嶋田 徹

J-GLOBALへ         更新日: 18/05/17 12:16
 
アバター
研究者氏名
嶋田 徹
 
シマダ トオル
URL
http://www.isas.ac.jp/j/about/professor/s/shimada_toru.shtml
所属
(国)宇宙航空研究開発機構
部署
宇宙科学研究所 宇宙飛翔工学研究系
職名
教授

プロフィール

嶋田 徹(しまだ とおる)
宇宙航空研究開発機構 宇宙科学研究所 宇宙飛翔工学研究系 教授
1985年 東京大学大学院工学系研究科航空学専門課程修了・工学博士取得。1985年~2000年まで日産自動車(株)宇宙航空事業部にてロケットの設計解析に従事。2000年 旧文部省宇宙科学研究所(現:宇宙航空研究開発機構)助教授。2007年より同教授。2003年~2007年までM-Vロケットプロジェクト・ファンクションマネージャ。同ロケットの開発と打ち上げに従事。その間、北海道大学、総合研究大学院大学、東京大学で客員助教授を経て、2007年より東京大学大学院 客員教授。専門は宇宙推進流体工学、固体/ハイブリッドロケット内部の燃焼流の研究。低コストで安全なロケットの実現を目指し、2008年! よりハイブリッドロケット研究WGを主宰。

研究分野

 
 

学歴

 
 
