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OBARA Tetsuro

■Faculty: Graduate School of Science and Engineering ■TEL:
■Position: Professor ■FAX:
■Address: 255 Shimo-Okubo, Sakura-ku, Saitama City, Saitama 338-8570, JAPAN ■Mail Address:
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Faculty of Engineering

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Books
第5回デトネｰション研究会 若手夏の学校テキスト(基礎研究における実験･計測技術)
:125-144 2010
小原 哲郎,他6名

Articles
スリットから回折したデトネｰション波の再開始に関する可視化観察
,第48回燃焼シンポジウム講演論文集:514-515 2010
菅原 崇, 沈 志剛, 小原 哲郎, 大八木 重治

ロｰタリｰバルブを用いたパルスデトネｰションエンジンに関する研究
,第48回燃焼シンポジウム講演論文集:231-232 2010
吉田 健司, 浅見 亮輔, 吉橋 照夫, 小原 哲郎, 大八木 重治

凹凸壁面を有する流路におけるデトネｰション波遷移過程の可視化観察
,第48回燃焼シンポジウム講演論文集:516-517 2010
小林 達典, 岩田 脩平, 小原 哲郎, 大八木 重治

火炎と衝撃波の干渉によるデトネｰション波開始過程の可視化観察
,第48回燃焼シンポジウム講演論文集:391-394 2010
小山田 拓, 清田 涼輔, 小原 哲郎, 大八木 重治, 吉橋 照夫

細い管内でのデトネーション遷移過程に関する実験的研究
日本燃焼学会,日本燃焼学会誌,52(159):86-93 2010
永井厚司、岡部俊彦、キム・ギョンミン、吉橋照夫、小原哲郎、大八木重治

水素及び空気噴射によるDDT過程の研究
,第48回燃焼シンポジウム講演論文集:387-390 2010
矢部 仁識, 内藤 正樹, 吉橋 照夫, 小原 哲郎, 大八木 重治

二気筒パルスデトネｰションエンジンによる燃焼過程の研究およびガスタｰビン性能評価
,第48回燃焼シンポジウム講演論文集:233-236 2010
澁谷 大智,齋藤 亘, 吉橋 照夫, 小原 哲郎, 大八木 重治

デトネーション波と衝撃波の干渉現象に関する研究
日本燃焼学会,日本燃焼学会誌,51(158):318-324 2009
永井厚司、横川真人、吉橋照夫、小原哲郎、大八木重治

第4回 デトネーション研究会 若手夏の学校テキスト
,デトネーション研究会:73-92 2009
小原哲郎

Re-initiation process of detonation wave behind a slit-plate
,Shock Waves,18(2):117-127 200807
T. Obara;J. Sentanuhady;Y. Tsukada;S. Ohyagi
電子ジャーナル Web Of Science

酸水素予混合気体への衝撃波入射により生じる燃焼波の伝ぱ形態
,日本機械学會論文集. B編,74(740):949-956 2008
小原哲郎、栗原慶博、落合俊幸、大八木重治
Propagation Behavior of Combustion Wave Induced by a Shock Wave Propagated into a Premixed Gas of Oxygen and Hydrogen, Transactions of the Japan Society of Mechanical Engineers, Series B

スリット板背後におけるデトネーション波の再開始過程 (スリット板形状の違いによる影響)
,日本機械学會論文集. B編,73(732):1737-1744 2007
Jayan Sentanuhady, 小原哲郎, 塚田豊, 大八木重治
Re-initiation Processes of Detonation Wave behind Slit-plate (Influence of Slit-Plate Configuration), Transactions of the Japan Society of Mechanical Engineers, Series B

スリット板背後におけるデトネーション波の再開始過程 (デトネーション波の再開始と消炎過程の可視化)
,日本機械学會論文集. B編,73(735):2354-2361 2007
小原哲郎、塚田豊、Jayan Sentanuhady、大八木重治
Re-initiation Processes of Detonation Wave behind Slit-Plate (Visualization of Re-initiation and Quenching Processes of Detonation Wave), Transactions of the Japan Society of Mechanical Engineers, Series B

