Design and test firing of a dual bidirectional double vortex bipropellant rocket engine

Augousti, A T., Baker, A and Marlow, J-J (2018) Design and test firing of a dual bidirectional double vortex bipropellant rocket engine. Journal of Physics: Conference Series, 1065, p. 262002. ISSN (print) 1742-6588

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Abstract

It is widely recognised that there is a global need for cheaper launchers for small satellites, and there is considerable global effort led primarily by private enterprise to develop these. One way to achieve these lower costs is to use cheaper materials, usually by sacrificing some of the performance benefit. A dual birectional double vortex bipropellant engine has been designed that confines combustion to the core of the rocket engine, thereby maintaining much cooler wall temperatures, enabling the employment of cheaper materials with lower melting temperatures. This paper reports on the design and successful test firing of such an engine with a nominal thrust of 20N, the first time that such an engine has been developed in an educational setting.

Item Type: Article
Additional Information: Published version of Augousti, A. T., Baker, A. and Marlow, J-J. (2018) Design and test firing of a dual bidirectional double vortex bipropellant rocket engine. In: XXII World Congress of the International Measurement Confederation (IMEKO 2018); 03 - 06 Sep 2018, Belfast, U.K.
Research Area: General engineering and mineral and mining engineering
Faculty, School or Research Centre: Faculty of Science, Engineering and Computing > School of Engineering
Depositing User: Susan Miles
Date Deposited: 28 Nov 2018 08:57
Last Modified: 28 Nov 2018 08:57
DOI: https://doi.org/10.1088/1742-6596/1065/26/262002
URI: http://eprints.kingston.ac.uk/id/eprint/42400

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