Performance information

• Experiments on critical behavior of oblique detonation wave in stratified mixtures
  Kazuya Iwata; Naoki Hanyu; Shinichi Maeda; Tetsuro Obara
  Physics of Fluids, Volume：36, Number：9, First page：096113, Sep. 2024, [Reviewed]
  Two-stage gas-gun ballistic experiments are performed to investigate the feasibility of stratified mixtures with variable global equivalence ratios Φglobal for the formation of sphere-induced oblique detonation wave (ODW) and quantify their critical behaviors, which include local quenching and transitional structure to ODW, by testing conventional detonation criteria for uniform mixtures. 2 Φglobal H2 + O2 + 3Ar mixtures are tested with different concentration gradients for each fuel-lean/fuel-rich global composition. Opposite responses are observed depending on the global equivalence ratio: the lean mixture of Φglobal = 0.7, which forms ODW in the uniform mixture, fails partly in the strongest stratification, whereas the richest mixture of Φglobal = 2.0 turns to ODW in the strongly stratified conditions. As elucidated in the authors' previous work, Chapman–Jouguet (C–J) theory, including the curvature effects, reproduces the wave angles of the stable ODWs, as well as provides a good prediction on the local quenching of ODW occurring in the area with less reactive composition. Comparison of different wave regimes observed in the explored conditions reveals that wave curvature governs the critical behaviors of ODW far away from the projectile, whereas the initiation structure around the projectile is also influenced by the non-dimensional diameter. Surface energy theory is proven to quantify well the initiation structure on the projectile using a local equivalence ratio. These results indicate a new possibility of controlling the methodology of ignition and stabilization of detonation in aerospace engines, in which perfect mixing is difficult and non-stoichiometric and non-uniform mixtures are expected.
  AIP Publishing, English, Scientific journal
  DOI：https://doi.org/10.1063/5.0225498
  DOI ID：10.1063/5.0225498, ISSN：1070-6631, eISSN：1089-7666
• Flame acceleration process and detonation transition in a channel with roughness elements on a wall　　　　　　　　　　　　　　　
  Shinichi Maeda; Masahiro Irokawa; Daiki Taneichi; Tetsuro Obara
  Proceedings of the Combustion Institute, Volume：39, Number：3, First page：2767, Last page：2776, 2023, [Reviewed], [Lead]
  Elsevier BV, English, Scientific journal
  DOI：https://doi.org/10.1016/j.proci.2022.07.224
  DOI ID：10.1016/j.proci.2022.07.224, ISSN：1540-7489
• Experimental visualization of sphere-induced oblique detonation in a non-uniform mixture　　　　　　　　　　　　　　　
  Kazuya Iwata; Naoki Hanyu; Shinichi Maeda; Tetsuro Obara
  Combustion and Flame, Volume：244, First page：112253, 2022, [Reviewed]
  Elsevier BV, English, Scientific journal
  DOI：https://doi.org/10.1016/j.combustflame.2022.112253
  DOI ID：10.1016/j.combustflame.2022.112253, ISSN：0010-2180
• Effect of sandpaper-like small wall roughness on deflagration-to-detonation transition in a hydrogen-oxygen mixture　　　　　　　　　　　　　　　
  Shinichi Maeda; Masashi Fujisawa; Shogo Ienaga; Keisuke Hirahara; Tetsuro Obara
  Proceedings of the Combustion Institute, Volume：37, Number：3, First page：3609, Last page：3616, 2019, [Reviewed]
  Deflagration-to-detonation transition (DDT) in a stoichiometric hydrogen-oxygen mixture was experimentally investigated using a channel with a sandpaper-like rough wall as a small blockage. The combustion channel was 486 mm long, 12 mm wide, and 10 mm high in the inner cross-section, and the top and bottom walls were covered with a sand cloth with surface roughness of 1000 μm by Rz and 100 μm by Ra (rough wall condition). The channel wall without the sand cloth (polished wall condition) was also tested for comparison. The entire process from the flame propagation following spark ignition to the detonation transition was visualized through optical windows on the side walls by high-speed schlieren photography. Although only the slow subsonic flame was observed in the polished wall condition, the wall roughness greatly enhanced flame acceleration and the detonation transition occurred at 120 mm downstream from the ignition. In the rough wall condition, the reaction front along the channel wall, which might propagate in the unreacted gas in the many cavities between the flame edge and the rough wall, was observed. This reaction front finally developed to form the high-speed tulip flame. The prominent reaction front near the channel wall and the accumulation of compression waves (the precompression zone), which increased the pressure up to 10-15 times the initial pressure, were observed immediately ahead the tulip flame, and this triggered the detonation onset. The estimated temperature in the precompression zone of 600-700 K was not high enough to induce instantaneous self-ignition. The present observation might indicate the experimental evidence for the possible mechanism of the final detonation onset, which was local spontaneous flame acceleration coupled with the compression wave immediately ahead of the flame front; which was suggested for highly reactive mixtures (Liberman et al. 2010).
  English, Scientific journal
  DOI：https://doi.org/10.1016/j.proci.2018.07.119
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  DOI ID：10.1016/j.proci.2018.07.119, ISSN：1540-7489, SCOPUS ID：85051328863
• Oblique Detonation on a Spherical Body Formed in Hydrogen Concentration Gradient　　　　　　　　　　　　　　　
  IWATA Kazuya; YAMASAKI Hiroshi; TOMITA Keita; YOSHIKI Isshu; MAEDA Shinichi; OBARA Tetsuro; NAKAYA Shinji; TSUE Mitsuhiro; IMAMURA Osamu; AKIHAMA Kazuhiro
  Journal of the Combustion Society of Japan, Volume：60, Number：192, First page：124, Last page：132, 2018, [Reviewed]
  

  Oblique detonation wave (ODW) in a non-uniform mixture was investigated using a two-stage light gas gun through a high-speed Schlieren photography. The concentration gradient was formed with hydrogen injection and controlled by the waiting time. Helium was used instead of hydrogen to measure the gradient by gas sampling. As the results, asymmetric curved ODW front appeared due to variable Chapman-Jouguet (C-J) speed. Asymmetric Straw-Hat type structure was also observed depending on the waiting time in which stabilized/attenuated ODW accompanied Straw Hat type structure above/below the projectile. Comparison to the cases of the uniform mixtures also revealed that the range of equivalence ratio for which ODW can be observed increases in the far field due to the absence of attenuation by the curvature effect and expansion wave, indicating that the criterion based on non-dimensional diameter is not always valid. In addition, one low-speed experimental case encountered a locally propagating detonation in a fuel-richer region, which can be attributed to a locally larger C-J speed exceeding the projectile speed.

