liquid propellants, specifically liquid oxygen and ethanol, are pressure-fed using gaseous nitrogen. The test platform supports engine thrust values up to 1 kN, as well as varying oxidizer/fuel ratios up to 4.0 and varying ethanol concentrations between 70 and 100%. The test platform will integrate with a mobile control centre, which was designed concurrently, and provides remote control of the test procedures and data acquisition of all relevant pressure, temperature, mass flow and thrust data. The propellant feed assembly can support both cold and hot fire testing campaigns and is equipped with numerous safety features including inert gas purge lines, emergency drain lines and emergency shut-down and de-pressurization procedures. |
| format | Thesis |
| id | oai:open.uct.ac.za:11427/36544 |
| institution | University of Cape Town (South Africa) |
| language | eng |
| last_indexed | 2026-06-10T12:31:30.019Z |
| license_str | Not specified — see source repository |
| provenance_str_mv | Harvested via OAI-PMH from UCTD — University of Cape Town Open Access Repository |
| publishDate | 2022 |
| publishDateRange | 2022 |
| publishDateSort | 2022 |
| publisher | Department of Electrical Engineering |
| publisherStr | Department of Electrical Engineering |
| record_format | dspace |
| source_str | UCTD — University of Cape Town Open Access Repository |
| spelling | oai:open.uct.ac.za:11427/36544 Preliminary design of a 1 kN liquid propellant rocket engine testing platform Ringas, Nicolas Donovan Martinez, Peter liquid rocket engines liquid propulsion test platform LOX/ethanol This work presents a preliminary design of a liquid rocket engine test platform to support research into liquid propulsion systems and rocket engine components, including injectors, ignition systems, combustion chambers and engine cooling systems. The liquid propellants, specifically liquid oxygen and ethanol, are pressure-fed using gaseous nitrogen. The test platform supports engine thrust values up to 1 kN, as well as varying oxidizer/fuel ratios up to 4.0 and varying ethanol concentrations between 70 and 100%. The test platform will integrate with a mobile control centre, which was designed concurrently, and provides remote control of the test procedures and data acquisition of all relevant pressure, temperature, mass flow and thrust data. The propellant feed assembly can support both cold and hot fire testing campaigns and is equipped with numerous safety features including inert gas purge lines, emergency drain lines and emergency shut-down and de-pressurization procedures. 2022-06-27T20:21:04Z 2022-06-27T20:21:04Z 2022 2022-06-27T18:08:25Z Master Thesis Masters MPhil http://hdl.handle.net/11427/36544 eng application/pdf Department of Electrical Engineering Faculty of Engineering and the Built Environment |
| spellingShingle | liquid rocket engines liquid propulsion test platform LOX/ethanol Ringas, Nicolas Donovan Preliminary design of a 1 kN liquid propellant rocket engine testing platform |
| thesis_degree_str | Master's |
| title | Preliminary design of a 1 kN liquid propellant rocket engine testing platform |
| title_full | Preliminary design of a 1 kN liquid propellant rocket engine testing platform |
| title_fullStr | Preliminary design of a 1 kN liquid propellant rocket engine testing platform |
| title_full_unstemmed | Preliminary design of a 1 kN liquid propellant rocket engine testing platform |
| title_short | Preliminary design of a 1 kN liquid propellant rocket engine testing platform |
| title_sort | preliminary design of a 1 kn liquid propellant rocket engine testing platform |
| topic | liquid rocket engines liquid propulsion test platform LOX/ethanol |
| url | http://hdl.handle.net/11427/36544 |
| work_keys_str_mv | AT ringasnicolasdonovan preliminarydesignofa1knliquidpropellantrocketenginetestingplatform |