@techreport{oai:jaxa.repo.nii.ac.jp:00045111,
 author = {日下, 和夫 and 黒田, 行郎 and 佐藤, 政裕 and 只野, 真 and 飯原, 重保 and KUSAKA, Kazuo and KURODA, Yukio and SATO, Masahiro and TADANO, Makoto and IIHARA, Shigeyasu},
 month = {Feb},
 note = {High altitude simulation tests of a storable engine with a thrust of 500 N and a chamber pressure of 700 kpa were conducted to evaluate the nozzle performance at low thrust and low chamber pressure. Since the available facility did not allow tests of such an engine, an auxiliary annular ejector/diffuser system was developed. Two injectors, one with 15％ fuel film cooling and the other 25％, were used. A comparison of performances between nitrogen tetroxide/monomethyl hydrazine (NTO/MMH) and nitrogen tetroxide/hydrazine propellant systems was made. A vacuum specific impulse of 305 seconds was obtained with NTO/MMH and a 150:1 area ratio nozzle at a energy release efficiency of 95％. By altering fuel from MMH to hydrazine, a peak specific impulse of 317 seconds was measured with 25％ film cooling and a 150:1 nozzle. Large area ratio specific impulses can be predicted generally within 0.5％ when energy release efficiencies are evaluated from sea level thrust measurements with a low area ratio nozzle., 資料番号: NALTR0853000, レポート番号: NAL TR-853},
 title = {低推力貯蔵性推進薬エンジンの高空性能},
 year = {1985}
}