@inproceedings{oai:jaxa.repo.nii.ac.jp:00002944,
 author = {住元, 剛志 and 千葉, 一永 and 金崎, 雅博 and 藤川, 貴弘 and 米本, 浩一 and Sumimoto, Tsuyoshi and Chiba, Kazuhisa and Kanazaki, Masahiro and Fujikawa, Takahiro and Yonemoto, Koichi},
 book = {宇宙航空研究開発機構特別資料: 第50回流体力学講演会/第36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 50th Fluid Dynamics Conference / the 36th Aerospace Numerical Simulation Symposium},
 month = {Feb},
 note = {第50回流体力学講演会/第36回航空宇宙数値シミュレーション技術シンポジウム (2018年7月4日-6日. 宮崎市民プラザ), 宮崎市, 宮崎, 50th Fluid Dynamics Conference /the 36th Aerospace Numerical Simulation Symposium (July 4-6, 2018. Miyazaki Citizen's Plaza), Miyazaki, Japan, We have implemented the design optimization of the three-dimensional geometry for a two-stage-to-orbit flyback booster under six objective functions regarding aerodynamics, aerodynamic heating, and structures to obtain the knowledge for designing reusable launch vehicle. It is important to view the relationship among the objective functions of other fields with aerodynamic heating under designing spacecraft. We defined many-objective problem to execute more realistic configuration design based on WInged REusable Sounding rocket of Kyushu Institute of Technology and feedback the design knowledge. Accordingly, we used evolutionary computation as the optimization method and applied Strength Pareto Evolutionary Algorithm 2 as evolutionary algorithm for searching design variable space and getting design information. Moreover, data analysis was carried out for the optimization result to reveal information in the design space. Consequently, we need to consider the strictly different design strategy for the speed range between the transonic and the supersonic as well as hypersonic conditions. We also revealed that the design strategy of configuration which improves each objective function., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1830029015, レポート番号: JAXA-SP-18-005},
 pages = {141--146},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {最適飛行経路を持つ翼胴一体型フライバックブースタ段形状の空力/空力加熱/構造重量最適設計},
 volume = {JAXA-SP-18-005},
 year = {2019}
}