Development of ammonium perchlorate based solid propellant

There are a lot of development and study of ammonium perchlorate (AP) based solid propellant are already existing in the world. However, there are no detail data and information on the low burning rate AP based solid propellant. This thesis discusses the study of development AP based solid propellan...

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Main Author:	Ahmad Hakimi, Abdul Nasir
Format:	Undergraduates Project Papers
Language:	English
Published:	2013
Subjects:	TL Motor vehicles. Aeronautics. Astronautics
Online Access:	http://umpir.ump.edu.my/id/eprint/8684/ http://umpir.ump.edu.my/id/eprint/8684/ http://umpir.ump.edu.my/id/eprint/8684/1/cd8245.pdf

id	ump-8684
recordtype	eprints
spelling	ump-86842015-10-29T00:02:55Z http://umpir.ump.edu.my/id/eprint/8684/ Development of ammonium perchlorate based solid propellant Ahmad Hakimi, Abdul Nasir TL Motor vehicles. Aeronautics. Astronautics There are a lot of development and study of ammonium perchlorate (AP) based solid propellant are already existing in the world. However, there are no detail data and information on the low burning rate AP based solid propellant. This thesis discusses the study of development AP based solid propellant. The objective of the study is to develop low burning rate AP based solid propellant including the selection of a propellant formulation, preparation and development of the propellant, and propellant burning rate experiments with the strand burner at atmospheric pressure. Together with the literature study and theoretical performance, five sets of different mixture were chosen based on their efficiency of propellant mixture. The propellant was a mixture of AP as an oxidizer, aluminum (Al) as fuel and hydroxy-terminated polybutadiene (HTPB) as a binder. For each mixture, HTPB was set at 15% and cured with isophorone diisocyanate (IPDI) (9.33% per weight of HTPB). By changing the AP and Al, the effect of oxidizer- fuel (O/F) ratio on the whole propellant can be determined. The lowest value of the testing obtained are propellant f80, that is 1.47mm/sec with O/F ratio 16.0. The study found, increased ratio O/F will affect to the combustion rate reduction factors of propellant. 2013-06 Undergraduates Project Papers NonPeerReviewed application/pdf en http://umpir.ump.edu.my/id/eprint/8684/1/cd8245.pdf Ahmad Hakimi, Abdul Nasir (2013) Development of ammonium perchlorate based solid propellant. Faculty of Mechanical Engineering, Universiti Malaysia Pahang. http://iportal.ump.edu.my/lib/item?id=chamo:82436&theme=UMP2
repository_type	Digital Repository
institution_category	Local University
institution	Universiti Malaysia Pahang
building	UMP Institutional Repository
collection	Online Access
language	English
topic	TL Motor vehicles. Aeronautics. Astronautics
spellingShingle	TL Motor vehicles. Aeronautics. Astronautics Ahmad Hakimi, Abdul Nasir Development of ammonium perchlorate based solid propellant
description	There are a lot of development and study of ammonium perchlorate (AP) based solid propellant are already existing in the world. However, there are no detail data and information on the low burning rate AP based solid propellant. This thesis discusses the study of development AP based solid propellant. The objective of the study is to develop low burning rate AP based solid propellant including the selection of a propellant formulation, preparation and development of the propellant, and propellant burning rate experiments with the strand burner at atmospheric pressure. Together with the literature study and theoretical performance, five sets of different mixture were chosen based on their efficiency of propellant mixture. The propellant was a mixture of AP as an oxidizer, aluminum (Al) as fuel and hydroxy-terminated polybutadiene (HTPB) as a binder. For each mixture, HTPB was set at 15% and cured with isophorone diisocyanate (IPDI) (9.33% per weight of HTPB). By changing the AP and Al, the effect of oxidizer- fuel (O/F) ratio on the whole propellant can be determined. The lowest value of the testing obtained are propellant f80, that is 1.47mm/sec with O/F ratio 16.0. The study found, increased ratio O/F will affect to the combustion rate reduction factors of propellant.
format	Undergraduates Project Papers
author	Ahmad Hakimi, Abdul Nasir
author_facet	Ahmad Hakimi, Abdul Nasir
author_sort	Ahmad Hakimi, Abdul Nasir
title	Development of ammonium perchlorate based solid propellant
title_short	Development of ammonium perchlorate based solid propellant
title_full	Development of ammonium perchlorate based solid propellant
title_fullStr	Development of ammonium perchlorate based solid propellant
title_full_unstemmed	Development of ammonium perchlorate based solid propellant
title_sort	development of ammonium perchlorate based solid propellant
publishDate	2013
url	http://umpir.ump.edu.my/id/eprint/8684/ http://umpir.ump.edu.my/id/eprint/8684/ http://umpir.ump.edu.my/id/eprint/8684/1/cd8245.pdf
first_indexed	2023-09-18T22:06:32Z
last_indexed	2023-09-18T22:06:32Z
_version_	1777414745160155136

Development of ammonium perchlorate based solid propellant

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