| Item type |
会議発表論文 / Conference Paper(1) |
| 公開日 |
2015-03-26 |
| タイトル |
|
|
タイトル |
Multi-Objective Design and Trajectory Optimization of Space Transport Systems with RBCC Propulsion via Evolutionary Algorithms and Pseudospectral Methods |
|
言語 |
en |
| 言語 |
|
|
言語 |
eng |
| 資源タイプ |
|
|
資源タイプ識別子 |
http://purl.org/coar/resource_type/c_5794 |
|
資源タイプ |
conference paper |
| アクセス権 |
|
|
アクセス権 |
metadata only access |
|
アクセス権URI |
http://purl.org/coar/access_right/c_14cb |
| 著者 |
小寺, 正敏
Ogawa, Hideaki
富岡, 定毅
植田, 修一
Kodera, Masatoshi
Ogawa, Hideaki
Tomioka, Sadatake
Ueda, Shuichi
|
| 著者所属 |
|
|
|
宇宙航空研究開発機構(JAXA) |
| 著者所属 |
|
|
|
ロイヤルメルボルン工科大学 |
| 著者所属 |
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宇宙航空研究開発機構(JAXA) |
| 著者所属 |
|
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宇宙航空研究開発機構(JAXA) |
| 著者所属（英） |
|
|
|
en |
|
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Japan Aerospace Exploration Agency(JAXA) |
| 著者所属（英） |
|
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|
en |
|
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Royal Melbourne Institute of Technology |
| 著者所属（英） |
|
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|
en |
|
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Japan Aerospace Exploration Agency(JAXA) |
| 著者所属（英） |
|
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en |
|
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Japan Aerospace Exploration Agency(JAXA) |
| 出版者（英） |
|
|
出版者 |
American Institute of Aeronautics and Astronautics(AIAA) |
| 書誌情報 |
発行日 2014-01
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| 会議概要（会議名, 開催地, 会期, 主催者等）（英） |
|
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内容記述タイプ |
Other |
|
内容記述 |
AIAA SciTech 2014, 52nd Aerospace Sciences Meeting （January 13-17, 2014. National Harbor), Maryland, United States. |
| 抄録（英） |
|
|
内容記述タイプ |
Other |
|
内容記述 |
In this study, a multi-objective design optimization coupling evolutionary algorithms and trajectory optimization via pseudo-spectral methods has been conducted for the first stage of two-stage to orbit (TSTO) system with a rocket-based combined cycle (RBCC) engine which combines rockets and ramjets by blending two kinds of vehicle configurations with different aerodynamic characteristics. The design criteria include the minimization of fuel consumption and the maximization of the final Mach number up to a separation of the TSTO system at the maximum altitude under certain ranges of acceleration and dynamic pressure. The optimization results reveal a counteractive trend between the final Mach number and fuel mass ratio and the major impact of effective specific impulse on those two objectives, which is mainly controlled by thrust throttling parameter within the trajectory optimization. In addition, the RBCC-powered vehicle tends to fly at lower altitude to attain the minimum fuel mass ratio, in contrast to the case for maximum final Mach number, which is attributed to the hybrid aerodynamic performance of the two configurations. The insight gained here can be usefully applied to the design of high-performance RBCC-poweredvehicles. |
| DOI |
|
|
|
識別子タイプ |
DOI |
|
|
関連識別子 |
http://dx.doi.org/10.2514/6.2014-0629 |
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|
関連名称 |
info:doi/10.2514/6.2014-0629 |
| 資料番号 |
|
|
内容記述タイプ |
Other |
|
内容記述 |
資料番号: AC1400045000 |
| レポート番号 |
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内容記述タイプ |
Other |
|
内容記述 |
レポート番号: AIAA2014-0629 |
