研究者詳細 - 北川　幸樹

論文 - 北川　幸樹

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科学観測用単段式ハイブリッドロケット概念設計への設計情報学の実運用査読有り

千葉一永, 金崎雅博, 中宮賢樹, 北川幸樹, 嶋田徹

進化計算学会論文誌 ( 進化計算学会 ) 4 ( 3 ) 85 - 95 2013年11月

CHARACTERISTICS OF CHEMICALLY MODIFIED AND NANOCOMPOSITE POLYMERS AS NOVEL FUELS FOR HYBRID ROCKET PROPULSION 査読有り国際誌

Koki Kitagawa, Paul Joseph, Vasily Novozhilov, Toru Shimada

International Journal of Energetic Materials and Chemical Propulsion 11 ( 6 ) 549 - 566 2013年11月

Conceptual Design of Single-Stage Launch Vehicle with Hybrid Rocket Engine for Scientific Observation Using Design Informatics 査読有り国際誌

Kazuhisa CHIBA, Masahiro KANAZAKI, Masaki NAKAMIYA, Koki KITAGAWA, Toru SHIMADA

Journal of Space Engineering ( 日本機械学会 ) 6 ( 1 ) 15 - 27 2013年09月

Burning rate anomaly of composite propellant grains 査読有り国際誌

H. Hasegawa, M. Fukunaga, K. Kitagawa, T. Shimada

Combustion, Explosion, and Shock Waves 49 ( 5 ) 583 - 592 2013年09月

Low-Frequency Feed-System-Coupled Combustion Instability in Hybrid Rocket Motors 査読有り国際誌

Takakazu MORITA, Saburo YUASA, Koki KITAGAWA, Toru SHIMADA, Shigeru YAMAGUCHI

Journal of Thermal Science and Technology ( 日本機械学会 ) 8 ( 2 ) 380 - 394 2013年07月

Multi-Stage Hybrid Rocket Conceptual Design for Micro-Satellites Launch using Genetic Algorithm 査読有り

Yosuke KITAGAWA, Koki KITAGAWA, Masaki NAKAMIYA, Masahiro KANAZAKI, Toru SHIMADA

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN ( 一般社団法人日本航空宇宙学会 ) 55 ( 4 ) 229 - 236 2012年07月

LIQUID OXYGEN VAPORIZATION TECHNIQUES FOR SWIRLING-OXIDIZER-FLOW-TYPE HYBRID ROCKET ENGINES 査読有り国際誌

Saburo Yuasa, Koki Kitagawa, Toshiaki Sakurazawa, Ikuno Kumazawa, Takashi Sakurai

International Journal of Energetic Materials and Chemical Propulsion 10 ( 2 ) 155 - 168 2011年04月

推力1500N級酸化剤流旋回型ハイブリッドロケットエンジン用LOX気化ノズルの評価燃焼実験査読有り

北川幸樹, 桜沢俊明, 湯浅三郎

宇宙技術 ( 日本航空宇宙学会 ) 6 47 - 54 2007年01月

担当区分：筆頭著者記述言語：日本語掲載種別：研究論文（学術雑誌）

液体酸素（LOX）を用いた酸化剤流旋回型ハイブリッドロケットエンジンでは，インジェクターより上流でLOXを気化する必要がある．筆者らは，LOXを気化する方法の一つとして，再生冷却方式のLOX気化ノズルを提案している．本研究では，推力1500N用のLOX気化ノズルを設計製作し，設計値より低い酸素流量と燃焼室圧条件において独立気化方式と再生冷却方式による気化燃焼実験を行った．独立気化方式の気化実験によって，LOXの気化とノズルの安全性が確認され，数値計算によるLOX気化ノズルの設計が適切であることが分かった．再生冷却方式の気化燃焼実験では，確実な着火と安定した燃焼が得られ，LOX気化ノズルを用いた酸化剤流旋回型ハイブリッドロケットエンジンの自立燃焼に成功した．また，LOXを気化させることで，LOXに直接旋回を与える場合より燃料後退速度やC*効率を向上できた．

DOI： 10.2322/stj.6.47

Kyutacar

Combustion Characteristics of Mg Vapor Jet Flames in CO2 Atmospheres 査読有り国際誌

Yuasa Saburo, Sakoda Kou, Aizawa Shinri, Kitagawa Koki

Proceedings of the Combustion Institute ( Elsevier ) 31 ( 2 ) 2037 - 2044 2007年01月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