  
  Combustion Society of Japan, Japanese, Scientific journal
  DOI：https://doi.org/10.20619/jcombsj.60.192_124
  DOI ID：10.20619/jcombsj.60.192_124, ISSN：1347-1864, CiNii Articles ID：130006736246, CiNii Books ID：AA11658490
• Time-resolved schlieren observations of shock-induced combustion around a high-speed spherical projectile　　　　　　　　　　　　　　　
  Shinichi Maeda; Shoichiro Kanno; Isshu Yoshiki; Tetsuro Obara
  Science and Technology of Energetic Materials, Volume：78, Number：1-2, First page：19, Last page：26, 2017, [Reviewed]
  Shock-induced combustion around a supersonic spherical projectile was experimentally investigated by high-time- resolution schlieren imaging using a high-speed camera. A projectile of 4.76 mm diameter was launched by a gas gun into a C2H4+3O2+12Ar mixture with the initial pressure varied between 25 and 150 kPa. The Mach number of the projectile ranged from 4.0 to 5.9. which corresponded to 0.7 to 1.1 times the propagation Mach number of the Chapman-Jouguet (C- J) detonation (C-J detonation Mach number). Various combustion regimes, including combustion instabilities with an oscillating combustion front, were observed, and the trend of these regimes was validated using the parameters of a chemical reaction and propagation of the pressure wave driven by a chemical reaction behind the shock wave on the stagnation streamline. Heat release rate parameter, q' was defined as the maximum temperature gradient in a reaction zone divided by a post-shock temperature assuming a constant-volume explosion, and the time scale, f ∗ for propagation of the pressure wave was defined as the projectile diameter divided by the difference between a sound speed and a flow velocity at a post-shock state. When the Mach number of the projectile exceeded approximately 0.9 times the C-J detonation Mach number, the induction length was considerably shorter than the scale of the projectile. In this case, the observed combustion regimes tended to exhibit oscillating combustion with a larger scale as the dimensionless heat release rate parameter became larger, which was defined as the product of the q' and /∗. This trend was in accordance with the one-dimensional consideration of the stagnation streamline in previous numerical studies using hydrogen-fueled mixtures. This was also confirmed by directly observing that the bow shock on the stagnation streamline was temporally oscillating by coupling with the rapid reaction. In contrast, when the Mach number of the projectile was approximately 0.7 to 0.8 times the C-J detonation Mach number, the induction length was comparable with the scale of the projectile. In this case, the mode of oscillating combustion did not exhibit a specific trend when plotted against the dimensionless heat release rate parameter. These experimental results revealed that one-dimensional considerations are insufficient for determining the combustion regime. The observed combustion regime also indicated that the evolution of the reaction front was probably affected by the flow field formed by the aft body of the projectile.
  English, Scientific journal
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  ISSN：1347-9466, CiNii Articles ID：40021226036, SCOPUS ID：85026504704
• Detonation initiation in a channel via facing injection of flame jets　　　　　　　　　　　　　　　
  MAEDA Shinichi; AOSHIMA Ryota; KUROSAWA Tetsuro; OBARA Tetsuro
  Transactions of the JSME (in Japanese), Volume：83, Number：846, First page：16, Last page：00269-16-00269, 2017, [Reviewed]
  

  Detonation transition was experimentally investigated using flame jetting through the orifice of a small sub-chamber, which was equipped on the side wall near the closed end of the main channel (square inner closs section, 50 mm on a side) filled with a stoichiometric hydrogen-oxygen mixture at an initial pressure of 80 kPa. The number of sub-chambers and orifice diameters were changed as 1, 2, 4 (called as FJ1, FJ2, FJ4, respectively) and 3, 5, 7 mm, respectively, and the facing flame jets were collided with each other in FJ2 and FJ4. Two regimes of detonation transition were observed: (i) deflagration-to-detonation transition (DDT) accompanied by flame acceleration process and (ii) direction initiation of a detonation near the flame jetting section. The flame propagation distance required for detonation transition was one-half to one-third for regime (i) compared to single-spark ignition without flame jet, and below one-sixth for regime (ii). Except for the case of regime (ii), observed for an orifice diameter of 5 or 7 mm of FJ4, the detonation transition distance had no significant effect on the types of flame jetting and orifice diameters. Time-resolved schlieren recordings showed that the choked jet of combustion products drove the shock wave preceding the flame front, and induced multi-dimensional flame motion and repeated shock-flame interactions in the confinement. These behaviors enhanced flame velocity at the ignition end by a factor of 4 to 7 in FJ1 and FJ2, compared to single-spark ignition. The effect of these enhanced flame velocities on DDT distances was consistent with the semi-empirical model of flame acceleration process in a smooth tube. The schlieren recordings and pressure measurements at the closed end indicated that the possible factors for the initiation of detonation in regime (ii) were the mixing of reacted and unreacted gas induced by the repeated strong shock-flame interaction and the hot spot formed by shock-shock interaction driven by the facing flame jetting.

  
  The Japan Society of Mechanical Engineers, Japanese, Scientific journal
  DOI：https://doi.org/10.1299/transjsme.16-00269
  DOI ID：10.1299/transjsme.16-00269, CiNii Articles ID：130005402100
• Detonation transition process caused by interaction of convex flame with planar shock wave　　　　　　　　　　　　　　　
  MAEDA Shinichi; KURAMOCHI Yuki; ONO Ryo; OBARA Tetsuro
  Transactions of the JSME (in Japanese), Volume：83, Number：850, First page：17, Last page：00049-17-00049, 2017, [Reviewed]
  

  This study addressed a deflagration-to-detonation transition (DDT) process after interaction of the convex flame with a planar shock wave. High-speedvideo cameras and schlieren optical technique were utilized to observe the DDT as well as shock-flame interaction processes. A double-diaphragmshock tube was used to produce the shock wave, while the flame was produced by igniting a premixed gas of stoichiometric methane-oxygenat the observation section. Experiments were conducted by changing Mach number of the incident shock wave, M_s and a distance of flame front from the end wall, x₀. As a result of schlieren photographs, flame propagation behaviors at initial stage were classified into four patterns, named as (a) coupling, (b) concave, (c) partial coupling and (d) convex type. The propagation patterns of flame were highly dependent on the initial position of flame front, x₀. Under the experimental conditions, DDT was not observed when the flame had been propagated revealing (a) coupling (observed with the conditions of x₀ > 110 mm) and (d) convex type (x₀ < 50 mm). However, the DDT was observed following that the flame had been propagated revealing (b) concave or (c) partial coupling (50 < x₀ < 110 mm). Furthermore, it was elucidated that DDT was typically caused through the following processes. (i) When the convex flame interacted with planar shock, the unburned gas was penetrated into burned gas inducing Richtmyer-Meshkov instability. (ii) The flame was highly accelerated at boundary layers behind the reflected shock. (iii) After accelerated flame propagated through the unburned shocked region, local explosion was occurred on the wall followed by detonation onset.

