Conceptual design of single-stage launch vehicle with hybrid rocket engine using design informatics
A single-stage launch vehicle with hybrid rocket engine has been conceptually designed by using design informatics, which has three points of view, i.e., problem definition, optimization, and data mining. The primary objective of the present design is that the down range and the duration time in the...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | Japanese |
| Published: |
The Japan Society of Mechanical Engineers
2014-10-01
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| Series: | Nihon Kikai Gakkai ronbunshu |
| Subjects: | |
| Online Access: | https://www.jstage.jst.go.jp/article/transjsme/80/818/80_2014trans0287/_pdf/-char/en |
| _version_ | 1798019082385096704 |
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| author | Kazuhisa CHIBA Shin'ya WATANABE Masahiro KANAZAKI Koki KITAGAWA Toru SHIMADA |
| author_facet | Kazuhisa CHIBA Shin'ya WATANABE Masahiro KANAZAKI Koki KITAGAWA Toru SHIMADA |
| author_sort | Kazuhisa CHIBA |
| collection | DOAJ |
| description | A single-stage launch vehicle with hybrid rocket engine has been conceptually designed by using design informatics, which has three points of view, i.e., problem definition, optimization, and data mining. The primary objective of the present design is that the down range and the duration time in the lower thermosphere are sufficiently obtained for the aurora scientific observation, whereas the initial gross weight is held down to the extent possible. The multidisciplinary design optimization was performed by using a hybrid evolutionary computation. Data mining was also implemented by using a self-organizing map and the stratum-type association analysis. Polypropylene and liquid oxygen with swirling flow are adopted as solid fuel and liquid oxidizer, respectively. The condition of single-time ignition is assumed in flight sequence. Consequently, the design information regarding the tradeoffs and the implication of the design variables for the objective functions has been obtained in order to quantitatively differentiate the advantage of hybrid rocket engine. |
| first_indexed | 2024-04-11T16:34:46Z |
| format | Article |
| id | doaj.art-77658e31b38e473e8a22c0c561292cab |
| institution | Directory Open Access Journal |
| issn | 2187-9761 |
| language | Japanese |
| last_indexed | 2024-04-11T16:34:46Z |
| publishDate | 2014-10-01 |
| publisher | The Japan Society of Mechanical Engineers |
| record_format | Article |
| series | Nihon Kikai Gakkai ronbunshu |
| spelling | doaj.art-77658e31b38e473e8a22c0c561292cab2022-12-22T04:13:52ZjpnThe Japan Society of Mechanical EngineersNihon Kikai Gakkai ronbunshu2187-97612014-10-0180818TRANS0287TRANS028710.1299/transjsme.2014trans0287transjsmeConceptual design of single-stage launch vehicle with hybrid rocket engine using design informaticsKazuhisa CHIBA0Shin'ya WATANABE1Masahiro KANAZAKI2Koki KITAGAWA3Toru SHIMADA4Graduate School of Engineering, Hokkaido University of ScienceCollege of Information and Systems, Muroran Institute of TechnologyGraduate School of System Design, Tokyo Metropolitan UniversityInstitute of Space and Astronautical Science, Japan Aerospace Exploration AgencyInstitute of Space and Astronautical Science, Japan Aerospace Exploration AgencyA single-stage launch vehicle with hybrid rocket engine has been conceptually designed by using design informatics, which has three points of view, i.e., problem definition, optimization, and data mining. The primary objective of the present design is that the down range and the duration time in the lower thermosphere are sufficiently obtained for the aurora scientific observation, whereas the initial gross weight is held down to the extent possible. The multidisciplinary design optimization was performed by using a hybrid evolutionary computation. Data mining was also implemented by using a self-organizing map and the stratum-type association analysis. Polypropylene and liquid oxygen with swirling flow are adopted as solid fuel and liquid oxidizer, respectively. The condition of single-time ignition is assumed in flight sequence. Consequently, the design information regarding the tradeoffs and the implication of the design variables for the objective functions has been obtained in order to quantitatively differentiate the advantage of hybrid rocket engine.https://www.jstage.jst.go.jp/article/transjsme/80/818/80_2014trans0287/_pdf/-char/endesign informaticsevolutionary computationdata miningsingle-stage launch vehicle for scientific observationhybrid rocket engine using solid fuel and liquid oxidizer |
| spellingShingle | Kazuhisa CHIBA Shin'ya WATANABE Masahiro KANAZAKI Koki KITAGAWA Toru SHIMADA Conceptual design of single-stage launch vehicle with hybrid rocket engine using design informatics Nihon Kikai Gakkai ronbunshu design informatics evolutionary computation data mining single-stage launch vehicle for scientific observation hybrid rocket engine using solid fuel and liquid oxidizer |
| title | Conceptual design of single-stage launch vehicle with hybrid rocket engine using design informatics |
| title_full | Conceptual design of single-stage launch vehicle with hybrid rocket engine using design informatics |
| title_fullStr | Conceptual design of single-stage launch vehicle with hybrid rocket engine using design informatics |
| title_full_unstemmed | Conceptual design of single-stage launch vehicle with hybrid rocket engine using design informatics |
| title_short | Conceptual design of single-stage launch vehicle with hybrid rocket engine using design informatics |
| title_sort | conceptual design of single stage launch vehicle with hybrid rocket engine using design informatics |
| topic | design informatics evolutionary computation data mining single-stage launch vehicle for scientific observation hybrid rocket engine using solid fuel and liquid oxidizer |
| url | https://www.jstage.jst.go.jp/article/transjsme/80/818/80_2014trans0287/_pdf/-char/en |
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