@inproceedings{oai:jaxa.repo.nii.ac.jp:00049483,
 author = {奈女良, 実央 and 藤浦, 彰友 and 中村, 祐太 and 中田, 大将 and 江口, 光 and 内海, 政春 and NAMERA, Mio and FUJIURA, Akitomo and NAKAMURA, Yuta and NAKATA, Daisuke and EGUCHI, Hikaru and UCHIUMI, Masaharu},
 book = {令和4年度宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium FY2022},
 month = {Jan},
 note = {令和4年度宇宙輸送シンポジウム（2023年1月12日-13日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)) , 相模原市, 神奈川県, Space Transportation Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, In this paper, describe a method of prediction for gas generator throttled combustion tests. In addition to the conventional method, the injector Cd was set small based on past test results. As a result, the LOX flow rate error at 70% throttle was improved from 10% to 1.3%. In addition, for flight operation, the propellant orifice diameter was examined for the feed-line resistance of the control valves., 資料番号: SA6000184027, STCP-2022-027},
 publisher = {宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS), Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)},
 title = {LOX/エタノールガスジェネレータの高精度流量予測に関する研究},
 year = {2023}
}