  
  The Japan Society of Mechanical Engineers, Japanese, Scientific journal
  DOI：https://doi.org/10.1299/transjsme.17-00049
  DOI ID：10.1299/transjsme.17-00049, CiNii Articles ID：130006943403
• Occurrence conditions for unsteady combustions in shock-induced combustions around spherical projectiles　　　　　　　　　　　　　　　
  MAEDA Shinichi; YOSHIKI Isshu; KANNO Shoichiro; TOMITA Keita; OBARA Tetsuro
  Transactions of the JSME (in Japanese), Volume：83, Number：852, First page：17, Last page：00019-17-00019, 2017, [Reviewed]
  

  Shock-induced combustion around a spherical body was experimentally investigated by launching the projectile at supersonic speed into a combustible mixture. This study focused on occurrence conditions for an unsteady combustion which was characterized as combustion instabilities with an oscillating combustion front. A spherical body of 4.76 mm dimeter was used as the projectile, and its flight Mach numbers were ranged from 3.5 to 7.5. Four types of combustible mixtures, which were stoichiometric hydrogen-oxygen and ethylene-oxygen mixtures diluted with argon or nitrogen (2H₂ + O₂ + 3Ar, 2H₂ + O₂ + N₂, C₂H₄ + 3O₂ + 12Ar, C₂H₄ + 3O₂ + 2.5N₂), were used and their initial pressures were varied between 25 and 100 kPa. The combustion regimes around the projectile were observed by using a schlieren optical system and high-speed camera. The combustion regimes generally varied from the steady combustion with smooth combustion front to the unsteady combustion with oscillating combustion front, when the projectile Mach number or the initial pressure increased. The occurrence conditions for the unsteady combustion were expressed by the two dimensionless parameters; dimensionless heat release rate, q^*t^* and dimensionless induction length, l_ind^*, which were defined by the post-shock state and flow velocity on the stagnation streamline of the projectile and by assuming the chemical reaction as a constant-volume explosion. The q^*t^* included a temperature gradient in a reaction zone, and represented the strength of the pressure wave driven by the heat release reaction. The l_ind^* included an induction time, and represented the distance between the shock wave and the location where the heat release reaction started. The unsteady combustion occurred when these two dimensionless parameters were above the critical values, and the trend of occurrence condition of the two combustion regimes could be explained by introducing the parameters.

  
  The Japan Society of Mechanical Engineers, Japanese, Scientific journal
  DOI：https://doi.org/10.1299/transjsme.17-00019
  DOI ID：10.1299/transjsme.17-00019, CiNii Articles ID：130006004003
• Effect of propagation of a reflected shock wave on a pressure field when a detonation wave reflects on an end wall of a tube with opened or closed ignition end　　　　　　　　　　　　　　　
  MAEDA Shinichi; OIKAWA Yosuke; HOSHINO Ryusuke; OBARA Tetsuro
  Transactions of the JSME (in Japanese), Volume：83, Number：852, First page：17, Last page：00039-17-00039, 2017, [Reviewed]
  

  A detonation wave propagating in a straight tube (detonation tube) was reflected off the end wall of the tube, and the pressure profile produced by the propagation of the reflected shock wave was experimentally investigated. The detonation wave was initiated at the opposite end of the reflection end, and two ignition conditions were tested. First, ignition at the closed end of the tube (called as "closed ignition end condition"), where the fluid motion was negligible, was evaluated. Second, ignition at the open end of the tube (called as "opened ignition end condition"), where the burned gas flowed toward the vacuum tank attached to the detonation tube, was evaluated. Karnesky et al. (2013) suggested the empirical model in order to represent the pressure profile near the reflection end in the closed ignition end condition. In this paper, the empirical model of Karnesky et al. was modified in order to represent the pressure profile in the opened ignition end condition, and the effect of two ignition conditions on the pressure profiles was discussed. In these models, the pressure profile at the reflection end was empirically formulated by using two empirical parameters, and a uniform pressure distribution between the reflected shock wave and the reflection end was assumed. In this paper, the empirical parameters were normalized by the characteristic parameters for the propagating reflected shock wave. These parameters expressed the conditions of the combustible mixture and the length of the detonation tube. In the opened ignition end condition, the model well represented the measured pressure profile created by the propagating detonation wave and reflected shock wave in the entire length of the detonation tube because the rarefaction wave existed in the entire region behind the detonation wave, and the pressure behind the reflected shock wave had an approximately uniform distribution. Conversely, the model was applicable for a limited duration for the closed ignition end condition because a pressure gradient gradually developed behind the reflected shock wave when the reflected shock wave began to propagate in the plateau region behind the rarefaction wave.