デトネーション波の消炎および再開始現象の解明
埼玉大学総合研究機構,総合研究機構研究プロジェクト研究成果報告書(5(18年度)):580-581 2007
小原哲郎
Study on Quenching and Re–initiation Behavior of Detonation Wave
リポジトリ

パルスデトネーション・エンジン連続作動特性の研究
埼玉大学総合研究機構地域共同研究センター産学連携推進部門,埼玉大学地域共同研究センター紀要,8:64-67 2007
遠藤慎介、中込大輔、吉橋照夫、小原哲郎、大八木重治、村山元
A Study on Multiple-cycle Operation of Pulse Detonation Engine
リポジトリ

水素 酸素予混合気体への衝撃波入射により誘起される燃焼波の挙動
,日本機械学會論文集. B編,73(727):871-878 2007
小原哲郎、楢原由樹子、栗原慶博、大八木重治
Behavior of Combustion Wave induced by Propagation of Shock Wave into Premixed Gas of Hydrogen and Oxygen, Transactions of the Japan Society of Mechanical Engineers, Series B

狭い間隙に進入する火炎の挙動に関する実験的研究(熱工学,内燃機関,動力など)
日本機械学会,日本機械学會論文集. B編,72(720):2018-2025 200608
小原哲郎、大八木重治、仁科祐介、成澤伸之
A behavior of a flame propagating through a narrow channel is of importance, since this phenomenon is concerned with a quenching of the flame when heat losses by convective heat transfer or radiative one to a wall of channel are dominant and temperature behind the flame is not enough to increase that of unburned gases. Since, this phenomenon is also related to a safety-engineering problem where combustible gaseous mixture is handled, a device applying a narrow channel in a pipe might be one of useful technique to prevent the flame from propagating. Experiments were conducted to investigate a behavior of the flame propagating through a narrow channel, which connects two rectangular combustion chambers. The behavior of the flame was visualized using schlieren optical technique with an aid of high-speed video camera. In this study, an equivalence ratio of methane-air mixture, initial pressure and a width of the channel were varied in order to investigate effects of these parameters on characteristics of the flame propagation. As a result, the behavior of the flame entering into the narrow channel was classified into two phenomena, i.e. (i) the flame was quenched inside the narrow channel and combustion wave was not propagated into the downstream chamber, which results in just an emission of burned gaseous jet to the downstream chamber, (ii) the flame was propagated through the channel without quenching, which produced a high-pressure at both chambers.
Combustion, Premixed Combustion, Premixed Combustion, Combustion Phenomena, Pressure Wave, Flow Visualization
リポジトリ

スリットに入射したデトネーション波の再開始過程<研究成果報告>
埼玉大学工学部,埼玉大学紀要, 工学部, 第1部論文集,39:119-126 200607
小原哲郎、大八木重治
Re-Inititaion Processes of Detonation Wave propagating through a Slit
リポジトリ

デトネーション駆動型衝撃風洞を用いたスクラムジェット燃焼器モデル内の燃焼過程(熱工学,内燃機関,動力など)
日本機械学会,日本機械学會論文集. B編,72(718):1596-1604 200606
小原哲郎、伊藤豪明、大八木重治、金泰煥、坪井伸幸
Experiments were conducted in order to investigate mixing and combustion processes in a model SCRAM (Supersonic Combustion RAM) jet combustor equipped with a backward-facing step. A detonation-driven shock tunnel was used to generate high-enthalpy flow of Mach number three. Firstly, an influence of installing a sidewall on the combustor model was investigated. Secondly, flow-fields around the step were visualized using high-speed video camera with an aid of schlieren technique. A hydrogen fuel was injected perpendicular to the supersonic flow behind the backward-facing step and a height of the step and an injection distance were varied in order to investigate the effects of these parameters on a characteristic of the combustion. As a result, the injected hydrogen was ignited behind the step and increasing the height of step became effective to the ignition and flame holding behaviors. Furthermore, a non-dimensional injection distance with respect to height of the step was considered to be an important parameter to influence an ignition and combustion processes in the model SCRAM jet combustor.
Supersonic Flow, Combustion, Shock Wave, Ignition, Detonation, SCRAM Jet Engine, Shock Tunnel
Combustion processes in model SCRAM jet combustor using detonation driven shock tunnel, Transactions of the Japan Society of Mechanical Engineers, Series B
リポジトリ

