@inproceedings{oai:jaxa.repo.nii.ac.jp:00003490,
 author = {千葉, 一永 and 金崎, 雅博 and 嶋田, 徹 and Chiba, Kazuhisa and Kanazaki, Masahiro and Shimada, Toru},
 book = {宇宙航空研究開発機構特別資料: 第48回流体力学講演会/第34回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 48th Fluid Dynamics Conference / the 34th Aerospace Numerical Simulation Symposium},
 month = {Dec},
 note = {第48回流体力学講演会/第34回航空宇宙数値シミュレーション技術シンポジウム (2016年7月6日-8日. 金沢歌劇座), 金沢市, 石川, 48th Fluid Dynamics Conference /the 34th Aerospace Numerical Simulation Symposium (July 6-8, 2016. The Kanazawa Theatre), Kanazawa, Ishikawa, Japan, The objective of this study is to reveal extinction-reignition ascendancy, which is one of the beneficial points of hybrid rocket, for expanding downrange and duration in the lower thermosphere in view of simple control of oxidizer mass flow. Swirling-flow oxidizer is furnished with solid fuel; we adopt polypropylene for solid fuel and liquid oxygen for oxidizer. A multidisciplinary design optimization has been implemented by using a hybrid evolutionary computation; data mining has been also conducted by using a scatter plot matrix to efficiently perceive the entire design space. It is consequently revealed that the hypothesis in the prior study is proved; extinction-reignition extends not only duration but also, downrange. Scatter plot matrix results express physical mechanisms of design-variable behaviors for the objective functions and also the roles of the design variables via bird's-eye visualization of the entire design space constitution., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630031015, レポート番号: JAXA-SP-16-007},
 pages = {131--136},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {Effective operations of hybrid-rocket extinction-reignition via oxidizer-mass-flow control},
 volume = {JAXA-SP-16-007},
 year = {2016}
}