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Effect of propellant composition to the temperature sensitivity of composite propellant

The propellant composition is one of several parameter that influencing the temperature sensitivity of composite propellant. In this paper, experimental investigation of temperature sensitivity in burning rate of composite propellant was conducted. Four sets of different propellant compositions had...

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Main Authors: Amir, Aziz, R., Mamat, Amin, Makeen, Wan Khairuddin, Wan Ali
Format: Conference or Workshop Item
Language:English
Published: IOP Publishing 2012
Subjects:
TJ Mechanical engineering and machinery
Online Access:http://umpir.ump.edu.my/id/eprint/25159/1/Effect%20of%20propellant%20composition%20to%20the%20temperature%20sensitivity%20of%20composite%20propellant.pdf
http://umpir.ump.edu.my/id/eprint/25159/
https://doi.org/10.1088/1757-899X/36/1/012023
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spelling my.ump.umpir.251592019-11-11T06:47:15Z http://umpir.ump.edu.my/id/eprint/25159/ Effect of propellant composition to the temperature sensitivity of composite propellant Amir, Aziz R., Mamat Amin, Makeen Wan Khairuddin, Wan Ali TJ Mechanical engineering and machinery The propellant composition is one of several parameter that influencing the temperature sensitivity of composite propellant. In this paper, experimental investigation of temperature sensitivity in burning rate of composite propellant was conducted. Four sets of different propellant compositions had been prepared with the combination of ammonium perchlorate (AP) as an oxidizer, aluminum (Al) as fuel and hydroxy-terminated polybutadiene (HTPB) as fuel and binder. For each mixture, HTPB binder was fixed at 15% and cured with isophorone diisocyanate (IPDI). By varying AP and Al, the effect of oxidizer- fuel mixture ratio (O/F) on the whole propellant can be determined. The propellant strands were manufactured using compression molded method and burnt in a strand burner using wire technique over a range of pressure from 1 atm to 31 atm. The results obtained shows that the temperature sensitivity, a, increases with increasing O/F. Propellant p80 which has O/F ratio of 80/20 gives the highest value of temperature sensitivity which is 1.687. The results shows that the propellant composition has significant effect on the temperature sensitivity of composite propellant. IOP Publishing 2012 Conference or Workshop Item PeerReviewed pdf en http://umpir.ump.edu.my/id/eprint/25159/1/Effect%20of%20propellant%20composition%20to%20the%20temperature%20sensitivity%20of%20composite%20propellant.pdf Amir, Aziz and R., Mamat and Amin, Makeen and Wan Khairuddin, Wan Ali (2012) Effect of propellant composition to the temperature sensitivity of composite propellant. In: 1st International Conference on Mechanical Engineering Research, ICMER 2011, 5-7 Disember 2011 , Kuantan, Pahang Darul Makmur. pp. 1-7., 36 (012023). ISSN 1757-899X https://doi.org/10.1088/1757-899X/36/1/012023
institution Universiti Malaysia Pahang
building UMP Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Malaysia Pahang
content_source UMP Institutional Repository
url_provider http://umpir.ump.edu.my/
language English
topic TJ Mechanical engineering and machinery
spellingShingle TJ Mechanical engineering and machinery
Amir, Aziz
R., Mamat
Amin, Makeen
Wan Khairuddin, Wan Ali
Effect of propellant composition to the temperature sensitivity of composite propellant
description The propellant composition is one of several parameter that influencing the temperature sensitivity of composite propellant. In this paper, experimental investigation of temperature sensitivity in burning rate of composite propellant was conducted. Four sets of different propellant compositions had been prepared with the combination of ammonium perchlorate (AP) as an oxidizer, aluminum (Al) as fuel and hydroxy-terminated polybutadiene (HTPB) as fuel and binder. For each mixture, HTPB binder was fixed at 15% and cured with isophorone diisocyanate (IPDI). By varying AP and Al, the effect of oxidizer- fuel mixture ratio (O/F) on the whole propellant can be determined. The propellant strands were manufactured using compression molded method and burnt in a strand burner using wire technique over a range of pressure from 1 atm to 31 atm. The results obtained shows that the temperature sensitivity, a, increases with increasing O/F. Propellant p80 which has O/F ratio of 80/20 gives the highest value of temperature sensitivity which is 1.687. The results shows that the propellant composition has significant effect on the temperature sensitivity of composite propellant.
format Conference or Workshop Item
author Amir, Aziz
R., Mamat
Amin, Makeen
Wan Khairuddin, Wan Ali
author_facet Amir, Aziz
R., Mamat
Amin, Makeen
Wan Khairuddin, Wan Ali
author_sort Amir, Aziz
title Effect of propellant composition to the temperature sensitivity of composite propellant
title_short Effect of propellant composition to the temperature sensitivity of composite propellant
title_full Effect of propellant composition to the temperature sensitivity of composite propellant
title_fullStr Effect of propellant composition to the temperature sensitivity of composite propellant
title_full_unstemmed Effect of propellant composition to the temperature sensitivity of composite propellant
title_sort effect of propellant composition to the temperature sensitivity of composite propellant
publisher IOP Publishing
publishDate 2012
url http://umpir.ump.edu.my/id/eprint/25159/1/Effect%20of%20propellant%20composition%20to%20the%20temperature%20sensitivity%20of%20composite%20propellant.pdf
http://umpir.ump.edu.my/id/eprint/25159/
https://doi.org/10.1088/1757-899X/36/1/012023
_version_ 1651866920588148736
score 13.211869

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