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

Material type: 文書・図像類

Author: 岩崎, 文哉ほか

Publisher: 宇宙航空研究開発機構

Publication date: 2006-11-01

Material Format: Digital

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Note (General)：: In the past, space propulsion systems were usually composed by accumulating the optimum design results for each component device. Therefore, 'system r...

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Material Type: 文書・図像類
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
Author/Editor: 岩崎, 文哉
倉谷, 尚志
青木, 宏
吉田, 誠
高田, 仁志
木村, 俊哉
長田, 敦
Iwasaki, Fumiya
Kuratani, Naoshi
Aoki, Hiroshi
Yoshida, Makoto
Takada, Hitoshi
Kimura, Toshiya
Osada, Atsushi
Author Heading: 岩崎, 文哉
倉谷, 尚志
青木, 宏
吉田, 誠
高田, 仁志
木村, 俊哉
長田, 敦
Iwasaki, Fumiya
Kuratani, Naoshi
Aoki, Hiroshi
Yoshida, Makoto
Takada, Hitoshi
Kimura, Toshiya
Osada, Atsushi
Publication, Distribution, etc.: 宇宙航空研究開発機構
Publication Date: 2006-11-01
Publication Date (W3CDTF): 2006-11-01
Alternative Title: Integrated design methodology for highly reliable liquid rocket engine: Analytical modeling and experimental investigation of failure mechanism for engine dynamic simulator
Periodical title: 宇宙航空研究開発機構特別資料: 平成18年度　宇宙航空研究開発機構　総合技術研究本部　宇宙科学研究本部　研究成果報告書 = JAXA Special Publication: Report on Research Achievements for FY2006 Institute of Space and Astronautical Science, Institute of Aerospace Technology, Japan Aerospace Exploration Agency
No. or year of volume/issue: JAXA-SP-06-006
Volume: JAXA-SP-06-006
Pages: 81-86
ISSN (Periodical Title): ISSN : 1349-113X
Text Language Code: jpn
Subject Heading: 信頼性
ロケットエンジン設計
宇宙推進システム
宇宙機推進
故障解析
シミュレーション
動的シミュレータ
燃焼試験
エンジン試験
液体燃料ロケットエンジン
reliability
rocket engine design
space propulsion system
spacecraft propulsion
failure analysis
simulation
dynamic simulator
combustion test
engine test
liquid propellant rocket engine
Target Audience: 一般
Note (General): 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
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=6001&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=6001&item_no=1&attribute_id=31&file_no=1
Access Restrictions: 限定公開
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