@techreport{oai:jaxa.repo.nii.ac.jp:00002736,
 author = {佐藤, 哲也 and 田口, 秀之 and 下平, 一雄 and 小林, 弘明 and 岡井, 敬一 and 岩瀬, 識 and 二村, 尚夫 and 森本, 哲也 and 小島, 孝之 and 藤田, 和央 and Sato, Tetsuya and Taguchi, Hideyuki and Shimodaira, Kazuo and Kobayashi, Hiroaki and Okai, Keiichi and Iwase, Shiki and Futamura, Hisao and Morimoto, Tetsuya and Kojima, Takayuki and Fujita, Kazuhisa},
 month = {Oct},
 note = {Development studies on a hypersonic turbo jet engine have been conducted to be employed to the reusable space transportation. As this mid-term target, it is proposed that a subscale prototype engine will be produced and demonstrated under sea-level-static and supersonic conditions (Mach 6) for getting fundamental key technologies and valuable experiences. Engine system optimization analyses for an actual TSTO space plane by the precise components data on the performance and weight as well as the dynamic characteristics along the accelerating trajectory is also investigated. In this year, fundamental key results were obtained by a trade-off study to decide the prototype engine cycle, a study of the defrosting system on the precooler (a cryogenic heat exchanger), wind tunnel tests of air inlets and nozzles and an application study of the composite materials., 資料番号: AA0047944005, レポート番号: JAXA-RM-04-009},
 title = {極超音速ターボジェットエンジンの研究開発},
 year = {2004}
}