Solid propellant formulation and testing for MESO-scale rocket / Zharif Farhan Ghazali

This research is intended to develop a solid propellant rocket. In order to achieve the improvement in aerospace and military, solid propellant rocket is widely applied because of its easier and cheaper to fabricate as compared to liquids propellant rocket. In aerospace, solid propellant rocket was...

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Main Author:	Ghazali, Zharif Farhan
Format:	Thesis
Language:	English
Published:	2010
Subjects:	Energy conservation
Online Access:	https://ir.uitm.edu.my/id/eprint/37350/1/37350.pdf
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id	my-uitm-ir.37350
record_format	uketd_dc
spelling	my-uitm-ir.373502023-06-23T03:05:29Z Solid propellant formulation and testing for MESO-scale rocket / Zharif Farhan Ghazali 2010 Ghazali, Zharif Farhan Energy conservation Control engineering systems. Automatic machinery (General) This research is intended to develop a solid propellant rocket. In order to achieve the improvement in aerospace and military, solid propellant rocket is widely applied because of its easier and cheaper to fabricate as compared to liquids propellant rocket. In aerospace, solid propellant rocket was used to transfer satellite to outer space and it can assist the nation and the telecommunication discipline. Propellant is the chemical mixture burned to produce thrust in rockets and consists of fuel and oxidizer. A fuel is a substance which burns when combined with oxygen producing gas for propulsion. Oxidizer is an agent that releases oxygen for combination with a fuel. The ratio of oxidizer to fuel is called the mixture ratio. Propellants are classified according to their state which are liquid, solid, or hybrid. The solid propellant was made of potassium nitrate and ammonium nitrate as the oxidizer and sucrose as the binder and the fuel. The energy releases by solid propellants were test by using bomb calorimeter. From this research, it is expected that the optimum mixture of the propellant is to be exposed. The higher the calorific value created the higher the thrust produced. Preliminary experiment showed that the solid propellant have good characteristic of a rocket propellant. This experiment shows that the propellant which has higher fuel contain has higher calorific value. 2010 Thesis https://ir.uitm.edu.my/id/eprint/37350/ https://ir.uitm.edu.my/id/eprint/37350/1/37350.pdf text en public degree Universiti Teknologi MARA Faculty of Mechanical Engineering Hussein, Ahmad
institution	Universiti Teknologi MARA
collection	UiTM Institutional Repository
language	English
advisor	Hussein, Ahmad
topic	Energy conservation Energy conservation
spellingShingle	Energy conservation Energy conservation Ghazali, Zharif Farhan Solid propellant formulation and testing for MESO-scale rocket / Zharif Farhan Ghazali
description	This research is intended to develop a solid propellant rocket. In order to achieve the improvement in aerospace and military, solid propellant rocket is widely applied because of its easier and cheaper to fabricate as compared to liquids propellant rocket. In aerospace, solid propellant rocket was used to transfer satellite to outer space and it can assist the nation and the telecommunication discipline. Propellant is the chemical mixture burned to produce thrust in rockets and consists of fuel and oxidizer. A fuel is a substance which burns when combined with oxygen producing gas for propulsion. Oxidizer is an agent that releases oxygen for combination with a fuel. The ratio of oxidizer to fuel is called the mixture ratio. Propellants are classified according to their state which are liquid, solid, or hybrid. The solid propellant was made of potassium nitrate and ammonium nitrate as the oxidizer and sucrose as the binder and the fuel. The energy releases by solid propellants were test by using bomb calorimeter. From this research, it is expected that the optimum mixture of the propellant is to be exposed. The higher the calorific value created the higher the thrust produced. Preliminary experiment showed that the solid propellant have good characteristic of a rocket propellant. This experiment shows that the propellant which has higher fuel contain has higher calorific value.
format	Thesis
qualification_level	Bachelor degree
author	Ghazali, Zharif Farhan
author_facet	Ghazali, Zharif Farhan
author_sort	Ghazali, Zharif Farhan
title	Solid propellant formulation and testing for MESO-scale rocket / Zharif Farhan Ghazali
title_short	Solid propellant formulation and testing for MESO-scale rocket / Zharif Farhan Ghazali
title_full	Solid propellant formulation and testing for MESO-scale rocket / Zharif Farhan Ghazali
title_fullStr	Solid propellant formulation and testing for MESO-scale rocket / Zharif Farhan Ghazali
title_full_unstemmed	Solid propellant formulation and testing for MESO-scale rocket / Zharif Farhan Ghazali
title_sort	solid propellant formulation and testing for meso-scale rocket / zharif farhan ghazali
granting_institution	Universiti Teknologi MARA
granting_department	Faculty of Mechanical Engineering
publishDate	2010
url	https://ir.uitm.edu.my/id/eprint/37350/1/37350.pdf
_version_	1783734422359506944

Solid propellant formulation and testing for MESO-scale rocket / Zharif Farhan Ghazali

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