  
  The Japan Society of Mechanical Engineers, Japanese, Scientific journal
  DOI：https://doi.org/10.1299/transjsme.17-00039
  DOI ID：10.1299/transjsme.17-00039, CiNii Articles ID：130006004001
• Visualization of deflagration-to-detonation transitions in a channel with repeated obstacles using a hydrogen–oxygen mixture　　　　　　　　　　　　　　　
  S. Maeda; S. Minami; D. Okamoto; T. Obara
  Shock Waves, Volume：26, Number：5, First page：573, Last page：586, Sep. 2016, [Reviewed]
  © 2016, Springer-Verlag Berlin Heidelberg. The deflagration-to-detonation transition in a 100 mm square cross-section channel was investigated for a highly reactive stoichiometric hydrogen oxygen mixture at 70 kPa. Obstacles of 5 mm width and 5, 10, and 15 mm heights were equally spaced 60 mm apart at the bottom of the channel. The phenomenon was investigated primarily by time-resolved schlieren visualization from two orthogonal directions using a high-speed video camera. The detonation transition occurred over a remarkably short distance within only three or four repeated obstacles. The global flame speed just before the detonation transition was well below the sound speed of the combustion products and did not reach the sound speed of the initial unreacted gas for tests with an obstacle height of 5 and 10 mm. These results indicate that a detonation transition does not always require global flame acceleration beyond the speed of sound for highly reactive combustible mixtures. A possible mechanism for this detonation initiation was the mixing of the unreacted and reacted gas in the vicinity of the flame front convoluted by the vortex present behind each obstacle, and the formation of a hot spot by the shock wave. The final onset of the detonation originated from the unreacted gas pocket, which was surrounded by the obstacle downstream face and the channel wall.
  English, Scientific journal
  DOI：https://doi.org/10.1007/s00193-016-0660-1
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  DOI ID：10.1007/s00193-016-0660-1, ISSN：0938-1287, SCOPUS ID：84966333715
• Detonation transition process in a channel equipped with the repeated obstacles (Effect of obstacle height and spacing on the DDT process)　　　　　　　　　　　　　　　
  MAEDA Shinichi; MINAMI Shohei; OKAMOTO Daisuke; OBARA Tetsuro
  Transactions of the JSME (in Japanese), Volume：82, Number：834, First page：15, Last page：00468-15-00468, 2016, [Reviewed]
  Experiments were performed to investigate the deflagration-to-detonation transition (DDT) process in the channel equipped with repeated obstacles. A premixed gas of hydrogen-oxygen was ignited and the DDT process was visualized by using a high-speed video camera with an aid of schlieren optical method. A configuration of the repeated obstacle such as a spacing, d and a height, h were varied to investigate effects of these parameters on the detonation induction distance (DID) as well as DDT process. Furthermore, the flow-field was visualized by changing the directions of obstacle installation, such as vertical installation and transverse one. The DDT process could be clarified in detail, because the transverse installation of obstacle could acquire the flow-field in depth direction of the obstacle. As a result, it was clarified that the DDT was occurred by highly accelerated flame caused by the interaction between deflagration wave and the vortex-ring behind obstacle. Thus, the vortex-ring generated by the diffraction of compression waves was interacted with the deflagration wave, and this behavior produced a high-velocity deflagration wave through the unburned gas pocket behind obstacle. This high-velocity deflagration wave propagated in the depth direction could be a trigger of DDT onset via local-explosion. The detonation induction distance was also determined by observing a fish-scale pattern on the soot which was typical of the detonation propagation, and the relationship between DID and the configurations of repeated obstacle was also obtained.
  The Japan Society of Mechanical Engineers, Japanese, Scientific journal
  DOI：https://doi.org/10.1299/transjsme.15-00468
  DOI ID：10.1299/transjsme.15-00468, CiNii Articles ID：130005129135
• Initiation of detonation wave in a non-uniform hydrogen-air premixed gas　　　　　　　　　　　　　　　
  MAEDA Shinichi; TERAOKA Takumi; OIKAWA Yosuke; OBARA Tetsuro; KAGEYAMA Kensuke
  Transactions of the JSME (in Japanese), Volume：82, Number：834, First page：15, Last page：00503-15-00503, 2016, [Reviewed]
  There is increasing interest in the use of hydrogen as an energy source in fuel cells, and such cells are expected to find practical applications in the near future. However, the reaction rate of a hydrogen-air mixture is so high that the deflagration wave generated during ignition can easily become a detonation wave, even though only a small amount of energy is supplied to the premixed gas. Such a detonation wave can cause serious damage because of the high-pressure and temperature at the wavefront. Despite such concerns, the onset conditions for producing a detonation wave in a non-uniform mixture of hydrogen and air have not yet been fully clarified. In the present study, these conditions were investigated by changing the concentration of hydrogen to understand the onset condition of detonation wave. A vertical detonation tube was divided into two chambers using a slide valve; the upper chamber was filled with air and the lower chamber with hydrogen. A hydrogen concentration gradient was produced by opening the valve for a specific period of time. A pair of electret sensors was used to determine the concentration of hydrogen and the equivalence ratio by measuring the speed of sound in the premixed gas. The onset conditions for detonation were investigated by changing the overall equivalence ratio, φ, and the elapsed time, t_d, from the onset of diffusion. It was found that for φ= 1.67 and t_d ≥ 540 s, a detonation wave was produced leading to a large increase in pressure. Furthermore, the results indicated that the local equivalence ratio in the vicinity of the spark plug had an important influence on the initiation of the detonation wave.
  The Japan Society of Mechanical Engineers, Japanese, Scientific journal
  DOI：https://doi.org/10.1299/transjsme.15-00503
  DOI ID：10.1299/transjsme.15-00503, CiNii Articles ID：130005129128
• Experimental study on acceleration of projectile by a gaseous detonation-driven gas gun using a light gas　　　　　　　　　　　　　　　
  Shinichi Maeda; Shoichiro Kanno; Isshu Yoshiki; Tetsuro Obara
  Science and Technology of Energetic Materials, Volume：77, Number：3-4, First page：79, Last page：85, 2016, [Reviewed]