 - 
1985年
東京大学 工学系研究科 航空学
 
 
 - 
1980年
京都大学 工学部 航空工学科
 

論文

 
Kenichi Takahashi, Rieko Doi, Takuo Kuwahara, Toru Shimada
Science and Technology of Energetic Materials   76 75-80   2015年
© 2015, Japan Explosives Society. All rights reserved. We conducted a three-dimensional numerical experiment to ascertain the luminous flame shape around a burning aluminum particle near the burning surface of composite propellant. To simulate the...
Masaki Adachi, Masaki Adachi, Toru Shimada
AIAA Journal   53 1578-1589   2015年6月
Copyright © 2014 by the authors. Copyright © Clearance Center, Inc. Numerical analysis on the instability of liquid/dense fluid films under supercritical operating conditions is performed on methane fuel. A numerical code for compressible fluid fl...
Akimasa Takayama, Koki Kitagawa, Toru Shimada
Journal of Mechanical Science and Technology   29 951-962   2015年3月
© 2015, The Korean Society of Mechanical Engineers and Springer-Verlag Berlin Heidelberg. The flow field of multi-parallelized swirling flow inside a circular pipe was investigated numerically. Two types of swirling flow configuration are consider...
Kazuhisa Chiba, Masahiro Kanazaki, Atthaphon Ariyarit, Hideyuki Yoda, Shoma Ito, Koki Kitagawa, Toru Shimada
International Journal of Turbo and Jet Engines   32 299-304   2015年9月
© 2015 by De Gruyter 2015. Conceptual design of a launch vehicle with a hybrid rocket engine (HRE) has been implemented using design informatics approach in order to investigate the feasibility of a single-stage hybrid rocket. Two test design prob...
Takakazu Morita, Koki Kitagawa, Toru Shimada, Shigeru Yamaguchi
International Journal of Energetic Materials and Chemical Propulsion   13 83-96   2014年
This paper presents a theoretical analysis of combustion instabilities induced by the combustion time delay of liquid oxidizer in hybrid rocket motors. In order to examine the low-frequency unstable combustion of the motors, the transfer function ...
P. Tadini, U. Tancredi, M. Grassi, L. Anselmo, C. Pardini, A. Francesconi, F. Branz, F. Maggi, M. Lavagna, L. T. Deluca, N. Viola, S. Chiesa, V. Trushlyakov, T. Shimada
Acta Astronautica   103 26-35   2014年10月
During the last 40 years, the mass of the artificial objects in orbit increased quite steadily at the rate of about 145 metric tons annually, leading to about 7000 metric tons. Most of the cross-sectional area and mass (97% in low Earth orbit) is ...
H. Hasegawa, M. Fukunaga, K. Kitagawa, T. Shimada
Combustion, Explosion and Shock Waves   49 583-592   2013年10月
In this study, characteristics of the burning rate anomaly in composite propellant grains are investigated. The burning rate anomaly has been known as the "midweb anomaly" or the "hump effect." This paper describes some results of an experimental ...
Takahashi, Kenichi; Nakadai, Keita; Oide, Sho; Tanabe, Mitsuaki; Kuwahara, Takuo
SCIENCE AND TECHNOLOGY OF ENERGETIC MATERIALS   74(6) 144-152   2013年   [査読有り]
Morita, Takakazu; Yuasa, Saburo; Kitagawa, Koki; Shimada, Toru; Yamaguchi, Shigeru
JOURNAL OF THERMAL SCIENCE AND TECHNOLOGY   8(4) 380-394   2013年   [査読有り]
Koki Kitagawa, Paul Joseph, Vasily Novozhilov, Toru Shimada
International Journal of Energetic Materials and Chemical Propulsion   11 549-566   2012年