狭い溝中を通過するデトネーション波の挙動に関する研究(熱工学,内燃機関,動力など)
日本機械学会,日本機械学會論文集. B編,72(718):1605-1612 200606
小原哲郎、SENTANUHADY Jayan、塚田豊、大八木重治
A detonation wave produced in a combustible gaseous mixture might cause serious damages by interacting with an artificial structure or human bodies because of an extremely high-pressure and high-temperature behind this wave. Therefore, the detonation wave produced in the gaseous mixture and propagated into a circumstance by accident should be attenuated or quenched within a short distance from its origin. Experiments were conducted in order to investigate behaviors of the detonation wave passing through narrow grooves, since the detonation wave was accompained with a cellular structure and no detonation wave could be propagated. In this study, the detonation wave produced in a gaseous mixture of hydrogen and oxygen was propagated through a grooved block and behaviors of the detonation wave were experimentally investigated by using techniques of pressure measurement and soot track record. As a result, the behavior of detonation wave propagating through the grooved block was classified into two categories, i. e. (i) the detonation wave was quenched, (ii) the detonation wave was once quenched behind the block but re-initiated again by focusing mechanisms of a reflected shock wave on a central axis.
Detonation, Premixed Combustion, Combustion Phenomena, Shock Wave, Compressible Flow
A Study on Behavior of Detonation Wave Passing through Narrow Grooves, Transactions of the Japan Society of Mechanical Engineers, Series B
リポジトリ

Experimental Study on a Flow Field behind Backward-facing Step using Detonation-driven Shock Tunnel
,Shock Waves,15(1):1-12 2006

Laser Ablation with Water Micro-Drop for Dicing of Silicon Wafer
,Journal of Laser Applications,18(2):127-130 2006

スリット板背後におけるデトネーション波の再開始過程 (供試気体初期圧力の影響)
,日本機械学會論文集. B編,72(724):3158-3165 2006
小原哲郎、Jayan Sentanuhady、塚田豊、大八木重治
Re-Inititaion Processes of Detonation Wave behind Slit-Plate - Influence of Initial Test Gas Pressure -, Transactions of the Japan Society of Mechanical Engineers, Series B

デトネーションアレスター技術の確立とメカニズムの解明
埼玉大学総合研究機構,総合研究機構研究プロジェクト研究成果報告書(4(17年度)) 2006
小原哲郎
A development of detonation-arrestor technique with investigation into the mechanisms
リポジトリ

パルスデトネーションエンジンの安定作動に関するパージ空気の噴射量および分布の影響
,日本航空宇宙学会論文集. B編,54(628):204-209 2006
桜井毅司、大古壮了、柚木聡、吉橋照夫、小原哲郎、大八木重治
Effect of Injected Volume and Distribution of Purge-Air Regarding Stable Operation for a Pulse Detonation Engine

研究プロジェクト「マイクロ／ナノスケール計測制御テクノセンタ ー」活動報告<研究成果報告>
埼玉大学工学部,埼玉大学紀要, 工学部, 第1部論文集,1(38):114-118 200503
水野毅、川橋正昭、大八木重治、加藤寛、佐藤勇一、堀尾健一郎、豊岡了、荒居善雄、綿貫啓一、池野順一、小原哲郎、高崎正也
Report on the Activities of Research Project “Techno Center for Micro/Nano-Scale Control and Measurement”
リポジトリ

Investigation of the Purge Process on the Multi-Cycle Operations of a Pulse Detonation Engine
,Transactions of the Japan Society for Aeronautical and Space Sciences,48(160):78-85 2005
Sakurai T., Ooko A., Yoshihashi T., Obara T., Ohyagi S.

