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クラスタ型リニアエアロスパイクエンジン性能予測手法の検討
https://jaxa.repo.nii.ac.jp/records/38611
https://jaxa.repo.nii.ac.jp/records/38611fb4afc86-980d-4b4f-9e3d-991b6428a9cd
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 | クラスタ型リニアエアロスパイクエンジン性能予測手法の検討 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Aerospike; Modeling; Propulsion | |||||
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 | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Study on Performance Prediction Model of Clustered Linear Aerospike Engines | |||||
著者 |
髙橋, 英美
× 髙橋, 英美× 富田, 健夫× 櫻中, 登× Takahashi, Hidemi× Tomita, Takeo× Sakuranaka, Noboru |
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著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
出版者 | ||||||
出版者 | 日本航空宇宙学会(JSASS) | |||||
出版者(英) | ||||||
出版者 | The Japan Society for Aeronautical and Space Sciences(JSASS) | |||||
書誌情報 |
第57回宇宙科学技術連合講演会講演集 en : Proceedings of 57th Space Sciences and Technology Conference 発行日 2013-10 |
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会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 第57回宇宙科学技術連合講演会(2013年10月9日-11日. 米子コンベンションセンター(BiG SHiP)), 米子市, 鳥取県 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | A performance prediction model for a clustered linear aerospike engine system has been established. The model predictsnot only thrust performance but also thrust-to-weight ratio. Aerodynamic performance calculation is first implementedthat involves spike contour design. Then the overall engine weight is calculated based on the spike geometry. Severalassumptions were given; external air condition is still-air condition, base pressures, skin friction drag obeyssemi-empirical models. Other minor assumptions were also given when calculating cell nozzle divergence angle and walltemperature. Spike surface pressure was calculated based on the method of characteristics. Predicted performance fornon-clustered two-dimensional linear aerospike nozzle with full-length was compared to that of bell-shaped nozzle whichprovides an ideal performance. The comparison indicated reasonable trend: aerospike nozzle has the maximum thrustcoefficient at in-vacuum condition of almost the same as that of bell-shaped nozzle, but has higher at sea level condition.The established model was thus confirmed to be valid. The model was expanded so that the model can predict a Paretooptimal solution of performance with some given parameters. | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AC1400027000 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: JSASS-2013-4277 |