@inproceedings{oai:jaxa.repo.nii.ac.jp:00017270,
 author = {小川, 博之 and 野中, 聡 and 谷口, 浩文 and 青木, 宏 and Ogawa, Hiroyuki and Nonaka, Satoshi and Taniguchi, Hirofumi and Aoki, Hiroshi},
 book = {宇宙輸送シンポジウム　平成15年度, Proceedings of Space Transportation Symposium FY2003},
 month = {Apr},
 note = {A baseline configuration of the reusable rocket demonstration vehicle is presented. The vehicle adopts a vertical take-off and vertical landing (VTVL) system to minimize ground support equipments (GSE) and turn-around time. The integrated propulsion system which consists of four LH2/LOX expander cycle engines, GH2/GOX reaction control system (RCS) and an assist power unit (APU). The vehicle is designed to meet the requirements of carrying 100 kg payload on a round trip to 120 km and repeating the mission within 24 hours., 資料番号: AA0047118040},
 pages = {158--161},
 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/ISAS)},
 title = {再使用観測ロケットのシステム検討},
 year = {2004}
}