スクラムジェットエンジンの開発を目指した基礎研究
埼玉大学総合研究機構,総合研究機構研究プロジェクト研究成果報告書,16年度 2005
小原哲郎
A fundamental research to develope SCRAM jet engine
リポジトリ

レーザダイシング技術の開発
,レーザ加工学会誌,12(6) 2005

ロータリーバルブを装着したPDE のデトネーション作動に関する研究
埼玉大学総合研究機構地域共同研究センター産学連携推進部門,埼玉大学地域共同研究センター紀要,6:58-62 2005
柚木聡、桜井毅司、笹森崇志、小原哲郎、大八木重治、村山元英
A PDE equipped with the rotary-valve was constructed. Fuel, which is hydrogen, was injected by the solenoid valve. The porous plates was used to promote the mixing of fuel-air mixture. In this paper, multi-cycle operations for 20Hz, 4.5 second were conducted. It was investigated that what kind of porous shape and the fuel injection position were effective to the mixing and subsequent detonation process. As a result, the “IP2”, which was downward injection to the air, was the best for the fuel injection position. The porous plate “P3” that has large open ratio and small aperture size was effective to the mixing and detonation. Detonations were not obtained at all cycles because the mixture could not be filled to the combustion tube uniformly.
Pulse Detonation Engine, Detonation, Rotary-Valve
リポジトリ

デトネーション波により駆動される衝撃波管の作動特性に関する実験的研究(熱工学,内燃機関,動力など)
日本機械学会,日本機械学會論文集. B編,70(691):707-714 200403
金泰煥、小原、哲郎、大八木重治、吉川正人
A detonation-driven shock tube is useful apparatus for producing high-enthalpy flow and it can be used to investigate a combustion flow inside Scramjet-engine. This detonation-driven shock tube produces a shock wave of high propagation Mach number using a particularly high-temperature gas behind detonation wave. However, state variables such as pressure and temperature behind detonation wave are not uniform, since a Taylor expansion wave follows precursor detonation wave so as to decrease these variables. Therefore, a performance of this device is necessary to be studied and this report is concerned with characteristics of this facility in order to produce a high-enthalpy flow. Experiments were conducted by applying a combination of sub-combustion tube and spiral-coil to produce a detonation wave. As a result, it was clarified that detonation wave was produced with extremely short distance from an igniter. The propagation Mach number of a shock wave was increased by diluting driver-gas with light-gas. A stagnation enthalpy behind reflected shock wave was evaluated and experimental conditions producing high-enthalpy flow were clarified, which would be practical to investigate a combustion flow inside a Scramjet-engine.
Detonation, Shock Wave, Compressible Flow, Shock Tunnel
Experimental Study on Performance of Shock Tube Driven by Detonation Wave, Transactions of the Japan Society of Mechanical Engineers, Series B
リポジトリ

A Study for Development of Hydrogen-fueled Pulse Detonation Engines
,Science and Technology of Energetic Materials,65(4):125-133 2004
Sakurai T., Minagawa T., Yoshihashi T., Obara T., Ohyagi S.

デトネーション駆動型衝撃風洞を用いた後ろ向きステップ周りの流れ場に関する実験的研究
,日本航空宇宙学会論文集,52(608):385-392 2004
金泰煥、小原哲郎、大八木重治、吉川正人
Experimental Study on Flow Field behind Backward-Facing Step using Detonation-Driven Shock Tunnel

