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...
| Main Authors: | , , , |
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| Format: | Conference or Workshop Item |
| Language: | English |
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IOP Publishing
2012
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| Online Access: | http://umpir.ump.edu.my/id/eprint/25159/ http://umpir.ump.edu.my/id/eprint/25159/1/Effect%20of%20propellant%20composition%20to%20the%20temperature%20sensitivity%20of%20composite%20propellant.pdf |
| _version_ | 1848822214518898688 |
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| 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 |
| building | UMP Institutional Repository |
| collection | Online Access |
| 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. |
| first_indexed | 2025-11-15T02:37:41Z |
| format | Conference or Workshop Item |
| id | ump-25159 |
| institution | Universiti Malaysia Pahang |
| institution_category | Local University |
| language | English |
| last_indexed | 2025-11-15T02:37:41Z |
| publishDate | 2012 |
| publisher | IOP Publishing |
| recordtype | eprints |
| repository_type | Digital Repository |
| spelling | ump-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 (Published) https://doi.org/10.1088/1757-899X/36/1/012023 |
| 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 |
| title | 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_short | Effect of propellant composition to the temperature sensitivity of composite propellant |
| title_sort | effect of propellant composition to the temperature sensitivity of composite propellant |
| topic | TJ Mechanical engineering and machinery |
| url | http://umpir.ump.edu.my/id/eprint/25159/ http://umpir.ump.edu.my/id/eprint/25159/ http://umpir.ump.edu.my/id/eprint/25159/1/Effect%20of%20propellant%20composition%20to%20the%20temperature%20sensitivity%20of%20composite%20propellant.pdf |