@techreport{oai:jaxa.repo.nii.ac.jp:00006001,
 author = {岩崎, 文哉 and 倉谷, 尚志 and 青木, 宏 and 吉田, 誠 and 高田, 仁志 and 木村, 俊哉 and 長田, 敦 and Iwasaki, Fumiya and Kuratani, Naoshi and Aoki, Hiroshi and Yoshida, Makoto and Takada, Hitoshi and Kimura, Toshiya and Osada, Atsushi},
 month = {Nov},
 note = {In the past, space propulsion systems were usually composed by accumulating the optimum design results for each component device. Therefore, 'system reliability level' was measured by long-time development tests. Recently, the new design method is required to predict 'system reliability level' at the conceptual design phase, to grasp and to optimize the distribution of 'risks and margins' because attainable 'system reliability level' strongly depends on its basic concept. This paper describes some sample approaches to measure 'system reliability level', focusing on analytical modeling of failure mechanism for rocket engine dynamic simulator. Some design parameters are picked up to understand where and how their dispersion makes an effect in the whole systems and to control the total system robustness., 資料番号: AA0049500017, レポート番号: JAXA-SP-06-006},
 title = {ロケットエンジン高信頼化設計手法の研究:動的故障モデル、限界試験結果反映の取り組み},
 year = {2006}
}