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 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.

Grantor

Department of Electrical Engineering

Year dc:date.issued

2022

Author dc:creator

• Ringas, Nicolas Donovan

Advisor dc:contributor.advisor

• Martinez, Peter

• liquid rocket engines
• liquid propulsion
• test platform
• LOX/ethanol

Handle dc:identifier.uri

http://hdl.handle.net/11427/36544

OAI identifier oai:identifier

oai:open.uct.ac.za:11427/36544