開放端から放出された衝撃波に関する実験と数値シミュレーション(流体工学,流体機械)
日本機械学会,日本機械学會論文集. B編,68(668):1036-1043 200204
小原哲郎、大八木重治、加藤肇、有賀洋介
It is important to investigate a pressure profile when a diffracted shock wave interacts with a reflector from a safety point of view. Because the diffracted shock waves are often generated by the explosions of combustible gases to cause serious damages against human race and surrounding buildings. The maximum pressure behind reflected shock wave is one of the most important parameter and this report is concerned with the evaluation of maximum pressure, which might be a function of Mach number of the shock wave, distance from a source of the shock wave, initial pressure of the gas, and initial diameter of the shock wave, etc. In this study, a detonation-driven shock tube of 14 m long and 50 mm diameter is used to generate a strong shock wave of propagating Mach number M_S=3.0～5.2. The shock wave is diffracted from an open end of the shock tube of 25 mm diameter and reflected from a cylindrical reflector of 50 mm diameter. These phenomena are observed using color-schlieren optical techniques and the pressure histories at the stagnation point of the reflector are simultaneously measured. As a result, (i) The behaviors of the diffracted shock wave and complicate flow-fields behind reflected shock wave are observed. (ii) An empirical equation to calculate the maximum pressure behind reflected shock wave is estimated by the results of experimental and numerical simulation.
Shock Wave, Detonation Wave, Compressible Flow, Flow Visualization, Diffraction, Reflection
Experimental and Numerical Simulation of a Shock Wave discharged from an Open-end, Transactions of the Japan Society of Mechanical Engineers, Series B
リポジトリ

Diffraction and Re-Initiation of Detonations behind a Backward-facing Step
,Shock Waves,12:221-226 2002

Propagation of Pressure Waves Initiated by Flame and Detonation in a Tube
,JSME International Journal, Series B,45(1):192-200 2002

Study on Performance of Detonation-Driven Shock Tube
,JSME International Journal, Series B,45(2):425-431 2002

回折する衝撃波の挙動に関する研究 : 第2報、溝付き開放端による衝撃波の減衰過程 : 流体工学,流体機械
日本機械学会,日本機械学會論文集. B編,67(659):1680-1686 200107
小原哲郎、大八木重治、高藤亮一、蔡品
Experiments are carried out to investigate behavior of shock wave diffraction from a safety-engineering point of view. Because, once the shock wave is released into an ambience, high pressure and negative pressure lasting for relatively long period have possibility to cause serious damages against human bodies as well as general buildings. Therefore, it should be one of the most significant subjects to attenuate the shock wave efficiently within a short distance from the source. In this report, a cavity is installed at an open end of a shock tube and flow-fields behind diffracted shock wave are visualized using schlieren photography. In addition, piezo-electric pressure transducer is flush mounted on the surface of reflector, which is installed at test section, and pressure histories are recorded with wide frequency response. Lastly, numerical simulation using the TVD finite difference scheme is performed to compare with the experimental results. As a result, (i) the pressure histories on the reflector coincides well between the numerical and experimental results, (ii) flow-fields behind the shock wave are clarified, (iii) maximum pressure behind reflected shock wave can be attenuated by installing several cavities inside the open end of the shock tube.
Compressible Flow, Computational Fluid Dynamics, Shock Wave, Flow Visualization
A Study on Behavior of Diffracted Shock Wave (2nd Report, Process of Shock Wave Attenuation by Cavities inside Open End of a Tube), Transactions of the Japan Society of Mechanical Engineers, Series B
リポジトリ