With a view to investigating the effect of Si on the fuel regression rates, polymethyl methacrylate (PMMA) and polypropylene (PP) containing Si were made, and the relevant thermal data regarding the fuel regression rates were obtained. Also, therm...
K. Kinefuchi, I. Funaki, T. Shimada, T. Abe
Physics of Plasmas   19    2012年10月
Under certain conditions during rocket flights, ionized exhaust plumes from solid rocket motors may interfere with radio frequency transmissions. To understand the relevant physical processes involved in this phenomenon and establish a prediction ...
Kitagawa, Yosuke; Kitagawa, Koki; Nakamiya, Masaki; Kanazaki, Masahiro; Shimada, Toru
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES   55(6) 229-236   2012年   [査読有り]
Morita, Takakazu; Yuasa, Saburo; Yamaguchi, Shigeru; Shimada, Toru
JOURNAL OF THERMAL SCIENCE AND TECHNOLOGY   7(4) 387-398   2012年   [査読有り]
Novozhilov, Vasily; Joseph, Paul; Ishiko, Keiichi; Shimada, Toru; Wang, Hui
ENERGIES   4(12) 1779-1839   2011年   [査読有り]
Yuasa, Saburo; Ide, Tatsuya; Masugi, Miho; Sakurai, Takashi; Shiraishi, Noriko
JOURNAL OF THERMAL SCIENCE AND TECHNOLOGY   6(4) 268-277   2011年   [査読有り]
Guery, Jean-Francois; Chang, I-Shih; Shimada, Toru; Glick, Marilyn; Boury, Didier
ACTA ASTRONAUTICA   66(12) 201-219   2010年   [査読有り]
Kinefuchi, Kiyoshi; Funaki, Ikkoh; Shimada, Toru; Abe, Takashi
JOURNAL OF SPACECRAFT AND ROCKETS   47(6) 627-633   2010年   [査読有り]
Yutaka Wada, Yoshio Seike, Makihito Nishioka, Nobuyuki Tsuboi, Toru Shimada, Katsuya Hasegawa, Kiyokazu Kobayashi, Keiichi Hori
International Journal of Energetic Materials and Chemical Propulsion   8 555-570   2009年12月
A basic study to clarify the combustion mechanism of glycidyl azide polymer (GAP) has been conducted. Temperature during the strand burner and 60-mm diameter motor tests was measured. The strand tests were performed with 2.5-m diameter S-type ther...
Toru Shimada, Hiroshi Hasegawa
International Journal of Energetic Materials and Chemical Propulsion   8 147-158   2009年12月
In the case of center-perforated composite solid propellant grains, the radial linear burning rate often depends on web location. In many cases, the burning rate of the propellant in the middle of the web is highest along the radial direction. Thi...
Shimada, Toru; Sekino, Nobuhiro; Fukunaga, Mihoko
JOURNAL OF PROPULSION AND POWER   25(6) 1300-1310   2009年   [査読有り]
Shimada, Toru; Hanzawa, Masahisa; Morita, Takakazu; Kato, Takashi; Yoshikawa, Takashi
AIAA JOURNAL   46(12) 947-957   2008年   [査読有り]
Toru Shimada, Hiroto Habu, Yoshio Seike, Seiji Ooya, Hideo Miyachi, Masaaki Ishikawa
Flow Measurement and Instrumentation   18 235-240   2007年10月
Simulated solid propellant slurry containing lead sphere tracers is experimentally cast into a double-circular cylindrical container. During the casting, the temperature and the pressure environment has been mimicked to an actual composite solid p...
Toru Shimada, Toru Shimada, Toru Shimada, Masumi Sekiguchi, Masumi Sekiguchi, Nobuhiro Sekino, Nobuhiro Sekino
AIAA Journal   45 1324-1332   2007年6月
Three-dimensional, single-phase (equilibrium two-phase) flows inside a solid rocket motor at three burn-back grain configurations are studied by computational fluid dynamics analyses of the Reynolds-averaged Navier-Stokes equations. The major conc...
佐藤裕, 大竹邦彦, 嶋田徹, 佐藤英一
Japan Journal of Thermophysical Properties   17(3) 199-204   2003年7月   [査読有り]

