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Design Optimization of Propellant Grain and Nozzle Contour to Improve Performance of Solid Rocket Propulsion

Journal of Engineering and Technological Sciences · Vol. 54 No. 5 (2022)

DOI
10.5614/j.eng.technol.sci.2022.54.5.8
ISSN
2338-5502, 2337-5779
Terbit
2022-09-15
Penerbit
Directorate for Research and Community Services, Institut Teknologi Bandung
Bahasa
eng

Abstrak

A rocket is a spacecraft, guided missile, or flying vehicle that boosted by a chemical reaction resulting from the combustion of propellant in the rocket motor. One of the essential parameters in the development of rocket motors is design optimization to improve the propulsion performance of the rocket. Increasing the propulsion performance of the rocket will increase the flight performance of the rocket, in terms of its maximum range or the altitude of the rocket trajectory. This study examined the determination of the design parameter values of a rocket motor by looking at it as an optimization problem with constraints. The problem studied was limited to the case of the second-stage rocket motor. A genetic algorithm was used to solve the resulting optimization problem of propellant grain configuration cases and a characteristic method for designing the bell nozzle. The results obtained indicated an increase in total impulse by 10% compared to the results before optimization.

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  • Lampung University
  • University of Bengkulu
  • Bandung Institute of Technology
  • Universitas Jambi
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Rekan penulisOrganisasiArtikel bersama
Suhadi SuhadiAfiliasi tidak diketahui1
Junaid JunaidAfiliasi tidak diketahui1
Dian KurniasariLampung University1
Mustofa UsmanLampung University1
Virda KurniawatiLampung University1
Rizki Khoirun NisaLampung University1
Fatimatuzzahra FatimatuzzahraLampung University1
Agus SutrisnoLampung University1
La ZakariaLampung University1
Fachri FaisalUniversity of Bengkulu1
Swita BakiUniversity of Bengkulu1
Mulia AstutiUniversity of Bengkulu1
Muhammad Iqbal SultanAfiliasi tidak diketahui1
Damris MuhammadUniversitas Jambi1
Rachmawati RachmawatiAfiliasi tidak diketahui1
Indrawata WardhanaAfiliasi tidak diketahui1
Vandri Ahmad IsnainiAfiliasi tidak diketahui1
Rahmi Putri WirmanAfiliasi tidak diketahui1
Dian MursyitahAfiliasi tidak diketahui1
Parmo ParmoAfiliasi tidak diketahui1
H. AssiyatunAfiliasi tidak diketahui1
E. T. BaskoroAfiliasi tidak diketahui1
Kuntjoro Adji SidartoBandung Institute of Technology1
Agus Yodi GunawanBandung Institute of Technology1
Yogi Wibisono BudhiAfiliasi tidak diketahui1

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Sumber metadata: OAI-PMH (metadata jurnal) https://journals.itb.ac.id/index.php/jets/oai, pertama di-harvest 9 Nov 2026, terakhir terlihat 9 Nov 2026.
Metadata asli (oai_dc) 
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	<dc:title xml:lang="en-US">Design Optimization of Propellant Grain and Nozzle Contour to Improve Performance of Solid Rocket Propulsion</dc:title>
	<dc:creator>Abyan, Muhammad Ihsan</dc:creator>
	<dc:creator>Nuryaman, Aang</dc:creator>
	<dc:creator>Jihad, Bagus Hayatul </dc:creator>
	<dc:creator>Junjunan, Soleh Fajar </dc:creator>
	<dc:creator>Asmiati, Asmiati</dc:creator>
	<dc:subject xml:lang="en-US">dual stage</dc:subject>
	<dc:subject xml:lang="en-US">genetic algorithm</dc:subject>
	<dc:subject xml:lang="en-US">method of characteristic optimizations</dc:subject>
	<dc:subject xml:lang="en-US">nozzle</dc:subject>
	<dc:subject xml:lang="en-US">propellant grain</dc:subject>
	<dc:subject xml:lang="en-US">Mechanical Engineering</dc:subject>
	<dc:description xml:lang="en-US">A rocket is a spacecraft, guided missile, or flying vehicle that boosted by a chemical reaction resulting from the combustion of propellant in the rocket motor. One of the essential parameters in the development of rocket motors is design optimization to improve the propulsion performance of the rocket. Increasing the propulsion performance of the rocket will increase the flight performance of the rocket, in terms of its maximum range or the altitude of the rocket trajectory. This study examined the determination of the design parameter values of a rocket motor by looking at it as an optimization problem with constraints. The problem studied was limited to the case of the second-stage rocket motor. A genetic algorithm was used to solve the resulting optimization problem of propellant grain configuration cases and a characteristic method for designing the bell nozzle. The results obtained indicated an increase in total impulse by 10% compared to the results before optimization.</dc:description>
	<dc:publisher xml:lang="en-US">Directorate for Research and Community Services, Institut Teknologi Bandung</dc:publisher>
	<dc:date>2022-09-15</dc:date>
	<dc:type>info:eu-repo/semantics/article</dc:type>
	<dc:type>info:eu-repo/semantics/publishedVersion</dc:type>
	<dc:format>application/pdf</dc:format>
	<dc:identifier>https://journals.itb.ac.id/index.php/jets/article/view/17255</dc:identifier>
	<dc:identifier>10.5614/j.eng.technol.sci.2022.54.5.8</dc:identifier>
	<dc:source xml:lang="en-US">Journal of Engineering and Technological Sciences; Vol. 54 No. 5 (2022); 220508</dc:source>
	<dc:source>2338-5502</dc:source>
	<dc:source>2337-5779</dc:source>
	<dc:source>10.5614/j.eng.technol.sci.2022.54.5</dc:source>
	<dc:language>eng</dc:language>
	<dc:relation>https://journals.itb.ac.id/index.php/jets/article/view/17255/5955</dc:relation>
	<dc:rights xml:lang="en-US">Copyright (c) 2022 Journal of Engineering and Technological Sciences</dc:rights>
</oai_dc:dc>