H-2AロケットおよびLNG推進系の開発を支援するCFD解析

Material type: 文書・図像類

Author: 清水, 和弥ほか

Publisher: 宇宙航空研究開発機構

Publication date: 2004-10-29

Material Format: Digital

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Note (General)：: Numerical simulation has been carried out to support the development of the H-2A launch vehicle and the LNG propulsion system. Numerical results revea...

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Material Type: 文書・図像類
Title: H-2AロケットおよびLNG推進系の開発を支援するCFD解析
Author/Editor: 清水, 和弥
伊藤, 隆
根岸, 秀世
清水, 太郎
山西, 伸宏
Shimizu, Kazuya
Ito, Takashi
Negishi, Hideyo
Shimizu, Taro
Yamanishi, Nobuhiro
Author Heading: 清水, 和弥
伊藤, 隆
根岸, 秀世
清水, 太郎
山西, 伸宏
Shimizu, Kazuya
Ito, Takashi
Negishi, Hideyo
Shimizu, Taro
Yamanishi, Nobuhiro
Publication, Distribution, etc.: 宇宙航空研究開発機構
Publication Date: 2004-10-29
Publication Date (W3CDTF): 2004-10-29
Alternative Title: Numerical analysis to support the development of H-2A launch vehicle and LNG propulsion system
Periodical title: 宇宙航空研究開発機構研究開発資料: 平成15年度総合技術研究本部宇宙領域研究成果報告書:輸送系 = JAXA Research and Development Memorandum: FY15 Annual Report of Research & Development on Space Technology in the Institute of Space Technology and Aeronautics: Space Transportation System
No. or year of volume/issue: JAXA-RM-04-009
Volume: JAXA-RM-04-009
Pages: 31-36
ISSN (Periodical Title): ISSN : 1349-1121
Text Language Code: jpn
Subject Heading: 数値解析
H-2Aロケット
固体ロケットブースター
LNG
CFD
燃焼器
火炎温度
エンジン性能
numerical analysis
H-2A rocket
solid rocket booster
combustion chamber
flame temperature
engine performance
Target Audience: 一般
Note (General): Numerical simulation has been carried out to support the development of the H-2A launch vehicle and the LNG propulsion system. Numerical results reveal the mixed flow field with hot hydrogen and cold hydrogen in a liquid rocket engine of the H-2A. The local erosion results from the change of the heat flux to the concavity and convexity of the fin in the solid rocket booster (SRB-A). In the LNG propulsion system, it is indicated from the numerical evaluation that the increase of the pressure in the combustion chamber and the decrease in the chemical non-equilibrium loss are required in order to improve the engine performance. The effect of the film cooling inside the igniter is shown and the flame temperature was estimated. The consumption of helium gas at the flight is evaluated by the numerical analysis.
資料番号: AA0047944007
レポート番号: JAXA-RM-04-009
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=2738&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=2738&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