Misc

 
Kazuhisa Chiba, Hideyuki Yoda, Shoma Ito, Masahiro Kanazaki, Shin’ya Watanabe, Koki Kitagawa, Toru Shimada
57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference      2016年1月
© 2016 by Authors.A single-stage launch vehicle with hybrid rocket engine has been conceptually designed by using design informatics, which has three points of view, i.e., problem definition, optimization, and data mining. The primary objective of...
Hideyuki Yoda, Shoma Ito, Masahiro Kanazaki, Kazuhisa Chiba, Koki Kitagawa, Toru Shimada
2015 IEEE Congress on Evolutionary Computation, CEC 2015 - Proceedings   618-625   2015年9月
© 2015 IEEE.A multi-objective genetic algorithm (MOGA) has been applied to the multidisciplinary design optimization (MDO) of a launch vehicle (LV) with a hybrid rocket engine (HRE) to investigate the ability of an HRE to serve as a sounding rocke...
Kohei Ozawa, Kohei Ozawa, Toru Shimada
51st AIAA/SAE/ASEE Joint Propulsion Conference      2015年1月
© 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.In practical usage of conventional hybrid rocket engines, the oxidizer-to-fuel ratio (O/F) shift occurs by either the fuel port diameter increase or throttli...
Kenichi Takahashi, Toru Shimada
51st AIAA/SAE/ASEE Joint Propulsion Conference      2015年1月
© 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.We conducted a three-dimensional numerical simulation to ascertain the luminous flame shape around an ignited aluminum particle near the burning surface of c...
Masahiro Kanazaki, Atthaphon Ariyairt, Kazuhisa Chiba, Koki Kitagawa, Toru Shimada
Procedia Engineering   99 198-207   2015年1月
© 2015 The Authors.In this study, a multi-objective genetic algorithm (MOGA) was applied to the multidisciplinary design optimization (MDO) of a hybrid rocket. A swirling-oxidizer-type hybrid rocket engine (HRE) with a single cylindrical grain por...
Kazuhisa Chiba, Masahiro Kanazaki, Koki Kitagawa, Toru Shimada
Computational Methods in Applied Sciences   36 369-384   2015年1月
© Springer International Publishing Switzerland 2015.A single-stage launch vehicle with hybrid rocket engine has been conceptually designed by using design informatics, which has three points of view as problem definition, optimization, and data m...
Mikiro Motoe, Toru Shimada
52nd Aerospace Sciences Meeting      2014年1月
© 2015, American Institute of Aeronautics and Astronautics Inc. All rights reserved.The objective of this study is to clarify inner state of a chamber of the Swirling-Oxidizer-Flow-Type Hybrid Rocket which is one of the types of a Hybrid Rocket by...
Masaki Adachi, Toru Shimada
52nd Aerospace Sciences Meeting      2014年1月
© 2014, American Institute of Aeronautics and Astronautics Inc. All rights reserved.The numerical analysis about the instability of liquid/dense fluid films under supercritical operating condition is performed on me than fuel. A numerical code for...
Kenichi Takahashi, Shoko Sakai, Makoto Nakagaki, Takafumi Sasaki, Takuo Kuwahara, Toru Shimada
50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014      2014年1月
© 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.For aluminized AP/AN composite propellant, the relation between the agglomerate diameter and pressure was investigated by observing aluminum particle agglom...
Kengo Ohe, Masato Mizuchi, Shigeru Aso, Yasuhiro Tani, Sho Ohyama, Kentaro Araki, Hiroshi Tada, Toru Shimada
50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014      2014年1月
© 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.Hybrid rocket engine with multi-section swirl injection method was designed and tested for the flight experiments of subscale space plane. Combustion experi...
Yuki Funami, Toru Shimada
50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014      2014年1月
© 2014 by the authors (Yuki Funami and Toru Shimada). Published by the American Institute of Aeronautics and Astronautics, Inc.In order to design hybrid rocket engines, we developed a numerical prediction method to the internal ballistics, such as...
Kazuhisa Chiba, Masahiro Kanazaki, Masaki Nakamiya, Koki Kitagawa, Toru Shimada
Journal of Advanced Mechanical Design, Systems and Manufacturing   8    2014年1月
A single-stage launch vehicle with hybrid rocket engine, which uses solid fuel and liquid oxidizer, has been studied and developed as a next-generation rocket for scientific observation due to the advantages as low cost, safety, re-ignition, and r...
Kohei Ozawa, Toru Shimada
50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014      2014年1月
© 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.In this paper, first, a theoretical prediction method of regression rates and heat flux to solid fuels of uni-directional vortex injection hybrid rocket eng...
Masaki Adachi, Toru Shimada
52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014      2014年1月
The numerical analysis about the instability of liquid/dense fluid films under supercritical operating condition is performed on methan fuel. A numerical code for compressible fluid flows accommodated for van der Waals equation of state is develop...
Hiroshi Tada, Shigeru Aso, Yasuhiro Tani, Sho Ohyama, Kentaro Araki, Kengo Ohe, Masato Mizuchi, Toru Shimada
50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014      2014年1月
© 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.In order to clarify combustion phenomena of hybrid rocket engines with multi-section swirl injection method, visualization tests of combustion flames has be...
Kazuhisa Chiba, Masahiro Kanazaki, Masaki Nakamiya, Koki Kitagawa, Toru Shimada
11th World Congress on Computational Mechanics, WCCM 2014, 5th European Conference on Computational Mechanics, ECCM 2014 and 6th European Conference on Computational Fluid Dynamics, ECFD 2014   3160-3179   2014年1月
A single-stage launch vehicle with hybrid rocket engine, which uses solid fuel and liquid oxidizer, has been being studied and developed as a next-generation rocket for scientific observation due to the advantages as low cost, safety, re-ignition,...
Mikiro Motoe, Toru Shimada
52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014      2014年1月
The objective of this study is to clarify inner state of a chamber of the Swirling-Oxidizer-Flow-Type Hybrid Rocket which is one of the types of a Hybrid Rocket by means of numerical fluid analysis. In this study, a numerical code which uses the L...
千葉一永, 渡邉真也, 金崎雅博, 北川幸樹, 嶋田徹
日本機械学会論文集(Web)   80(818) WEB ONLY TRANS0287   2014年
Kazuhisa Chiba,Masahiro Kanazaki,Koki Kitagawa,Toru Shimada
SIMULTECH 2013 - Proceedings of the 3rd International Conference on Simulation and Modeling Methodologies, Technologies and Applications, Reykjavík, Iceland, 29-31 July, 2013   777-784   2013年12月   [査読有り]
A single-stage hybrid rocket is necessary in order to efficiently perform the scientific observations and experiments. The primary objective of the present conceptual design is that the sufficient downrange and duration time in the low thermospher...
K. Araki, Y. Hirata, S. Ohyama, K. Ohe, S. Aso, Y. Tani, T. Shimada
49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference      2013年9月
Recently, hybrid rockets have attracted a lot of interests, because it has main some advantages of low cost, safety, and thrust throttling. On the other hand, launching practical satellites, hybrid rocket has technical problems to overcome, such a...