  Experiments were conducted to investigate the gaseous detonation-driven gas gun in which the driving source was the high-pressure combustion products behind the detonation waves propagating inside the simple straight tube (called detonation tube), and demonstrated that the acceleration of the projectile reached to the supersonic or hypersonic speeds. As the simplest configuration, the single-stage gun was tested directly connecting the detonation tube with the launch tube. When the detonation wave was driven by the hydrogen-oxygen mixture, the gun could accelerate the spherical projectile of 4.76 mm diameter and 52 mg mass up to 1400 m s"1. The dilution of the hydrogen-oxygen mixture with the helium gas within 30% of the volumetric fraction had an insignificant effect on the projectile acceleration, and the reason was explained from the thermodynamic properties of the combustion products. However, the increase of the dilution rate to 40% caused to increase the projectile velocity up to 1600 m s"1. This was owing to the arrival of the overdriven detonation at the launch tube, because the location of the detonation transition shifted to the downstream section of the detonation tube. In these experiments, the detonation-driven gas gun could obtain experimentally two to three times the projectile velocities compared to the theoretical velocities of the conventional single-stage light-gas gun driven by the pure hydrogen or helium gas under the same gun geometry and the filling pressure. The two-stage gun driven by the hydrogen-oxygen detonation was also tested by using the same detonation tube. The pump tube was added downstream of the detonation tube to compress the pure helium gas using the free piston driven by the detonation products. The detonation driver successfully established the pumping process of the helium gas in the pump tube. The velocities obtained in this study were up to around 2500 m s"1, and these results were about 1.8 times higher than the velocities of the single-stage gun using the same detonation driver.
  English, Scientific journal
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  ISSN：1347-9466, CiNii Articles ID：40020915806, SCOPUS ID：84995794123
• Experiment of projectile acceleration using a gaseous detonation driven gas gun　　　　　　　　　　　　　　　
  MAEDA Shinichi; KANNO Shoichiro; KOTO Ryohei; OBARA Tetsuro
  Transactions of the JSME (in Japanese), Volume：81, Number：822, First page：14, Last page：00332-14-00332, 2015
  The gaseous detonation driven gas gun was developed for accelerating the projectile to a supersonic speed. The gas gun was simply consisted of two straight stainless-steel tubes. The one was the detonation tube and the other was the launch tube. The detonation tube was 50 mm inside diameter with 2180 or 4280 mm long, and the launch tube was 5 mm inside diameter with 1040 mm long. Chapman-Jouguet detonation wave was initiated in the detonation tube, and the projectile was accelerated in the launch tube via combustion products behind the detonation wave. The spherical projectile of 4.76 mm diameter was made of high-density polyethylene with 52 mg mass. The driver mixture was stoichiometric hydrogen-oxygen premixed gas with initial pressure ranging from 120 to 450 kPa. The gas gun was successfully operated, and the maximum projectile velocity of 1400 m/s was obtained for the conditions that the detonation tube was 4280 mm long and the initial pressure of the driver gas was 450 kPa. The results of the longer detonation tube demonstrated that the projectile velocity was 1.15 - 1.25 times higher than the case of shorter detonation tube. This velocity change of the projectile could be explained by the pressure increase at the inlet of the launch tube by using longer detonation tube. The reason of the pressure increase has a possibility that the length of Taylor wave behind the detonation wave becomes longer for the case of longer detonation tube.
  The Japan Society of Mechanical Engineers, Japanese
  DOI：https://doi.org/10.1299/transjsme.14-00332
  DOI ID：10.1299/transjsme.14-00332, CiNii Articles ID：130005005046
• Scale effect of spherical projectiles for stabilization of oblique detonation waves　　　　　　　　　　　　　　　
  S. Maeda; S. Sumiya; J. Kasahara; A. Matsuo
  Shock Waves, Volume：25, Number：2, First page：141, Last page：150, 2015, [Reviewed]
  © 2015, Springer-Verlag Berlin Heidelberg. Oblique detonation waves (ODWs) were stabilized by launching a spherical projectile with 1.2–1.4 times the Chapman–Jouguet (C–J) velocity into detonable mixtures at rest. We used smaller projectiles (3.18 mm diameter) than those (4.76 mm diameter) in our previous studies and investigated the effect of the projectile scale on the stabilization of ODWs. We carried out high time resolution schlieren visualization using a high-speed camera. The detonable mixtures used were stoichiometric oxygen mixtures with acetylene, ethylene or hydrogen. They were diluted with argon with a 50 % volumetric fraction, and a dilute mixture containing 75 % argon was also tested for the acetylene/oxygen mixture. Here, we discuss the detonation stability in terms of the curvature effect arising from the three-dimensional nature of a stabilized ODW around a projectile. The curvature effect attenuated the detonation wave to below its C–J velocity in the vicinity of the projectile before the wave velocity asymptotically reached the C–J velocity in the far field. Our previous study showed that the propagation limit of the curvature effect is responsible for the stabilizing criticality of detonation waves. By obtaining detailed distributions of the wave propagation velocity and radius of curvature at the stabilizing criticality, we showed that the radius of curvature at the local minimum point of the wave propagation velocity represents the critical radius of curvature required for curved self-sustained detonation. In this study, we focused on this critical mode of the stabilized ODW for a small projectile (3.18 mm diameter). Distributions of the wave velocity and radius of curvature were obtained in the critical mode of the stabilized ODW. We compare these distributions with those for a larger projectile (4.76 mm diameter) and discuss the stabilizing criticality. For the small projectile, the observed combustion regimes had qualitatively the same trend for the initial pressure of the mixture as that observed for the large projectile. However, the initial pressure for each combustion regime was quantitatively different for the different projectile scales. The small projectile required a higher initial pressure to stabilize the ODW than the large projectile. For the critical mode of the stabilized ODW, the wave velocity distribution had a local minimum value (0.8–0.9 times the C–J velocity) due to the curvature effect. The radius of curvature at this characteristic point was about five times the projectile radius, regardless of the mixture composition. The radius of curvature normalized by the cell size was about 8–10 and 15 for mixtures diluted with 50  and 75 % argon, respectively, regardless of the projectile diameter. These results mean that the projectile radius (diameter) proportionally affects the geometrical scale of the wave around the projectile, and the fraction of the gas used for dilution affects the cell size required to sustain a curved detonation wave. The stabilizing criticality, expressed as the dimensionless projectile diameter (projectile diameter normalized by cell size), was about 3.5 and 5.5 for mixtures diluted with 50 and 75 % argon, respectively. These criticalities agreed with those of the large projectile of the previous study. This indicates that the dimensionless projectile diameter is a unique parameter for the stabilizing criticality regardless of the projectile diameter.
  English, Scientific journal
  DOI：https://doi.org/10.1007/s00193-015-0549-4
  Scopus：https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=84925485352&origin=inward
  Scopus Citedby：https://www.scopus.com/inward/citedby.uri?partnerID=HzOxMe3b&scp=84925485352&origin=inward
  DOI ID：10.1007/s00193-015-0549-4, ISSN：0938-1287, SCOPUS ID：84925485352
• Effects of Transversely Flame Jetting into Channel from Sub-chambers on Flame Accelerations and Detonation Transition Distances　　　　　　　　　　　　　　　
  MAEDA Shinichi; AOSHIMA Ryota; KUROSAWA Tetsuro; ICHIKAWA Akinori; OBARA Tetsuro
  Journal of the Combustion Society of Japan, Volume：57, Number：181, First page：222, Last page：231, 2015, [Reviewed]
  