デトネーション駆動形衝撃波管の作動特性
日本機械学会,日本機械学會論文集. B編,66(651):2992-2998 200011
山中昭央、有賀洋介、小原哲郎、蔡品、大八木重治
A detonation-driven shock tube firstly designed by H.-R. Yu, is considered as a useful facilities capable of producing high-enthalpy flow. In this apparatus, a strong shock wave is generated by detonating oxygen-hydrogen (oxyhydrogen) mixture and has characteristics that temperature as well as pressure of driver gas is extremely high compared with conventional shock tubes. However, a structure of detonation wave is not uniform e.g., detonation wave has three-dimensional cellular structures and multiple transverse waves. Furthermore, the detonation wave is followed by a Taylor expansion fan and performance of detonation-driven shock tube is not well understood. In this preliminary study, a detonation-driven shock tube is constructed and its performance is experimentally investigated by measuring pressure histories and a profile of ionization current behind detonation wave. As a result, (i) the pressure histories of detonation wave is clarified and it shows reasonable agreement with a result obtained by KASIMIR shock tube simulation code. (ii) A propagation velocity of detonation wave is coincided well with theoretical predictions assuming Chapman-Jouguet detonation wave. (iii) An equivalence ratio of oxyhydrogen mixture to produce a highest Mach number of the shock wave is evaluated as 〓&sime;1.7.
Combustion, Detonation, Shock Wave, Shock Tube, Detonation-Driver, Mach Number
A Study on Performance of a Detonation-Driven Shock Tube, Transactions of the Japan Society of Mechanical Engineers, Series B
リポジトリ

A Numerical Simulation of Reflection Processes of a Detonation Wave on a Wedge
,Shock Waves,10(3):185-190 2000

気体デトネーションの構造とその反射・回折現象
サイエンス・コミュニケーションズ・インターナショナル,燃焼の科学と技術,7:249-263 2000
Structure of Gaseous Detonation and Reflection and Diffraction Phenonena

回折する衝撃波の挙動に関する研究 : 第1報, 衝撃波の回折と反射過程
日本機械学会,日本機械学會論文集. B編,65(639):3602-3607 199911
高藤亮一、山中昭央、小原哲郎、蔡品、大八木重治
As is well known when a shock wave is emitted from an open end of a tube, an expansion wave and a vortex ring are generated behind the shock wave. Furthermore, a contact surface, slip line and these wave interactions may cause considerably complicate flow-fields. In this study, shock waves of Mach number 1.3, 1.6 and 2.2 are produced utilizing diaphragm-less shock tube of 50 mm diameter and c. a. 10 m total length, and the flow-fields are visualized with an aid of schlieren optical techniques. A cylindrical reflector is installed at test section and stagnation pressure behind reflected shock wave is measured with wide frequency response. A numerical analysis is also carried out to investigate these flow-fields using Predictor-Corrector TVD finite difference scheme. As a result, (i) the contour of diffracted shock wave is well coincided between experimental and numerical results, (ii) pressure histories behind reflected shock wave are clarified, (iii) an empirical formula is obtained between Mach number, non-dimensional distance from the open end of the tube and non-dimensional pressure just behind reflected shock wave.
Compressible Flow, Computational Fluid Dynamics, Shock Wave, Flow Visualization
A Study on Behavior of Diffracted Shock Wave (1st Report, Process of Shock Wave Diffraction and Reflection), Transactions of the Japan Society of Mechanical Engineers, Series B
リポジトリ

後向きステップ後方に安定化される平面的拡散火炎に関する数値解析
,日本機械学會論文集. B編,65(632):1446-1451 1999
Numerical Study on a Planar Diffusion Flame Stabilized behind a Backward-facing Step, Transactions of the Japan Society of Mechanical Engineers, Series B

Diffusion Flame Stabilized on a Porous Plate in a Parallel Airstream
,AIAA Journal,36(11):1945-1952 1998

フィルムデトネーション波開始過程の可視化(流体工学, 流体機械)
日本機械学会,日本機械学會論文集. B編,63(612):2700-2706 199708
渡辺真次、小原哲郎、吉橋照夫、大八木重治
The detonation wave caused by the combustion of a liquid fuel film coated on an inner tube wall has recently attracted considerable attention because of its possible role in explosion hazards in compressed oxygen pipelines. This type of detonation is known as "film detonation" and is classified as a heterogeneous detonation. The structure of a heterogeneous detonation wave is very complex because physical processes such as momentum, heat and mass exchanges between liquid film and the gas phase are coupled with a chemical reaction. Experiments are conducted to investigate the initiation process of film detonation using high-speed schlieren photography and direct photography. It is clearly observed that a secondary shock wave caused by the combustion of liquid fuel film plays a significant role in the transition of film detonation wave.
Detonation, Combustion Phenomena, Flow Visualization, Shock Wave, Pressure Wave
Visualization of Initiation Processes of Film Detonation, Transactions of the Japan Society of Mechanical Engineers, Series B
リポジトリ

