Conceptual design: Dependence of parameterization on design performance of three-stage hybrid rocket
The subject of this paper is to improve on parameterization for conceptual design method of three stage hybrid rocket. Multi-Objective Genetic Algorithm (MOGA) is employed to solve multi-disciplinary design exploration of a three-stage launch vehicle concept using a hybrid rocket engine. MOGA which...
| Main Authors: | , , , , , |
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| Format: | Article |
| Language: | English |
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The Japan Society of Mechanical Engineers
2014-11-01
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| Series: | Journal of Fluid Science and Technology |
| Subjects: | |
| Online Access: | https://www.jstage.jst.go.jp/article/jfst/9/5/9_2014jfst0071/_pdf/-char/en |
| _version_ | 1818943128258740224 |
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| author | Masahiro KANAZAKI Fumio KANAMORI Yosuke KITAGAWA Masaki NAKAMIYA Koki KITAGAWA Toru SHIMADA |
| author_facet | Masahiro KANAZAKI Fumio KANAMORI Yosuke KITAGAWA Masaki NAKAMIYA Koki KITAGAWA Toru SHIMADA |
| author_sort | Masahiro KANAZAKI |
| collection | DOAJ |
| description | The subject of this paper is to improve on parameterization for conceptual design method of three stage hybrid rocket. Multi-Objective Genetic Algorithm (MOGA) is employed to solve multi-disciplinary design exploration of a three-stage launch vehicle concept using a hybrid rocket engine. MOGA which is used as the optimization methods for multi-objective problems utilizes real-number cording and the Pareto ranking method. According to our previous study, the propulsive performance of MOGA's solution was as low as the lower limit of design space. The design space of a conceptual three-stage launch vehicle hybrid rocket engine was reconsidered based on the results of multi-disciplinary design optimization. The design variables of the nozzles were reconsidered by exploring the design space. Specifically, the nozzle expansion ratio was considered as the ratio of the nozzle exit radius to the body radius. In this way, there are no solutions which violate the design constraints about the geometric condition of the nozzle exit. Consequently, the new conceptual design method can effectively explore solutions which have higher propulsive performance than previous method. As the result, the combustion chamber pressure is increased in the first stage. In the second stage, the solutions which are explored, modified parameterization are shown larger thrust level than previously. |
| first_indexed | 2024-12-20T07:22:24Z |
| format | Article |
| id | doaj.art-57f2ab13bbeb46f59ad1ba7f1e05b1b0 |
| institution | Directory Open Access Journal |
| issn | 1880-5558 |
| language | English |
| last_indexed | 2024-12-20T07:22:24Z |
| publishDate | 2014-11-01 |
| publisher | The Japan Society of Mechanical Engineers |
| record_format | Article |
| series | Journal of Fluid Science and Technology |
| spelling | doaj.art-57f2ab13bbeb46f59ad1ba7f1e05b1b02022-12-21T19:48:39ZengThe Japan Society of Mechanical EngineersJournal of Fluid Science and Technology1880-55582014-11-0195JFST0071JFST007110.1299/jfst.2014jfst0071jfstConceptual design: Dependence of parameterization on design performance of three-stage hybrid rocketMasahiro KANAZAKI0Fumio KANAMORI1Yosuke KITAGAWA2Masaki NAKAMIYA3Koki KITAGAWA4Toru SHIMADA5Faculty of System Design, Tokyo Metropolitan UniversityFaculty of System Design, Tokyo Metropolitan UniversityFaculty of System Design, Tokyo Metropolitan UniversityResearch Institute for Sustainable Humanosphere, Kyoto UniversityInstitute of Space and Astronautical Science/Japan Aerospace Exploration AgencyInstitute of Space and Astronautical Science/Japan Aerospace Exploration AgencyThe subject of this paper is to improve on parameterization for conceptual design method of three stage hybrid rocket. Multi-Objective Genetic Algorithm (MOGA) is employed to solve multi-disciplinary design exploration of a three-stage launch vehicle concept using a hybrid rocket engine. MOGA which is used as the optimization methods for multi-objective problems utilizes real-number cording and the Pareto ranking method. According to our previous study, the propulsive performance of MOGA's solution was as low as the lower limit of design space. The design space of a conceptual three-stage launch vehicle hybrid rocket engine was reconsidered based on the results of multi-disciplinary design optimization. The design variables of the nozzles were reconsidered by exploring the design space. Specifically, the nozzle expansion ratio was considered as the ratio of the nozzle exit radius to the body radius. In this way, there are no solutions which violate the design constraints about the geometric condition of the nozzle exit. Consequently, the new conceptual design method can effectively explore solutions which have higher propulsive performance than previous method. As the result, the combustion chamber pressure is increased in the first stage. In the second stage, the solutions which are explored, modified parameterization are shown larger thrust level than previously.https://www.jstage.jst.go.jp/article/jfst/9/5/9_2014jfst0071/_pdf/-char/enhybrid rocketmultidisciplinary design optimizationgenetic algorithmconceptual designdesign parameterization |
| spellingShingle | Masahiro KANAZAKI Fumio KANAMORI Yosuke KITAGAWA Masaki NAKAMIYA Koki KITAGAWA Toru SHIMADA Conceptual design: Dependence of parameterization on design performance of three-stage hybrid rocket Journal of Fluid Science and Technology hybrid rocket multidisciplinary design optimization genetic algorithm conceptual design design parameterization |
| title | Conceptual design: Dependence of parameterization on design performance of three-stage hybrid rocket |
| title_full | Conceptual design: Dependence of parameterization on design performance of three-stage hybrid rocket |
| title_fullStr | Conceptual design: Dependence of parameterization on design performance of three-stage hybrid rocket |
| title_full_unstemmed | Conceptual design: Dependence of parameterization on design performance of three-stage hybrid rocket |
| title_short | Conceptual design: Dependence of parameterization on design performance of three-stage hybrid rocket |
| title_sort | conceptual design dependence of parameterization on design performance of three stage hybrid rocket |
| topic | hybrid rocket multidisciplinary design optimization genetic algorithm conceptual design design parameterization |
| url | https://www.jstage.jst.go.jp/article/jfst/9/5/9_2014jfst0071/_pdf/-char/en |
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