  Sub-chambers were used to initiate the detonation wave by injecting a flame-jet into the detonation tube. A configuration of the sub-chamber was divided into five types by changing the number of sub-chambers and the directions of flame injection. The detonation tube had a cross area of 50 × 50 mm, a length of 775 mm and equipped a window section for a visualization of the flowfield. The test gas was a stoichiometric premixed gas of hydrogen and oxygen and the initial pressure was constant as 80 kPa. The experimental results showed that the detonation transition distance was about 60% shorter than the case of spark ignition without flame-jet. Increasing the number of sub-chambers and colliding flame-jets emanating from counter positions resulted in decreasing the detonation transition distance. Schlieren photographs showed that the flame-jets promoted the formation of leading shock wave ahead of the turbulent flame in a short distance. Pressure measurements on the end wall of the detonation tube indicated that the shock or compression waves were reflected repeatedly in the cross-section, leading to a pressure wave and flame interaction. For the flame-jet initiation using the sub-chambers, generating turbulent flow in the premixed gas was of importance to promote the detonation transition.

  
  Combustion Society of Japan, Japanese, Scientific journal
  DOI：https://doi.org/10.20619/jcombsj.57.181_222
  DOI ID：10.20619/jcombsj.57.181_222, ISSN：1347-1864, CiNii Articles ID：130006320853, CiNii Books ID：AA11658490
• Initiation and sustaining mechanisms of stabilized Oblique Detonation Waves around projectiles　　　　　　　　　　　　　　　
  Shinichi Maeda; Satoshi Sumiya; Jiro Kasahara; Akiko Matsuo
  Proceedings of the Combustion Institute, Volume：34, Number：2, First page：1973, Last page：1980, 2013, [Reviewed]
  Direct initiations and stabilizations of three-dimensional conical detonation waves were attained by launching spheres with 1.06-1.31 times the C-J velocities into detonable mixtures. We conducted high time-resolution Schlieren visualizations of the whole processes over unsteady initiations to stable propagations of the stabilized Oblique Detonation Waves (ODWs) using a high-speed camera. The detonable mixtures were stoichiometric oxygen mixtures with acetylene, ethylene or hydrogen. They were diluted with argon in a 50% volumetric fraction, and a 75% diluted mixture was also tested for the acetylene/oxygen. The direct initiation of detonation by the projectile and the DDT process like the re-initiation appeared in the initiation process of stabilized ODW. This process eventually led to the stabilized ODW supported by the projectile velocity and the ringed shape detonation wave originating in the re-initiation. We modeled the spatial evolution of stabilized ODW after the re-initiation based on its C-J velocity and angle. The model qualitatively reproduced the measured development rate of stabilized ODW. We also discussed about the detonation stability for the curvature effect arising from the three-dimensional nature of stabilized ODW around the projectile. The curvature effect attenuated the detonation wave below its C-J velocity at the vicinity of projectile. The propagation limits of curvature effect will be responsible for the criticality to attain the stabilized ODWs. By accessing the detailed distributions of propagation velocities and curvature radiuses, the critical curvature radiuses normalized by the cell sizes experimentally revealed to be 8-10 or 15-18 for mixtures diluted with each 50% argon or 75% argon/krypton. © 2012 The Combustion Institute. Published by Elsevier Inc. All rights reserved.
  English, Scientific journal
  DOI：https://doi.org/10.1016/j.proci.2012.05.035
  Scopus：https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=84872048916&origin=inward
  Scopus Citedby：https://www.scopus.com/inward/citedby.uri?partnerID=HzOxMe3b&scp=84872048916&origin=inward
  DOI ID：10.1016/j.proci.2012.05.035, ISSN：1540-7489, SCOPUS ID：84872048916
• Oblique detonation wave stability around a spherical projectile by a high time resolution optical observation　　　　　　　　　　　　　　　
  Shinichi Maeda; Jiro Kasahara; Akiko Matsuo
  Combustion and Flame, Volume：159, Number：2, First page：887, Last page：896, Feb. 2012, [Reviewed]
  Spherical projectiles were launched into detonable mixtures over a wide range of projectile velocities from near to about 1.8 times the Chapman-Jouguet (C-J) velocity. Oblique detonation waves (ODWs) and shock-induced combustions (SICs) stabilized around the projectiles were visualized with high time and high spatial resolutions using the Schlieren technique and a high-speed camera with a 1-μs frame speed. Unsteady wave structures called Straw Hat type structures consisting of a SIC region followed by a C-J ODW were observed near stabilizing criticalities of a C-J ODW, and they were divided into two propagation types, depending on whether the C-J ODW could be stabilized [11,12,14]. In the present study, we suggested wave structures of the Straw Hat types based on our examination of dozens of continuous images. Triple points were observed at the intersection of a bow shock, a C-J ODW and a transverse detonation or shock wave when projectile velocities were slightly higher than C-J velocities. Onsets of local explosions in the SIC region for stabilizing the ODW in the Straw Hat type structures have been reported [14]. We observed this stabilizing mechanism by visualizing onsets of periodical local explosions and their transition to spherical detonation waves when the projectile velocity was much higher than the C-J velocity. We also determined stabilizing criticalities using a stoichiometric acetylene-oxygen mixture diluted with argon or krypton in 50% or 75% volumetric fractions, respectively. We found that the stabilizing criticalities did not depend only on the ratio of the projectile diameter and the cell size of the mixture. © 2011 The Combustion Institute.
  English, Scientific journal
  DOI：https://doi.org/10.1016/j.combustflame.2011.09.001
  Scopus：https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=84355162987&origin=inward
  Scopus Citedby：https://www.scopus.com/inward/citedby.uri?partnerID=HzOxMe3b&scp=84355162987&origin=inward
  DOI ID：10.1016/j.combustflame.2011.09.001, ISSN：0010-2180, eISSN：1556-2921, SCOPUS ID：84355162987
• Unsteady Propagation Process of Oblique Detonation Waves Initiated by Hypersonic Spherical Projectiles　　　　　　　　　　　　　　　
  Shinichi Maeda; Jiro Kasahara; Akiko Matsuo
  Volume：10, Number：ists28, First page：Pe_1, Last page：Pe_6, 2012, [Reviewed]
  English, Scientific journal
  DOI：https://doi.org/10.2322/tastj.10.Pe_1
  DOI ID：10.2322/tastj.10.Pe_1
• Visualization of the Non-Steady State Oblique Detonation Wave Phenomena around Hypersonic Spherical Projectile　　　　　　　　　　　　　　　
  Shinichi Maeda; Ryuichi Inada; Jiro Kasahara; Akiko Matsuo
  Volume：33, Number：2, First page：2343, Last page：2349, 2011, [Reviewed]
  English, Scientific journal
  DOI：https://doi.org/10.1016/j.proci.2010.06.066
  DOI ID：10.1016/j.proci.2010.06.066
• Analysis on Thermal Efficiency of Non-Compressor Type Pulse Detonation Turbine Engine　　　　　　　　　　　　　　　
  Shinichi Maeda; Jiro Kasahara; Akiko Matsuo; Takuma Endo
  Volume：53, Number：181, First page：192, Last page：206, 2010, [Reviewed]
  English, Scientific journal
  DOI：https://doi.org/10.2322/tjsass.53.192
  DOI ID：10.2322/tjsass.53.192