講演・口頭発表等

 
Kazuhisa Chiba, Hideyuki Yoda, Shoma Ito, Masahiro Kanazaki, Shin’ya Watanabe, Koki Kitagawa, Toru Shimada
57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference   2015年7月27日   
© 2016 by Authors. A single-stage launch vehicle with hybrid rocket engine has been conceptually designed by using design informatics, which has three points of view, i.e., problem definition, optimization, and data mining. The primary objective o...
Kohei Ozawa, Kohei Ozawa, Toru Shimada
51st AIAA/SAE/ASEE Joint Propulsion Conference   2015年7月27日   
© 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. In practical usage of conventional hybrid rocket engines, the oxidizer-to-fuel ratio (O/F) shift occurs by either the fuel port diameter increase or throttl...
Kenichi Takahashi, Toru Shimada
51st AIAA/SAE/ASEE Joint Propulsion Conference   2015年7月27日   
© 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. We conducted a three-dimensional numerical simulation to ascertain the luminous flame shape around an ignited aluminum particle near the burning surface of ...
中山良男, 杉山勇太, 松村知治, 若林邦彦, 出雲充生, 北川幸樹, 嶋田徹
火薬学会年会講演要旨集   2014年5月22日   
Mikiro Motoe, Toru Shimada
52nd Aerospace Sciences Meeting   2014年1月13日   
© 2015, American Institute of Aeronautics and Astronautics Inc. All rights reserved. The objective of this study is to clarify inner state of a chamber of the Swirling-Oxidizer-Flow-Type Hybrid Rocket which is one of the types of a Hybrid Rocket b...
Masaki Adachi, Toru Shimada
52nd Aerospace Sciences Meeting   2014年1月13日   
© 2014, American Institute of Aeronautics and Astronautics Inc. All rights reserved. The numerical analysis about the instability of liquid/dense fluid films under supercritical operating condition is performed on me than fuel. A numerical code fo...
Kenichi Takahashi, Shoko Sakai, Makoto Nakagaki, Takafumi Sasaki, Takuo Kuwahara, Toru Shimada
50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014   2014年7月28日   
© 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. For aluminized AP/AN composite propellant, the relation between the agglomerate diameter and pressure was investigated by observing aluminum particle agglo...
Kazuhisa Chiba, Masahiro Kanazaki, Masaki Nakamiya, Koki Kitagawa, Toru Shimada
11th World Congress on Computational Mechanics, WCCM 2014, 5th European Conference on Computational Mechanics, ECCM 2014 and 6th European Conference on Computational Fluid Dynamics, ECFD 2014   2014年7月20日   
A single-stage launch vehicle with hybrid rocket engine, which uses solid fuel and liquid oxidizer, has been being studied and developed as a next-generation rocket for scientific observation due to the advantages as low cost, safety, re-ignition,...
Yuki Funami, Toru Shimada
50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014   2014年7月28日   
© 2014 by the authors (Yuki Funami and Toru Shimada). Published by the American Institute of Aeronautics and Astronautics, Inc. In order to design hybrid rocket engines, we developed a numerical prediction method to the internal ballistics, such a...
Kohei Ozawa, Toru Shimada
50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014   2014年7月28日   
© 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. In this paper, first, a theoretical prediction method of regression rates and heat flux to solid fuels of uni-directional vortex injection hybrid rocket en...
Kengo Ohe, Masato Mizuchi, Shigeru Aso, Yasuhiro Tani, Sho Ohyama, Kentaro Araki, Hiroshi Tada, Toru Shimada
50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014   2014年7月28日   
© 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Hybrid rocket engine with multi-section swirl injection method was designed and tested for the flight experiments of subscale space plane. Combustion exper...
Hiroshi Tada, Shigeru Aso, Yasuhiro Tani, Sho Ohyama, Kentaro Araki, Kengo Ohe, Masato Mizuchi, Toru Shimada
50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014   2014年7月28日   
© 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. In order to clarify combustion phenomena of hybrid rocket engines with multi-section swirl injection method, visualization tests of combustion flames has b...
千葉一永, 渡邉真也, 金崎雅博, 北川幸樹, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2014年   
安藤秀幸, 高橋瞬, 富澤勉, 林大貴, 櫻井毅司, 湯浅三郎, 北川幸樹, 嶋田徹, 高山明正, 由井亮典
宇宙科学技術連合講演会講演集(CD-ROM)   2014年   
千葉一永, 金崎雅博, 北川幸樹, 嶋田徹
日本機械学会設計工学・システム部門講演会論文集(CD-ROM)   2013年10月22日   
K. Araki, Y. Hirata, S. Ohyama, K. Ohe, S. Aso, Y. Tani, T. Shimada
49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference   2013年9月16日   
Recently, hybrid rockets have attracted a lot of interests, because it has main some advantages of low cost, safety, and thrust throttling. On the other hand, launching practical satellites, hybrid rocket has technical problems to overcome, such a...
