@inproceedings{oai:jaxa.repo.nii.ac.jp:00038611,
 author = {髙橋, 英美 and 富田, 健夫 and 櫻中, 登 and Takahashi, Hidemi and Tomita, Takeo and Sakuranaka, Noboru},
 book = {第57回宇宙科学技術連合講演会講演集, Proceedings of 57th Space Sciences and Technology Conference},
 month = {Oct},
 note = {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, 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: AC1400027000, レポート番号: JSASS-2013-4277},
 publisher = {日本航空宇宙学会(JSASS), The Japan Society for Aeronautical and Space Sciences(JSASS)},
 title = {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},
 year = {2013}
}