Investigation of the Lox/Alcohol Propulsion System

Abstract:

This work describes the design of a liquid propellant rocket engine using non-toxic, low-cost propellants, for a second generation space transportation system. The primary goals of this effort were to identify the most attractive fuel and system design approach for sizing a workhorse engine and to determine technology advancements that are needed to provide subsequent system development. The emphasis of the analysis was directed toward propellant perfomance and engine characterization. On the basis of operational and cost criteria, ethanol was determined to be the best fuel candidate. Because of the high heat flux conditions at high chamber pressures, regenerative cooling was chosen as the preferred method of wall protection, leaving film cooling as a supplementary chamber cooling method. A finite element analysis was carried out to evaluate thrust chamber reliability on steady working operation and hydraulic test mode. The study contributed to establish a better understanding of propellant potentialities and to investigate the best means of utilizing these capabilities in typical engine designs.

• Periodical: Applied Mechanics and Materials (Volume 319)
• Pages: 427-432
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.319.427
• Online since: May 2013
• Authors: Bruno Barreto Vasques, Luiz Carlos Gadelha de Souza
• Keywords: Finite Element Analysis (FEA), Green Propellants, Liquid Propulsion

References

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DOI: 10.1017/s0001924000049770

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