High-speed Photography and Stress Gauge Studies of Jet Impact upon Surfaces
,Philosophical Transaction Royal Society of London,A-355:607-623 1997

A High-Speed Photographic Study of the Transition from Deflagration to Detonation Wave
,Shock Waves,6(4):205-210 1996

The Impact and Penetration of a Water Surface by a Liquid Jet
,Proc. Royal Society of London,A-452:1497-1502 1996

A Stress Gauge for Use in Electrically Noisy Environments
,Meas. Sci. Technology,6(12):1659-1661 1995

Liquid-Jet Impact on Liquid and Solid Surfaces
,Wear,186/187:388-394 1995

The Construction and Calibration of an Inexpensive PVDF Stress Gauge for Fast Pressure Measurements
,Meas. Sci. Technology,6(4):345-348 1995

Cavitation Phenomena in Extracorporeal Microexplosion Lithotripsy
,Shock Waves,3(3):149-157 1994

デフラグレーション波からデトネーション波への遷移過程 : 障害物の影響
日本機械学会,日本機械学會論文集. B編,59(567):3552-3556 199311
大八木重治、小原哲郎、吉橋照夫、矢島智
Transition processes from deflagration to detonation waves in stoichiometric oxyhydrogen mixtures diluted with nitrogen were observed using high-speed Schlieren photography as well as pressure and ionization current measurements. In this study, effects of obstacles on the transition processes were investigated. The obstacles were multigutter shaped and were installed near an ignition plug on an inner wall of a rectangular tube. Width and depth of the gutter were selected as parameters while composition of the mixture was fixed. It was revealed that there exist optimum values of these parameters for enhancing the transition to detonation.
Detonation, Premixed Combustion, Shock Wave, Flow Visualization, Deflagration, Transition
Transition Processes from Deflagration to Detonation Waves (Effects of Obstacles), Transactions of the Japan Society of Mechanical Engineers, Series B
リポジトリ

衝撃波フォーカシングと肝損傷－その病態と機序の検討－
,胆道,5(1):11-20 1991

水中微小爆発による衝撃波フォーカッシング医療応用への基礎研究
,日本機械学會論文集. B編,57(539):2285-2292 1991
Underwater Shock Wave Focusing by Microexplosions, a Medical Application, Transactions of the Japan Society of Mechanical Engineers, Series B

閉じた回転楕円体容器内での水中衝撃波フォーカッシングによる超高圧生成についての研究
,工業火薬,52(4):301-306 1991

弱い衝撃波と気泡の干渉に関する一実験 (単一および2個の気泡の崩壊時に発生する液体マイクロジェットの挙動)
,日本機械学會論文集. B編,56(526):1583-1587 1990
An Experiment on the Interation between a Weak Plane Shock Wave and Bubbles (Behavior of Liquid Microjet Produced by Collapse of Single and Double Bubbles), Transactions of the Japan Society of Mechanical Engineers, Series B

水中衝撃波のフォーカッシンング現象と高圧発生のメカニズム
,日本機械学會論文集. B編,56(526):1579-1582 1990
Focusing of Underwater Shock Waves and the Mechanism of High-Pressure Generation, Transactions of the Japan Society of Mechanical Engineers, Series B

体外衝撃波による胆石の被破砕性の検討
,胆道,4(4):451-459 1990

衝撃波による複数空気泡の崩壊に関する一実験
,日本機械学會論文集. B編,53(495):3141-3145 1987
An Experimetal Study on the Collapse of Multiple Air-Bubbles by a Shock Wave, Transactions of the Japan Society of Mechanical Engineers, Series B

