@inproceedings{oai:jaxa.repo.nii.ac.jp:00016716,
 author = {吉田, 誠 and 成尾, 芳博 and 丹生, 謙一 and Yoshida, Makoto and Naruo, Yoshihiro and Niu, Kenichi},
 book = {宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium},
 month = {},
 note = {平成20年度宇宙輸送シンポジウム(2009年1月19日-20日, 宇宙航空研究開発機構宇宙科学研究本部), A 40 kN rocket engine development has been initiated relating to the reusable sounding rocket, which is also developed in Japan. This rocket vertically takes off, reaches to 100 km altitude, lands vertically on the launch site and is launched again within several days. This rocket will provide observation mission chances with low cost and with quickness utilizing the advantages of reusability. This program has been authorized as a technology demonstration phase, and most of the technologies required for the vehicle are to be demonstrated in a few years. In order to realize this rocket concept, the engines installed on the rocket should have features of reusability, long life, deep throttling and health monitoring. Those have not yet been established in Japanese rocket engines. In this paper, development status of the engine is mentioned, including fundamental design and engineering tests of turbopump bearing and seal. Also program prospect relating with the other engine development programs in Japan are also presented., 形態: カラー図版あり, 資料番号: AA0064292023},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {再使用観測ロケット主推進系の進捗状況},
 volume = {平成20年度},
 year = {2009}
}