@inproceedings{oai:jaxa.repo.nii.ac.jp:00016724,
 author = {富岡, 定毅 and 加藤, 周徳 and 谷, 香一郎 and 植田, 修一 and Tomioka, Sadatake and Kato, Kanenori and Tani, Koichiro and Ueda, Shuichi},
 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), One-dimensional simulation was carried out on a rocket-ramjet combined cycle engine model under of ramjet-mode (dual mode combustion) operation. Combustion efficiency distribution was given with an empirical equation for dual-mode scramjet combustors. Pressure recovery with pseudo-shock system was represented with a normal shock wave, and its location was so selected to attain thermal choking at designated locations. The simulation was carried out for several fuel flow rates and injection locations to show that the ramjet-mode operation with thermal choking at the engine model exit observed often in the experiments can be simulated one-dimensionally. The pressure level after the pressure recovery was over-estimated in the present study, so that modeling pseudo-shock system in one-dimensional sense must be included in the simulation. Combustion efficiency was also overestimated to attain thermal choking at the engine model exit at equivalence ration close to unity, so that the empirical equation should be modified for more precise simulation., 資料番号: AA0064292031},
 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 = {ロケット-ラムジェット複合エンジンのラムジェットモード作動の解析},
 volume = {平成20年度},
 year = {2009}
}