@inproceedings{oai:jaxa.repo.nii.ac.jp:00017259,
 author = {下山, 幸治 and 藤井, 孝蔵 and 小林, 弘明 and Shimoyama, Koji and Fujii, Kozo and Kobayashi, Hiroaki},
 book = {宇宙輸送シンポジウム　平成15年度, Proceedings of Space Transportation Symposium FY2003},
 month = {Apr},
 note = {A multi-objective optimization and a robust optimization are developed as a realistic comprehensive optimization method of the TSTO spaceplane. The result of the multi-objective optimization reveals the strong trade-off relation between the gross take-off weight and the Orbiter separation time minimizations. The propulsion parameter that controls the flow rate of captured air during the supersonic flight turns out to play an important role in this trade-off relation. The result of the robust optimization, in consideration of both the objective function optimality and robustness of the gross take-off weight, shows that the use of larger thrust engine with less fuel leads to the improvement of the optimality. On the other hand, the most robustest design did not coincide with the lightest gross take-off weight design. This result indicates that balancing the amount of fuel with the engine thrust is necessary for the improvement of the robustness., 資料番号: AA0047118029},
 pages = {113--116},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)},
 title = {TSTO統合最適設計の高度化:多目的問題への拡張とロバスト最適化の導入},
 year = {2004}
}