@inproceedings{oai:jaxa.repo.nii.ac.jp:00006621,
 author = {木村, 俊哉 and 高橋, 政浩 and 若松, 義男 and 長谷川, 恵一 and 山西, 伸宏 and Kimura, Toshiya and Takahashi, Masahiro and Wakamatsu, Yoshio and Hasegawa, Keiichi and Yamanishi, Nobuhiro},
 book = {宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2003論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2003},
 month = {Mar},
 note = {The Rocket Engine Dynamic Simulator (REDS) has been developed. REDS is a kind of simulation tool to simulate and examine unsteady behavior of a rocket engine. A rocket engine is modeled as a system of pipes with various hydraulic elements such as turbopumps, turbines, valves, orifices, etc. Flows of fuel oxidizer and combustion gas are simulated by solving conservative equations with calculations of their phase changes and physical properties. The motion of turbopumps and turbines are solved coupling with flow equations. The heat exchange between fluid and walls is also calculated and incorporated into the energy state of fluids. In the present version of REDS, the simulation code has been developed to simulate the unsteady behavior such as a startup and a shutdown of a staged combustion cycle engine, which has been applied to Japanese launch vehicles H-2 and H-2A. The validity of REDS has been checked by comparing with the combustion test data, and the results showed high capability in reproduction of unsteady response in startup and shutdown and steady state working condition. REDS has been constructed with flexibility to apply to any configuration of a rocket engine and is expected to contribute to research and development of a next generation rocket engine., 資料番号: AA0047427020, レポート番号: JAXA-SP-03-002},
 pages = {107--112},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {ロケットエンジン動的シミュレータ(REDS)},
 volume = {JAXA-SP-03-002},
 year = {2004}
}