Sho Ohyama, Y. Hirata, K. Araki, K. Ohe, S. Aso, Y. Tani, T. Shimada
49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference   2013年9月16日   
Low fuel regression rate is fatal disadvantage for hybrid rocket. To overcome this problem, a lot of methods have been proposed. In Kyushu university multi-section swirl injection method has been proposed to increase the fuel regression rate and c...
Mikiro Motoe, Toru Shimada
49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference   2013年9月16日   
It has been clarified by experimental investigations that the regression rate can be improved by swirling injection of gaseous oxidizers. Because it has not been enough that the analysis considering characteristics of Swirling-Oxidizer-Flow-Type H...
Takakazu Morita, Takakazu Morita, Saburo Yuasa, Saburo Yuasa, Toru Shimada, Toru Shimada, Shigeru Yamaguchi, Shigeru Yamaguchi
49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference   2013年9月16日   
Theoretical regression rates and combustion response functions in hybrid rocket motors are obtained by using the heat-feedback law that describes the heat flux from flame to fuel surface. In our previous studies, we derived a heat-feedback law usi...
P. Tadini, U. Tancredi, M. Grassi, L. Anselmo, C. Pardini, F. Branz, A. Francesconi, F. Maggi, M. Lavagna, L. T. De Luca, N. Viola, S. Chiesa, V. Trushlyakov, T. Shimada
Proceedings of the International Astronautical Congress, IAC   2013年9月23日   
During the last 40 years, the mass of the artificial objects in orbit increased quite steadily at the rate of about 145 metric tons annually, leading to about 7000 metric tons. Most of the cross-sectional area and mass (97% in low Earth orbit) is ...
Shota Yamanaka, Toru Shimada
Proceedings of the International Astronautical Congress, IAC   2013年9月23日   
In this paper, we develop a systematical method for the reduction of chemistry model of hydro-carbon oxygen/air reaction in order to compute the ignition process of boundary layer combustion with a proposed dynamic load balance strategy for the pa...
湯浅三郎, 畑垣伶, 由井亮典, 櫻井毅司, 安藤秀幸, 高橋瞬, 白石紀子, 北川幸樹, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2013年   
北川幸樹, 中山良男, 和田豊, 松村知治, 若林邦彦, 戸田諒, 森田貴和, 那賀川一郎, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2013年   
船見祐揮, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2013年   
森田貴和, 臼井雄太郎, 勝又玲子, 北川幸樹, 湯浅三郎, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2013年   
金森文男, 北川洋介, 金崎雅博, 中宮賢樹, 北川幸樹, 嶋田徹
日本航空宇宙学会年会講演会講演集(CD-ROM)   2013年   
千葉一永, 金崎雅博, 中宮賢樹, 北川幸樹, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2013年   
本江幹朗, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2013年   
金森文男, 中宮賢樹, 北川幸樹, 金崎雅博, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2013年   
麻生茂, 谷泰寛, 大山翔, 荒木健太郎, 大江健悟, 多田洋史, 水地壮登, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2013年   
S. Ohyama, S. Asoy, Y. Hirata, K. Araki, K. Ohe, Y. Taniz, T. Shimada
48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012   2012年7月30日   
A new method with multi-section swirl injection was proposed in order to improve the fuel regression rate of hybrid rockets. The new method was to introduce swirling flow through injector ports, which were placed at several cross-sections along th...
Masahiro Kanazaki, Yosuke Kitagawa, Koki Kitagawa, Masaki Nakamiya, Toru Shimada
ECCOMAS 2012 - European Congress on Computational Methods in Applied Sciences and Engineering, e-Book Full Papers   2012年9月10日   
The multi-objective genetic algorithm (MOGA) is applied to the multi-disciplinary conceptual design problem for a three-stage launch vehicle (LV) with a hybrid rocket engine (HRE). MOGA is an optimization tool used for multi-objective problems. Th...
Masaki Adachi, Toru Shimada
Proceedings of the International Astronautical Congress, IAC   2012年10月1日   
It is necessary for designing hybrid rocket engines which use liquefying fuel to understand the behavior of liquid films on the surface of solid fuel. Although it is reported that there is supercritical region inside hybrid rocket engines using li...
Yuki Funami, Toru Shimada
AIP Conference Proceedings   2012年7月10日   
Boundary-layer combustion, a major characteristic of a hybrid rocket engine, is a complex phenomenon of fluid dynamics and combustion. Its rate-limiting process is diffusion, whereas combustion reactions are generally very fast. One of numerical a...
Yoshihide Hirata, Shigeru Aso, Sho Ohyama, Kentaro Araki, Kengo Ohe, Yasuhiro Tani, Toru Shimada
Proceedings of the International Astronautical Congress, IAC   2012年10月1日   
