Výsledky vyhledávání - "燃焼試験"

Research and development of ejector rocket for combined cycle engine: Design and production of clustered rocket chamber for combined cycle engine

Autor: Takegoshi, Masao, Tomioka, Sadatake, Ueda, Shuichi, Saito, Toshihito, Izumikawa, Muneo

Publikováno v: 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. :111-116

A gaseous hydrogen/gaseous oxygen rocket chamber was designed to fit in a rocket-ramjet combined cycle engine model, and its performance was evaluated experimentally. Such a rocket chamber is required to operate in a very wide operation range in term

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::0c847c82a12ac94ecd702fc46f9ca288
http://id.nii.ac.jp/1696/00006002/

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Development of ceramic thruster

Autor: Nakatsuka, Junichi, Sawai, Shujiro

In recent days, the propulsion subsystem of spacecraft is required to achieve higher reliability and performance simultaneously. The performance of thrusters has a great impact to the weight budget of the propulsion subsystem, because high performanc

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::afc91331a453142b9837fdbed5694976
http://id.nii.ac.jp/1696/00006039/

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Integrated design methodology for highly reliable liquid rocket engine: Analytical modeling and experimental investigation of failure mechanism for engine dynamic simulator

Autor: Iwasaki, Fumiya, Kuratani, Naoshi, Aoki, Hiroshi, Yoshida, Makoto, Takada, Hitoshi, Kimura, Toshiya, Osada, Atsushi

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 re

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::861d66eab22220e8b7bd86d8d6bd7e23
http://id.nii.ac.jp/1696/00005995/

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The results of propulsion system firing test for HTV

Autor: Nagata, Taiichi, Kajiwara, Kenichi, Imada, Takane, Sasaki, Hiroshi

Publikováno v: 宇宙航空研究開発機構特別資料: 平成16年度総合技術研究本部宇宙領域宇宙科学研究本部合同研究成果報告書:宇宙輸送系基盤技術 = JAXA Special Publication: FY2004 Report of Joint Research Achievements of the Space Division of Institute of Aerospace Technology and Institute of Space and Astronautical Science: Basic Technologies of Space Transportation Systems. :93-98

The system firing test for HTV (H-2 Transfer Vehicle) was performed on June thru August, 2004. The result shows that the system provides approximately 50 percent thrust during short impulse RCS firings using four forward thrusters with GHe saturated

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::ff532a8857bddd3f5f350041748c143d
http://id.nii.ac.jp/1696/00006244/

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Research and development of ejector rocket for combined cycle engine: Research of rocket engine with variable combustion pressure and variable mixture ratio

Autor: Takegoshi, Masao, Tomioka, Sadatake, Ueda, Shuichi, Saito, Toshihito, Izumikawa, Muneo

A gaseous hydrogen/gaseous oxygen rocket chamber was designed to fit to a Rocket-Based-Combined-Cycle engine model, and its performances were evaluated experimentally. The rocket chamber was required to operate at a very wide operation range in terms

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::27d9a1d21765ee6e7e26bfd844fea711
http://id.nii.ac.jp/1696/00006241/

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Research on an extendible nozzle: Characteristics of dynamic loads acting on an extendible nozzle

Autor: Hasegawa, Keiichi, Kusaka, Kazuo, Sato, Masahiro, Tadano, Makoto, Moriya, Shinichi, Sato, Masaki

An extendible nozzle is considered to be a feasible device to improve the performance of booster engines because it has possibilities to provide altitude compensation and to achieve higher specific impulse. The booster engines with the extendible noz

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::585a1bcf2e9f832d1cb40c27db1b5052
http://id.nii.ac.jp/1696/00006234/

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Overview of the investigation of failure causes of ADEOS-2

Autor: Takahashi, Masato

Publikováno v: 宇宙航空研究開発機構特別資料: 第1回宇宙環境シンポジウム報告書 = JAXA Special Publication: Proceedings of the First Spacecraft Environment Symposium. :84-92

2003年10月25日(JST)に、環境観測技術試験衛星みどり2(ADEOS-2)の太陽電池パドル発生電力が6kWから1kWに低下する事象が発生し、衛星全損に至る不具合となった。原因調査の結果、電力ハーネ�

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::6661557ca15a1751b45729a44e41a62d
http://id.nii.ac.jp/1696/00006503/

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Design of a small ethanol engine

Autor: Otake, Juri, Shiobara, Tatsuro, Suzuki, Hibiki, Watanabe, Yuichi, Yatsuyanagi, Nobuyuki

Publikováno v: 宇宙輸送シンポジウム平成15年度 = Proceedings of Space Transportation Symposium FY2003. :57-60

資料番号: AA0047118015

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::e9d9a246bb106272f4f37201ff5e04bd
http://id.nii.ac.jp/1696/00017239/

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Overview of the nozzle liner erosion during solid rocket motor combustion and its measurement system

Autor: Otsuka, Hidekazu, Yamamoto, Yoichi, Ito, Koji

Publikováno v: 宇宙輸送シンポジウム平成14年度 = Proceedings of Space Transportation Symposium FY2002. :5-8

資料番号: AA0045426002

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::830f8e9dca7159c6f76c488b1a4b83b7
http://id.nii.ac.jp/1696/00017332/

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Experimental investigation of a fuel-cooled flameholder for a ramjet engine combustor

Autor: Kurosawa, Yoji, Yamamoto, Takeshi, Saito, Takashi, Tamaru, Suguru

Publikováno v: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory. 1384:1-22

航空宇宙技術研究所では、宇宙往還機用エアブリージングエンジンに用いるラムジェットエンジン用燃焼器(以降、ラム燃焼器)の基礎研究を進めている。その研究の一環として、水素燃�

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::6dc93ede1aa680029f145364ffba8c39
http://id.nii.ac.jp/1696/00040605/

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