ドイツハイデルベルグ

An experimental study was performed on the combustion characteristics of a jet diffusion flame of Mg vapor injected through a small nozzle into CO2 atmospheres at low pressures from 8 to 48 kPa with a view to using Mg as fuel for a CO2-breathing turbojet engine in the Mars atmosphere. The Mg vapor jet produced three types of the flame. At lower pressures and higher injection velocities, a red-heated jet flame formed, in which the injected Mg vapor was heated by spontaneous reactions, turning red. At medium pressures and injection velocities, a stable luminous lifted-like flame developed above the rim of the chimney, a tube-like combustion product for the Mg vapor passage that grew on the nozzle during combustion. The flame had similar flame length properties to laminar jet diffusion flames of gaseous fuels. At higher pressures and lower injection velocities, a stable luminous attached flame developed at the rim of the chimney. The same reactions, producing MgO(g), CO and MgO(c), proceeded preferentially for all flames and chimneys. Carbon was only subordinately generated. Burning behavior of Mg vapor jets in a CO2 atmosphere has been represented, including the homogeneous reaction of Mg vapor with CO2, the diffusion of CO2, and the condensation and deposit of MgO. The injection velocity of Mg vapor at the rim of the chimney and the exothermic reactions with diffused CO2 that occur there play a crucial role in the attachment and development of the flames. The flame structure may be explained in terms of the relatively low gas-phase reaction rate of Mg with CO2.

DOI： 10.1016/j.proci.2006.07.192

液体酸素旋回型ハイブリッドロケットエンジンの燃焼特性査読有り

北川幸樹, 湯浅三郎

日本航空宇宙学会論文集 ( 日本航空宇宙学会 ) 54 ( 629 ) 242 - 249 2006年06月

担当区分：筆頭著者記述言語：日本語掲載種別：研究論文（学術雑誌）

We have proposed a swirling oxidizer type hybrid rocket engine. In this paper, liquid oxygen (LOX) was used as oxidizer. Combustion tests of a hybrid rocket engine with a swirling LOX flow were conducted by changing the swirl strength. Ignition was rapid and reliable, and combustion of PMMA with swirling LOX was stable. Fuel regression rates, C* efficiency and specific impulse of the hybrid rocket engine with swirling LOX flow were smaller than those with swirling gaseous oxygen (GOX). This low performance may be restraint of atomization and vaporization of LOX by formation of a liquid layer on the PMMA fuel and a decline of angular momentum of the swirling LOX during vaporization. Combustion oscillation occurred when the ratios of differential pressure between injector pressure and chamber pressure to chamber pressure were small. This combustion oscillation was confirmed to be a “Chugging” mode due to combustion time lag of LOX.

DOI： 10.2322/jjsass.54.242

Kyutacar

大学における小型再使用打上げシステムの開発研究その2：酸化剤旋回型小型ハイブリッドロケットの開発と打上げ査読有り

湯浅三郎,山本研吾,蜂谷仁司,北川幸樹

日本航空宇宙学会誌 53 ( 616 ) 13 - 19 2005年05月

Current Status of Rocket Developments in Universities -Development of a Small Hybrid Rocket with a Swirling Oxidizer Flow Type Engine 査読有り

Saburo YUASA, Koki KITAGAWA

The Journal of Space Technology and Science ( 日本ロケット協会 ) 21 ( 1 ) 1_1 - 1_11 2005年01月

記述言語：英語掲載種別：研究論文（学術雑誌）

To develop an experimental small hybrid rocket with a swirling gaseous oxygen flow type engine, we made a flight model engine. Burning tests of the engine showed that a maximum thrust of 692 N and a specific impulse of 263 s (at sea level) were achieved. We designed a small hybrid rocket with this engine. The rocket measured 1.8 m in length and 15.4 kg in mass. To confirm the flight stability of the rocket, wind tunnel tests using a 112-scale model of the rocket and simulations of the flight attitude and trajectory were carried out. A flight test was conducted at Taiki-cho, Hokkaido, Japan on March 2001. The rocket reached an altitude of about 600 m, thus recording the first successful flight of a hybrid rocket in Japan. For the next stage, future issues to develop larger hybrid rockets using a swirling liquid oxygen flow type engine are discussed, and preliminary burning tests of the engine have been carried out.

DOI： 10.11230/jsts.21.1_1

Kyutacar

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