Development of a 10 newton hydrogen peroxide monopropellant rocket thruster

Propellant is one of the important parts in rocket development. There are many types of propellant such as nitrogen tetroxide and hydrazine but most of them are toxic in nature and can harm our health and environment. This has increased the renewed interest on hydrogen peroxide, also known as “green...

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Main Author:	Nambaraja, Kuberaraaj
Format:	Thesis
Language:	English
Published:	2013
Subjects:	TJ Mechanical engineering and machinery
Online Access:	http://eprints.utm.my/id/eprint/40596/5/KuberaraajNambarajaMFKM2013.pdf
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id	my-utm-ep.40596
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spelling	my-utm-ep.405962020-06-03T05:40:02Z Development of a 10 newton hydrogen peroxide monopropellant rocket thruster 2013-02 Nambaraja, Kuberaraaj TJ Mechanical engineering and machinery Propellant is one of the important parts in rocket development. There are many types of propellant such as nitrogen tetroxide and hydrazine but most of them are toxic in nature and can harm our health and environment. This has increased the renewed interest on hydrogen peroxide, also known as “green” propellant that can act as monopropellant or oxidizer which is ideal for spacecraft programs. This research is mainly about developing a rocket thruster by using hydrogen peroxide as monopropellant. Therefore, a 10 Newton rocket thruster has been designed and fabricated. However, in order to test the performance of rocket thruster, there are several preparations that have been done. Firstly, was the preparation of rocket grade hydrogen peroxide (concentration > 85%) from lower concentration of hydrogen peroxide. Next, was development of rocket test facility which consists of two integral parts; (1) static test rig and (2) data acquisition system. Measuring discharge coefficient of the thruster injector was also part of the preparations to ensure the mass flow rate of propellant. Finally, the catalyst pack was prepared where silver screens were used as catalyzer. The hydrogen peroxide would react with the catalyst pack and decompose into water and oxygen. In order to identify the optimum configuration of producing 10 N thrust, several parameters were taken into consideration and they are injector orifice diameter, nozzle throat diameter, type of hydrogen peroxide used, catalyst pack length, compaction pressure of catalyst pack, engine heating temperature and propellant injection pressure. With a total of 5 series of successful hot tests, the optimum configuration of producing 10 N thrust using hydrogen peroxide monopropellant rocket thruster had been achieved. The configuration is: i D = 0.601 mm, t D = 2.236 mm, cp P = 9.29 MPa (50 kg by strain gauge) and 2 P = 37 bar. 2013-02 Thesis http://eprints.utm.my/id/eprint/40596/ http://eprints.utm.my/id/eprint/40596/5/KuberaraajNambarajaMFKM2013.pdf application/pdf en public masters Universiti Teknologi Malaysia, Faculty of Mechanical Engineering Faculty of Mechanical Engineering
institution	Universiti Teknologi Malaysia
collection	UTM Institutional Repository
language	English
topic	TJ Mechanical engineering and machinery
spellingShingle	TJ Mechanical engineering and machinery Nambaraja, Kuberaraaj Development of a 10 newton hydrogen peroxide monopropellant rocket thruster
description	Propellant is one of the important parts in rocket development. There are many types of propellant such as nitrogen tetroxide and hydrazine but most of them are toxic in nature and can harm our health and environment. This has increased the renewed interest on hydrogen peroxide, also known as “green” propellant that can act as monopropellant or oxidizer which is ideal for spacecraft programs. This research is mainly about developing a rocket thruster by using hydrogen peroxide as monopropellant. Therefore, a 10 Newton rocket thruster has been designed and fabricated. However, in order to test the performance of rocket thruster, there are several preparations that have been done. Firstly, was the preparation of rocket grade hydrogen peroxide (concentration > 85%) from lower concentration of hydrogen peroxide. Next, was development of rocket test facility which consists of two integral parts; (1) static test rig and (2) data acquisition system. Measuring discharge coefficient of the thruster injector was also part of the preparations to ensure the mass flow rate of propellant. Finally, the catalyst pack was prepared where silver screens were used as catalyzer. The hydrogen peroxide would react with the catalyst pack and decompose into water and oxygen. In order to identify the optimum configuration of producing 10 N thrust, several parameters were taken into consideration and they are injector orifice diameter, nozzle throat diameter, type of hydrogen peroxide used, catalyst pack length, compaction pressure of catalyst pack, engine heating temperature and propellant injection pressure. With a total of 5 series of successful hot tests, the optimum configuration of producing 10 N thrust using hydrogen peroxide monopropellant rocket thruster had been achieved. The configuration is: i D = 0.601 mm, t D = 2.236 mm, cp P = 9.29 MPa (50 kg by strain gauge) and 2 P = 37 bar.
format	Thesis
qualification_level	Master's degree
author	Nambaraja, Kuberaraaj
author_facet	Nambaraja, Kuberaraaj
author_sort	Nambaraja, Kuberaraaj
title	Development of a 10 newton hydrogen peroxide monopropellant rocket thruster
title_short	Development of a 10 newton hydrogen peroxide monopropellant rocket thruster
title_full	Development of a 10 newton hydrogen peroxide monopropellant rocket thruster
title_fullStr	Development of a 10 newton hydrogen peroxide monopropellant rocket thruster
title_full_unstemmed	Development of a 10 newton hydrogen peroxide monopropellant rocket thruster
title_sort	development of a 10 newton hydrogen peroxide monopropellant rocket thruster
granting_institution	Universiti Teknologi Malaysia, Faculty of Mechanical Engineering
granting_department	Faculty of Mechanical Engineering
publishDate	2013
url	http://eprints.utm.my/id/eprint/40596/5/KuberaraajNambarajaMFKM2013.pdf
_version_	1747816560354918400

Development of a 10 newton hydrogen peroxide monopropellant rocket thruster

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