:: International Transaction Journal of Engineering, Management, & Applied Sciences & Technologies
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ISSN 2228-9860
eISSN 1906-9642
CODEN: ITJEA8
FEATURE PEER-REVIEWED ARTICLE
Vol.13(13)(2022) |
Effects of Propellant Fabrication on the Design for N-Class KNSB Solid Rocket Motor
Mohamad Amirul Muhammad (High Energy Material Research Laboratory (HEMREL), School of Mechanical Engineering, College of Engineering, Universiti Teknologi MARA (UiTM), 40450 Shah Alam, Selangor, MALAYSIA),
(MTC Engineering Sdn. Bhd., No. 2, Jalan Astaka U8/88B, 40150 Shah Alam, Selangor, MALAYSIA),
Zuraidah Salleh, Ahmad Hussein Abd Hamid (High Energy Material Research Laboratory (HEMREL), School of Mechanical Engineering, College of Engineering, Universiti Teknologi MARA (UiTM), 40450 Shah Alam, Selangor, MALAYSIA),
Mohammad Juani Sujana (MTC Engineering Sdn. Bhd., No. 2, Jalan Astaka U8/88B, 40150 Shah Alam, Selangor, MALAYSIA),
Muhammad Hanafi Azami (Department of Mechanical & Aerospace Engineering, Kulliyyah of Engineering, International Islamic University Malaysia, Gombak, Kuala Lumpur, 53100, MALAYSIA),
Abd Halim Haji Idris (Weapons Technology Division, Science and Technology Research Institute for Defence (STRIDED), Selangor, MALAYSIA).
Discipline: Aerospace, Mechanical Engineering.
doi: 10.14456/ITJEMAST.2022.272
Keywords:Static Test; Density Ratio; Cartridge; Case-Bonded; External Voids; Internal Voids
AbstractIn the age of the Internet of Things (IoT), satellite launching has become more common than in the past decades. To date, the rocket system is the only means of bringing satellites into Earth's orbit. However, the technology is very localized, and Malaysia is still in an embryonic stage. The main motivation is to produce a reliable rocket motor using relatively cheap and easily available resources. In this thesis, the best manufacturing casting method that yields more than 95% density ratio was studied for KNSB sugar-based propellant. The N-Class SRM was fabricated, tested and discussed. Each propellant manufacturing method was repeated for three samples and the sample density was calculated. The fabricated SRM was static test fired and the results were discussed with root cause analysis. The results were compared with the theoretical and discuss. The findings from the test static test show that the ejection of the nozzle during the static firing test is most probably case by the external and internal voids caused by the manufacturing method. The suggested method is to change from cartridge form to case-bonded propellant and use compression during casting to remove the internal air bubble that produced internal voids.Paper ID: 13A13T
Cite this article:
Muhammad, M.A., Salleh Z., A Hamid A.H., Sujana M.J., Azami, M.H., and Idris, A.H. (2022). Effects of Propellant Fabrication on the Design for N-Class KNSB Solid Rocket Motor. International Transaction Journal of Engineering, Management, & Applied Sciences & Technologies, 13(13), 13A13T, 1-15. http://TUENGR.COM/V13/13A13T.pdf DOI: 10.14456/ITJEMAST.2022.272
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