Presentation
スリットから回折したデトネｰション波の再開始に関する可視化観察
第48回燃焼シンポジウム,第48回燃焼シンポジウム講演論文集:514-515 201012
菅原 崇, 沈 志剛, 小原 哲郎, 大八木 重治

凹凸壁面を有する流路におけるデトネｰション波遷移過程の可視化観察
第48回燃焼シンポジウム,第48回燃焼シンポジウム講演論文集:516-517 201012
小林 達典, 岩田 脩平, 小原 哲郎, 大八木 重治

スクラムジェットエンジン燃焼器モデル内における超音速燃焼過程
平成21年度衝撃波シンポジウム,平成21年度衝撃波シンポジウム講演論文論文集:301-302 201003
名倉功、相川温史、小原哲郎、大八木重治、吉橋照夫

回折したデトネーション波の再開始過程
平成21年度衝撃波シンポジウム,平成21年度衝撃波シンポジウム講演論文論文集:295-296 201003
沈志剛、菅原崇、小原哲郎、大八木重治、吉橋照夫

ロータリーバルブを装着したパルスデトネーションエンジンの安定作動に関する研究
平成21年度衝撃波シンポジウム,平成21年度衝撃波シンポジウム講演論文論文集:227-230 201003
中込大輔、吉田健司、吉橋照夫、小原哲郎、大八木重治

水素 空気予混合気への衝撃波入射により生成される燃焼波の挙動
平成21年度衝撃波シンポジウム,平成21年度衝撃波シンポジウム講演論文論文集:73-76 201003
今井健太、大須賀尚文、小原哲郎、大八木重治、吉橋照夫

二気筒パルスデトネーションタービンエンジンの研究
平成21年度衝撃波シンポジウム,平成21年度衝撃波シンポジウム講演論文論文集:231-232 201003
澁谷大智、矢部仁識、吉橋照夫、小原哲郎、大八木重治

ロｰタリｰバルブを用いたパルスデトネｰションエンジンに関する研究(紙面発表)
平成22年度衝撃波シンポジウム,平成22年度衝撃波シンポジウム講演論文集:231-232 2010
吉田 健司, 浅見 亮輔, 吉橋 照夫, 小原 哲郎, 大八木 重治

火炎と衝撃波の干渉によるデトネｰション波開始過程の可視化観察(紙面発表)
平成22年度衝撃波シンポジウム,平成22年度衝撃波シンポジウム講演論文集:391-394 2010
小山田 拓, 清田 涼輔, 小原 哲郎, 大八木 重治, 吉橋 照夫

水素及び空気噴射によるDDT過程の研究(紙面発表)
平成22年度衝撃波シンポジウム,平成22年度衝撃波シンポジウム講演論文集:387-390 2010
矢部 仁識, 内藤 正樹, 吉橋 照夫, 小原 哲郎, 大八木 重治

二気筒パルスデトネｰションエンジンによる燃焼過程の研究およびガスタｰビン性能評価(紙面発表)
平成22年度衝撃波シンポジウム,平成22年度衝撃波シンポジウム講演論文集:233-236 2010
澁谷 大智,齋藤 亘, 吉橋 照夫, 小原 哲郎, 大八木 重治

凹凸壁面におけるデトネーション波遷移過程の可視化観察
第47回燃焼シンポジウム,第47回燃焼シンポジウム講演論文集:386-387 200912
小林達典、岡田、小原哲郎、大八木重治

凹凸壁面におけるDDT過程の可視化観察
第53回宇宙科学技術連合講演会,第53回宇宙科学技術連合講演会講演集(CD-ROM):1424-1425 200909
小林達典、岡田安正、小原哲郎、大八木重治

ロータリーバルブを用いたPDEの特性改善について
第41回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2009,第41回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2009講演集:365-368 200906
中込大輔、澁谷大智、吉橋照夫、小原哲郎、大八木重治

水素 空気予混合気体への衝撃波入射により生じる燃焼波の挙動
第41回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2009,第41回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2009講演集:377-378 200906
今井健太、竹内樹美男、小原哲郎、大八木重治