• 連続した障害物上におけるデトネーション開始過程に関する可視化観察　　　　　　　　　　　　　　　
  小原 哲郎; 前田 慎市
  Volume：62, Number：200, First page：124, Last page：131, 2020
  Japanese, Introduction scientific journal
• グループ紹介 埼玉大学工学部機械工学・システムデザイン学科熱工学研究室　　　　　　　　　　　　　　　
  前田 慎市
  Volume：28, Number：3, First page：209, Last page：212, 2018
  Japanese
  ISSN：0916-801X, CiNii Articles ID：40021776936, CiNii Books ID：AN10402529
• Symposium on Shock Waves in Japan, 2016　　　　　　　　　　　　　　　
  前田 慎市
  Explosion, Volume：26, Number：2, First page：125, Last page：127, 2016
  Japanese
  ISSN：0916-801X, CiNii Articles ID：40020946370, CiNii Books ID：AN10402529

• Frontiers of Shock Wave Research (Kazuyoshi Takayama and Ozer Igra Eds.)　　　　　　　　　　　　　　　
  Shinichi Maeda; Tetsuro Obara, [Contributor], Experimental Demonstration on High-Speed Gas Gun Driven by a Gaseous Detonation, pp.147-159
  Springer, 2022
  Total pages：242
  ISBN：3030907341, ASIN：3030907341, EAN：9783030907341
• デトネーション現象　　　　　　　　　　　　　　　
  Lee, John H. S.; 笠原, 次郎; 前田, 慎市; 遠藤, 琢磨; 笠原, 裕子
  2018
  Japanese, Total pages：vii, 277p
  CiNii Books：http://ci.nii.ac.jp/ncid/BB25755490
  ISBN：9784873266978, CiNii Books ID：BB25755490

