@techreport{oai:jaxa.repo.nii.ac.jp:00045218,
 author = {渡辺, 光男 and 長谷川, 敏 and 上條, 謙二郎 and 青木, 宏 and WATANABE, Mitsuo and HASEGAWA, Satoshi and KAMIJO, Kenjiro and AOKI, Hiroshi},
 month = {Feb},
 note = {Recently, a two-stage combustion cycle has been applied to liquid rocket engines in order to obtain high performance. However, the engine cycle inevitably requires extremely high pressure propellant feed pumps which require quite high technology. In order to investigate the characteristics of high pressure cryogenic pumps, a small high pressure and high speed liquid oxygen (LOX) pump was designed, fabricated and tested from 1980 to 1983 in the National Aerospace Laboratory (NAL) in cooperation with the National Space Development Agency of Japan (NASDA). It is a single-stage centrifugal pump with a three bladed helical inducer. The designed rotational speed is 47,500 rpm. Points of technology studied in the present experiments included establishing fluid dynamic design details and mechanical design details such as a thrust balancing system, and bearing and seal systems., 資料番号: NALTR0959000, レポート番号: NAL TR-959},
 title = {Experimental Study on High Pressure Liquid Oxygen Pump},
 year = {1988}
}