Today developments of nano satellites, whose weight is less than 100 kg, become quite active. As nano satellites are used commercial, inexpensive components, the cost of nano satellites becomes cheap and also the size of subsystems of nano satelli...
Yuki Funami, Toru Shimada
AIP Conference Proceedings   2012年7月10日   
In order to design hybrid rocket engines, we have developed a numerical prediction approach to the internal ballistics. The key point is its cost performance. Therefore simple but efficient models are required. Fluid phenomenon and thermal conduct...
高橋賢一, 生出翔, 田辺光昭, 桑原卓雄, 嶋田徹
火薬学会秋季研究発表講演会講演要旨集   2012年11月   
嶋田徹, 北川幸樹, 湯浅三郎, 那賀川一郎, 永田晴紀, 福地亜宝郎, 和田豊
宇宙科学技術連合講演会講演集(CD-ROM)   2012年   
平田吉秀, 荒木健太郎, 大山翔, 大江健悟, 麻生茂, 谷泰寛, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2012年   
坪井伸幸, 吹場活佳, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2012年   
金崎雅博, 北川洋介, 北川幸樹, 中宮賢樹, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2012年   
森田貴和, 原田潤一, 湯浅三郎, 北川幸樹, 嶋田徹, 山口滋
宇宙科学技術連合講演会講演集(CD-ROM)   2012年   
Koki Kitagawa, Toru Shimada, Hiroshi Hasegawa, Mihoko Fukunaga, Hideo Miyachi, Hiroki Kosuge
47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011   2011年7月31日   
To investigate correlation between the orientation of sub-millimeter AP particles and the local burning rate in a propellant containing high amount of Al particles, the orientation angle data of sub-millimeter AP particles were obtain by using X-r...
Y. Hirata, S. Aso, T. Hayashida, R. Nakawatase, Y. Tani, K. Morishita, T. Shimada
47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011   2011年7月31日   
In order to improve fuel regression rate of hybrid rockets, a new method with multisection swirl injection is proposed. The new method is to introduce swirling flow through multi-section swirl injector ports, which are placed at several locations ...
Mikiro Motoe, Toru Shimada
47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011   2011年7月31日   
For the hybrid engine, it has been proven by ground and flight experiments that the fuel regression characteristic can be improved by tangential injection of the oxidizer. The mechanism, however, of this enhancement has not yet been well-understoo...
嶋田徹
火薬学会年会講演要旨集   2011年5月26日   
高田智弘, 福永美保子, 長谷川宏, 北川幸樹, 平岡克己, 嶋田徹
火薬学会年会講演要旨集   2011年5月26日   
森田貴和, 砂田将成, 崎尾和樹, 藤原聡一郎, 山口滋, 嶋田徹
日本機械学会関東支部総会講演会講演論文集   2011年3月17日   
淺川弘也, 福永美保子, 関野展弘, 長谷川宏, 北川幸樹, 嶋田徹
航空原動機・宇宙推進講演会講演集(CD-ROM)   2011年   
坪井伸幸, 鈴木直洋, 船木一幸, 嶋田徹
流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM)   2011年   
船見祐揮, 嶋田徹
航空原動機・宇宙推進講演会講演集(CD-ROM)   2011年   
坪井伸幸, 香川岳寛, 吹場活佳, 嶋田徹
流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM)   2011年   
森田貴和, 藤原桂, 松木彩, 山口滋, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2011年   
坪井伸幸, 吹場活佳, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2011年   
本江幹朗, 嶋田徹
航空原動機・宇宙推進講演会講演集(CD-ROM)   2011年   
北川幸樹, PAUL Joseph, NOVOZHILOV Vasily, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2011年   
北川洋介, 北川幸樹, 中宮賢樹, 金崎雅博, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2011年   
嶋田徹, 石向桂一, 本江幹朗, 船見祐揮, NOVOZHILOV Vasily
宇宙科学技術連合講演会講演集(CD-ROM)   2011年   
Koki Kitagawa, Koki Kitagawa, Toru Shimada, Toru Shimada, Hiroshi Hasegawa, Hiroshi Hasegawa, Mihoko Fukunaga, Mihoko Fukunaga, Hideo Miyachi, Hideo Miyachi
46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit   2010年7月25日   
Three dimensional information of sub-millimeter AP particles and local burning rates of composite propellant have been obtained. In this study, to investigate correlation between the orientation of sub-millimeter AP particles and the local burning...
T. Shimada, K. Kitagawa, H. Hasegawa, M. Fukunaga, H. Asakawa
61st International Astronautical Congress 2010, IAC 2010   2010年9月27日   
This paper describes the development of a numerical simulation system, "Advanced Computer Science on Solid-Rocket-Motor (SRM) Internal Ballistics (ACSSIB)". The objectives of this technology development consist of development of composite-propella...
長谷川宏, 加藤一成, 福永美保子, 嶋田徹
火薬学会年会講演要旨集   2010年5月20日   
高田智弘, 平岡克己, 北川幸樹, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2010年   
森田貴和, 北川幸樹, 湯浅三郎, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2010年   
北川幸樹, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2010年   
北川洋介, 金崎雅博, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2010年   
坪井伸幸, 香川岳寛, 吹場活佳, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2010年   
淺川弘也, 福永美保子, 関野展弘, 長谷川宏, 北川幸樹, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2010年   
嶋田徹, 福永美保子, 長谷川宏, 北川幸樹, 淺川弘也, 佐藤航
宇宙科学技術連合講演会講演集(CD-ROM)   2010年   
船見祐揮, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2010年   
小菅裕紀, 平岡克己, 北川幸樹, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2010年   
嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2010年   
杵淵紀世志, 船木一幸, 小川博之, 加藤輝雄, 太刀川純孝, 嶋田徹, 安部隆士
