Static hot-fire testing of a green hybrid rocket engine

Citation

Ahmad, Mohamed Tarmizi and Jagannathan, Anudiipnath and Abidin, Razali and Zhahir, Amzari and Saniman, Muhammad Nur Farhan (2014) Static hot-fire testing of a green hybrid rocket engine. Journal of Aeronautics, Astronautics and Aviation, 56 (1S). art. no. 30. pp. 405-417. ISSN 1990-7710

Abstract

This paper presents the conduct of the hot-fire testing for a green hybrid rocket engine. The hybrid rocket engine consists of liquid nitrous oxide (N2O) as the oxidizer, with the stearic acid as the solid fuel and the incorporation of carbon nanotube and aluminum powder as the additives. From the conducted experimental, all systems that have been designed and developed in this study for the green hybrid rocket engine are demonstrated to be successful and fully functional, which also include the radio frequency control unit. Based on the results of the experiment, the developed laboratory-scale green hybrid rocket motor has been successfully ignited and produced a maximum thrust of 348 N, with the maximum combustion chamber pressure is recorded as 14 bar. In addition, several suggestions to improve the hybrid rocket engine design are also discussed.

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Additional Metadata

Item Type:	Article
Subject:	Aerospace engineering
Subject:	Jet propulsion
Divisions:	Faculty of Engineering
DOI Number:	https://doi.org/10.6125/JoAAA.202403_56(1S).29
Publisher:	Aeronautical and Astronautical Society of the Republic of China
Keywords:	Oxidizer flow control; Nitrous oxide; Green hybrid rocket engine; Static hybrid rocket; Stearic acid fuel
Depositing User:	Scopus 2024
Date Deposited:	23 Apr 2024 01:16
Last Modified:	23 Apr 2024 01:16
Altmetrics:	http://www.altmetric.com/details.php?domain=psasir.upm.edu.my&doi=10.6125/JoAAA.202403_56(1S).29
URI:	http://psasir.upm.edu.my/id/eprint/111004
Statistic Details:	View Download Statistic

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