http://swrc.ontoware.org/ontology#InProceedings
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
ja
Aerospike; Modeling; Propulsion
髙橋 英美
富田 健夫
櫻中 登
Takahashi Hidemi
Tomita Takeo
Sakuranaka Noboru
日本航空宇宙学会(JSASS)
The Japan Society for Aeronautical and Space Sciences(JSASS)
第57回宇宙科学技術連合講演会講演集
2013-10
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