航空原動機・宇宙推進講演会講演集(CD-ROM)   2009年12月1日   
In rocket flights, ionized exhaust plumes from solid rocket motors may interfere with RF transmission under some conditions. In order to clarify the important physical process involved, microwave attenuation and phase delay due to rocket exhaust p...
Mikiro Motoe, Toru Shimada
45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit   2009年8月2日   
It has been proven by ground and flight experiments that the fuel regression characteristic of hybrid rocket can be improved by tangential injection of the oxidizer. The mechanism, however, of this enhancement has not yet been well-understood. The...
Kenichi Takahashi, Takuya Mano, Mitsuaki Tanabe, Takuo Kuwahara, Toru Shimada
45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit   2009年8月2日   
The thrust performance of the solid propellant is improved by adding the metal particles which have good ignition and combustion characteristics. In the reaction zone which is a very thin zone near the burning surface, the metal particles ignite, ...
高橋賢一, 眞野卓也, 田辺光昭, 桑原卓雄, 嶋田徹
火薬学会秋季研究発表講演会講演要旨集   2009年12月   
本江幹朗, 矢島雄三, 嶋田徹, 湯浅三朗, 平岡克己
航空原動機・宇宙推進講演会講演集(CD-ROM)   2009年   
長谷川宏, 清家誉志男, 加藤一成, 福永美保子, 大門優, 坪井伸幸, 嶋田徹
航空原動機・宇宙推進講演会講演集(CD-ROM)   2009年   
矢島雄三, 嶋田徹, 平岡克己
宇宙科学技術連合講演会講演集(CD-ROM)   2009年   
坪井伸幸, 吹場活佳, 嶋田徹
航空原動機・宇宙推進講演会講演集(CD-ROM)   2009年   
淺川弘也, 福永美保子, 関野展弘, 長谷川宏, 坪井伸幸, 大門優, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2009年   
坪井伸幸, 吹場活佳, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2009年   
船見祐揮, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2009年   
長谷川宏, 木村元康, 加藤一成, 宮地英生, 福永美保子, 坪井伸幸, 大門優, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2009年   
石向桂一, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2009年   
福永美保子, 関野展弘, 嶋田徹, 坪井伸幸, 大門優, 長谷川宏
航空原動機・宇宙推進講演会講演集(CD-ROM)   2009年   
本江幹朗, 嶋田徹, 湯浅三朗, 平岡克己
流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集   2009年   
本江幹朗, 嶋田徹, 湯浅三郎, 平岡克己
宇宙科学技術連合講演会講演集(CD-ROM)   2009年   
嶋田徹, 坪井伸幸, 大門優, 関野展弘, 福永美保子, 淺川弘也, 加藤一成, 清家誉志男, 長谷川宏
航空原動機・宇宙推進講演会講演集(CD-ROM)   2009年   
矢島雄三, 本江幹朗, 嶋田徹, 平岡克己
航空原動機・宇宙推進講演会講演集(CD-ROM)   2009年   
嶋田徹
航空原動機・宇宙推進講演会講演集(CD-ROM)   2009年   
光中渉, 麻生茂, 谷泰寛, 嶋田徹
日本航空宇宙学会西部支部講演会講演集   2009年   
Toru Shimada
International Astronautical Federation - 59th International Astronautical Congress 2008, IAC 2008   2008年9月29日   
Discussions are made on the localized erosion of charring ablators used in the expanding part of solid rocket motor nozzles. Such erosion pattern is sometimes seen over liner surface downstream the throat inserts after static firing tests. The maj...
Toru Shimada, Toru Shimada, Nobuhiro Sekino, Nobuhiro Sekino, Mihoko Fukunaga, Mihoko Fukunaga
44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit   2008年7月21日   
In order to understand the mechanism of the large roll-torque generation in the operating solid rocket motor with axially-slotted propellant grain and the narrow nozzle submergence region, fully three-dimensional Navier-Stokes numerical simulation...
嶋田徹, 安田誠一, 鈴木直洋, 冨澤利夫, 二宮一芳, 菊地原清澄, 矢島卓, 尾澤剛
宇宙科学技術連合講演会講演集(CD-ROM)   2008年   
嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2008年   
坪井伸幸, 永井大樹, 浅井圭介, 大門優, 嶋田徹
流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集   2008年   
本江幹朗, 松原寿洋, 嶋田徹, 湯浅三郎
宇宙科学技術連合講演会講演集(CD-ROM)   2008年   
Shinichiro Tokudome, Shinichiro Tokudome, Shinichiro Tokudome, Tsuyoshi Yagishita, Tsuyoshi Yagishita, Hiroto Habu, Hiroto Habu, Hiroto Habu, Toru Shimada, Toru Shimada, Toru Shimada, Yasuhiro Daimo, Yasuhiro Daimo
Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference   2007年7月8日   
Nitrous Oxide (N2O) / ethanol propulsion system is distinguished as the liquid propulsion with non-toxic, user-friendly, and storable bipropellant. The current target of the present study is to build a quick-response and maneuverable main engine o...
Daimon Yu, Daimon Yu, Daimon Yu, Toru Shimada, Toru Shimada, Toru Shimada, Nobuyuki Tsuboi, Nobuyuki Tsuboi, Nobuyuki Tsuboi, Kazuhisa Fujita, Kazuhisa Fujita, Kazuhisa Fujita
Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference   2007年7月8日   
A numerical framework is established to predict the erosion amount of nozzle wall in solid rocket motor. Understanding of the flow field and erosion mechanism is very important for the performance of solid rocket motor and the success of the launc...
竹前俊昭, 嶋田徹
宇宙科学技術連合講演会講演集(CD-ROM)   2007年12月1日   
Reliability and efficiency in the operation from the assembly of rocket vehicles to the launch of them are considered. Especially, the form of health-confirmation inspection/test after procedures of assembling operations with high efficiency and, ...

競争的資金等の研究課題

 
宇宙推進システム
固体ロケットの燃焼流体力学
ノズルの定量的設計技術の研究
アブレータの表面後退現象の研究
ハイブリッドロケットの研究