Design and fabrication of a rocket engine powered by kerosene with compressed oxygen as an oxidiser / Rusli Abdul Aziz

This paper presents the design, fabrication and testing of a bi - propellant rocket engine with a thrust of 250N. Kerosene and oxygen, in liquid and gaseous form respectively, are used as propellants. The test engine is fabricated from solid round bars of stainless steel on a lathe machine. A test s...

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Main Author:	Abdul Aziz, Rusli
Format:	Thesis
Language:	English
Published:	2006
Subjects:	Machine design and drawing
Online Access:	https://ir.uitm.edu.my/id/eprint/37346/1/37346.pdf
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id	my-uitm-ir.37346
record_format	uketd_dc
spelling	my-uitm-ir.373462020-11-23T05:15:02Z Design and fabrication of a rocket engine powered by kerosene with compressed oxygen as an oxidiser / Rusli Abdul Aziz 2006 Abdul Aziz, Rusli Machine design and drawing This paper presents the design, fabrication and testing of a bi - propellant rocket engine with a thrust of 250N. Kerosene and oxygen, in liquid and gaseous form respectively, are used as propellants. The test engine is fabricated from solid round bars of stainless steel on a lathe machine. A test stand is designed and built for mounting the test rocket motor. Auxiliary systems, such as the fuel and oxygen feed systems, together with the ignition system, are designed and assembled. Specific operating procedures for testing the engine and its related systems, for application during both non - firing and firing tests, are developed. The rocket engine is water - tested for pressure leaks and the spray pattern of propellant at the injector is observed. The static firing test of the rocket engine is yet to be performed. The thrust produced by the rocket motor during the static firing test is expected to be about 200N. The static firing test operating procedures are recommended to determine the performance of the rocket engine. Further recommendations for modifications and improvement of the test rocket engine are discussed. These recommendations are discussed in the context of building a UiTM rocket 2006 Thesis https://ir.uitm.edu.my/id/eprint/37346/ https://ir.uitm.edu.my/id/eprint/37346/1/37346.pdf text en public degree Universiti Teknologi MARA Faculty of Mechanical Engineering Atan, Rahim (A/P Dr Hj)
institution	Universiti Teknologi MARA
collection	UiTM Institutional Repository
language	English
advisor	Atan, Rahim (A/P Dr Hj)
topic	Machine design and drawing
spellingShingle	Machine design and drawing Abdul Aziz, Rusli Design and fabrication of a rocket engine powered by kerosene with compressed oxygen as an oxidiser / Rusli Abdul Aziz
description	This paper presents the design, fabrication and testing of a bi - propellant rocket engine with a thrust of 250N. Kerosene and oxygen, in liquid and gaseous form respectively, are used as propellants. The test engine is fabricated from solid round bars of stainless steel on a lathe machine. A test stand is designed and built for mounting the test rocket motor. Auxiliary systems, such as the fuel and oxygen feed systems, together with the ignition system, are designed and assembled. Specific operating procedures for testing the engine and its related systems, for application during both non - firing and firing tests, are developed. The rocket engine is water - tested for pressure leaks and the spray pattern of propellant at the injector is observed. The static firing test of the rocket engine is yet to be performed. The thrust produced by the rocket motor during the static firing test is expected to be about 200N. The static firing test operating procedures are recommended to determine the performance of the rocket engine. Further recommendations for modifications and improvement of the test rocket engine are discussed. These recommendations are discussed in the context of building a UiTM rocket
format	Thesis
qualification_level	Bachelor degree
author	Abdul Aziz, Rusli
author_facet	Abdul Aziz, Rusli
author_sort	Abdul Aziz, Rusli
title	Design and fabrication of a rocket engine powered by kerosene with compressed oxygen as an oxidiser / Rusli Abdul Aziz
title_short	Design and fabrication of a rocket engine powered by kerosene with compressed oxygen as an oxidiser / Rusli Abdul Aziz
title_full	Design and fabrication of a rocket engine powered by kerosene with compressed oxygen as an oxidiser / Rusli Abdul Aziz
title_fullStr	Design and fabrication of a rocket engine powered by kerosene with compressed oxygen as an oxidiser / Rusli Abdul Aziz
title_full_unstemmed	Design and fabrication of a rocket engine powered by kerosene with compressed oxygen as an oxidiser / Rusli Abdul Aziz
title_sort	design and fabrication of a rocket engine powered by kerosene with compressed oxygen as an oxidiser / rusli abdul aziz
granting_institution	Universiti Teknologi MARA
granting_department	Faculty of Mechanical Engineering
publishDate	2006
url	https://ir.uitm.edu.my/id/eprint/37346/1/37346.pdf
_version_	1783734421202927616

Design and fabrication of a rocket engine powered by kerosene with compressed oxygen as an oxidiser / Rusli Abdul Aziz

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