• 回転デトネーションエンジン内部現象の可視化観測を目的としたLinear detonation channel実験装置の構築　　　　　　　　　　　　　　　
  前田 慎市; 西村 聡真; 碇 健太; 関 陽子; 小原 哲郎; 丹野 英幸
  Jan. 2025, [Domestic conference]
  Japanese, Oral presentation
• 空気吸い込み式パルスデトネーションエンジンのシーケンス変更による性能への影響　　　　　　　　　　　　　　　
  松村 朋輝; 吹場 活佳; 荒木 堅斗; 平山 歩果; 川崎 央; 前田 慎市; 小林 弘明
  Jan. 2025, [Domestic conference]
  Japanese, Oral presentation
• 空気吸い込み式パルスデトネーションエンジンの作動周波数の性能への影響　　　　　　　　　　　　　　　
  平山 歩果; 吹場 活佳; 荒木 堅斗; 松村 朋輝; 小林 弘明; 前田 慎市; 川崎 央
  Jan. 2025, [Domestic conference]
  Japanese, Oral presentation
• 管軸近傍における小さな障害物が誘起するデトネーション再起爆　　　　　　　　　　　　　　　
  関 陽子; 前田 慎市; 小原 哲郎
  Nov. 2024, [Domestic conference]
  Japanese, Oral presentation
• 不燃性気体の噴射によるデトネーション・アレスターの試作および性能　　　　　　　　　　　　　　　
  高橋 哲也; 坂口 達磨; 宮一 栄斗; 関 陽子; 前田 慎市; 小原 哲郎
  Nov. 2024, [Domestic conference]
  Japanese, Poster presentation
• ブロッケージ比が小さい障害物の形状がデフラグレーション・デトネーション遷移現象に与える影響　　　　　　　　　　　　　　　
  渡邉 光毅; 新垣 裕大; 稲垣 直哉; 前田 慎市; 関 陽子; 小原 哲郎
  Nov. 2024, [Domestic conference]
  Japanese, Oral presentation
• Observation of Detonation Initiation by a Spherical Projectile Using The Soap Bubble Filled with a Combustible Mixture　　　　　　　　　　　　　　　
  Ryoto Sato; Ken Suzuki; Shinichi Maeda; Tetsuro Obara
  The 8th International Symposium on Energetic Materials and their Applications (ISEM2024), Nov. 2024, [International conference]
  English, Oral presentation
• Deflagration-to-Detonation transition process caused by interaction between shock wave and flame　　　　　　　　　　　　　　　
  Genta Matsumoto; Mitsuru Iwashita; Yoko Seki; Shinichi Maeda; Tetsuro Obara; Yusuke Ryu; Nobuyuki Tsuboi
  The 8th International Symposium on Energetic Materials and their Applications (ISEM2024), Nov. 2024, [International conference]
  English, Oral presentation
• 空気吸い込み式パルスデトネーションエンジンを用いた姿勢制御　　　　　　　　　　　　　　　
  荒木 堅斗; 吹場 活佳; 平山 歩果; 松村 朋輝; 前田 慎市; 川崎 央; 小林 弘明
  Nov. 2024, [Domestic conference]
  Japanese, Oral presentation
• 準バルブレス・パルスデトネーション燃焼器における既燃ガス逆流現象の可視化観測　　　　　　　　　　　　　　　
  青井 瑞樹; 田中 悠豊; 池田 北斗; 前田 慎市; 小原 哲郎
  Jul. 2024
  Japanese, Oral presentation
• 姿勢制御用スラスタへの応用を目指した準バルブレス水素・空気パルスデトネーションスラスタの推力計測実験　　　　　　　　　　　　　　　
  田中 悠豊; 青井 瑞樹; 関口 長愛; 池田 北斗; 前田 慎市; 小原 哲郎
  Mar. 2024
  Japanese, Oral presentation
• 気体デトネーションを用いた爆風生成装置の形状が爆風特性に与える影響の評価　　　　　　　　　　　　　　　
  亀山 隼杜; 新垣 裕大; 前田 慎市; 小原 哲郎
  Mar. 2024
  Japanese, Oral presentation
• 単一障害物を有する流路におけるデトネーション遷移過程に関する実験および数値シミュレーション　　　　　　　　　　　　　　　
  井上 悠; 大豆生田 駿; 松本 颯斗; 前田 慎市; 中森 一郎; 小原 哲郎
  Mar. 2024
  Japanese, Oral presentation
• 液体推進剤回転デトネーションロケットエンジンの内部現象可視化を目指した Linear Detonation Channel 実験装置の検討　　　　　　　　　　　　　　　
  西村 聡真; 會澤 宗一郎; 前田 慎市; 小原哲郎; 丹野 英幸
  Mar. 2024
  Japanese, Poster presentation
• 大気アシスト姿勢制御用スラスタへの応用を目指した準バルブレス水素・空気パルスデトネーションエンジンの推力計測実験　　　　　　　　　　　　　　　
  前田 慎市
  Jan. 2024
  Japanese, Oral presentation
• 姿勢制御用曲がり管パルスデトネーションエンジンの推力測定　　　　　　　　　　　　　　　
  荒木 堅斗; 吹場 活佳; 川崎 央; 前田 慎市; 中田 大将; 奥村 政基; 松村 朋輝; 丸 祐介
  Jan. 2024
  Japanese, Oral presentation
• 空気吸込み式パルスデトネーションエンジンの自立運転に向けた性能・成立性検討　　　　　　　　　　　　　　　
  奥村 政基; 吹場 活佳; 前田 慎市; 川崎 央; 中田 大将; 荒木 堅斗; 松村 朋輝
  Jan. 2024
  Japanese, Oral presentation
• 異なる壁面粗さ要素を有する障害物がデフラグレーション・デトネーション遷移現象に与える影響　　　　　　　　　　　　　　　
  渡邉 光毅; 前田 慎市; 小原 哲郎
  Nov. 2023
  Japanese, Oral presentation
• Visualization of Detonation Initiation by a Spherical Projectile Launched into The Soap Bubble Filled with a Combustible Mixture　　　　　　　　　　　　　　　
  Shinichi Maeda; Naoki Hanyu; Yuichi Hiraoka; Ryoto Sato; Keisuke Nomura; Tetsuro Obara
  29th International Colloquium on the Dynamics of Explosions and Reactive Systems (ICDERS 2023), Jul. 2023
  English, Oral presentation
• 水素・空気パルスデトネーション燃焼器の空冷による長時間作動　　　　　　　　　　　　　　　
  田中 悠豊; 林 晃佑; 関口 長愛; 小久保 颯人; 青井 瑞樹; 前田 慎市; 小原 哲郎
  Jul. 2023
  Japanese, Oral presentation
• 空気吸い込み式PDEの自立運転に向けた成立性検討　　　　　　　　　　　　　　　
  奥村 政基; 吹場 活佳; 前田 慎市; 川崎 央
  Jul. 2023
  Japanese, Oral presentation
• Experiments on hydrogen-air pulse detonation combustor with air-cooling for more than 1 minute operation　　　　　　　　　　　　　　　
  Haruto Tanaka; Kosuke Hayashi; Nagachika Sekiguchi; Hayato Kokubo; Shinichi Maeda; Tetsuro Obara
  The 11th Asian Joint Conference on Propulsion and Power (AJCPP 2023), Mar. 2023
  English, Oral presentation
• 凸状火炎と垂直衝撃波の干渉によるデトネーション遷移過程の可視化観察　　　　　　　　　　　　　　　
  山本 直希; 顧 楷文; 小原 哲郎; 前田 慎市
  Mar. 2023
  Japanese, Oral presentation
• 気体デトネーションを用いた平面状爆風波生成装置の構築　　　　　　　　　　　　　　　
  竹原 智輝; 亀山 隼杜; 前田 慎市; 小原 哲郎
  Mar. 2023
  Japanese, Oral presentation
• シャボン玉内の高速飛行体により誘起されるデトネーション起爆現象の可視化観測　　　　　　　　　　　　　　　
  羽生 直樹; 平岡 祐一; 佐藤 亮斗; 野村 圭佑; 前田 慎市; 小原 哲郎
  Mar. 2023
  Japanese, Oral presentation
• パルスデトネーションエンジンの新観測ロケットへの応用　　　　　　　　　　　　　　　
  吹場 活佳; 川﨑 央; 前田 慎市
  Jan. 2023
  Japanese, Oral presentation
• パルスデトネーション燃焼器の熱負荷の解明に向けた研究　　　　　　　　　　　　　　　
  前田 慎市
  Jan. 2023
  Japanese, Oral presentation
• 壁面粗さ要素の違いが管内の火炎加速とデトネーション遷移に与える影響　　　　　　　　　　　　　　　
  種市 大輝; 渡邉 光毅; 前田 慎市; 小原 哲郎
  Nov. 2022
  Japanese, Oral presentation
• 単一障害物を有する管内におけるデトネーション遷移過程の実験ならびに数値シミュレーション　　　　　　　　　　　　　　　
  大豆生田; 駿; 松本 弦太; 前田 慎市; 中森 一郎; 小原 哲郎
  Nov. 2022
  Japanese, Oral presentation
• Flame acceleration process and detonation transition in a channel with roughness elements on a wall　　　　　　　　　　　　　　　
  Shinichi Maeda; Masahiro Irokawa; Daiki Taneichi; Tetsuro Obara
  The 39th International Symposium on Combustion, Jul. 2022
  English, Oral presentation
• 空冷機構を有する水素・空気パルスデトネーション燃焼器の長時間作動に向けた検討　　　　　　　　　　　　　　　
  田中 悠豊; 林 晃佑; 関口 長愛; 小久保 颯人; 前田 慎市; 小原 哲郎
  Jun. 2022
  Japanese, Oral presentation
• シャボン玉内に充填した可燃性混合気中へ射出した極超音速飛行体周りに誘起されるデトネーション起爆現象の可視化観測　　　　　　　　　　　　　　　
  前田 慎市; 羽生 直樹; 平岡 祐一; 小原 哲郎
  Jun. 2022
  Japanese, Oral presentation
• Visualization of Deflagration-to-detonation Transition in a Channel with Rough Wall　　　　　　　　　　　　　　　
  Shinichi Maeda; Masahiro Irokawa; Daiki Taneichi; Tetsuro Obara
  28th International Colloquium on the Dynamics of Explosions and Reactive Systems (ICDERS 2022), Jun. 2022
  English, Oral presentation
• 凸状火炎と衝撃波の干渉によるデトネーション遷移過程の可視化実験　　　　　　　　　　　　　　　
  江田 健汰; 山本 直希; 前田 慎市; 小原 哲郎
  Mar. 2022
  Mar. 2022 - Mar. 2022, Japanese, Oral presentation
• 同軸熱電対を用いたパルスデトネーション燃焼器の内壁面温度計測に向けた検討　　　　　　　　　　　　　　　
  前田 慎市; 林 晃佑; 関口 長愛; 田中 悠豊; 小原 哲郎; 丹野 英幸
  Mar. 2022
  Mar. 2022 - Mar. 2022, Japanese, Oral presentation
• 同軸熱電対を用いたデトネーション波の伝播による管内壁面温度変化の計測　　　　　　　　　　　　　　　
  林 晃佑; 田中 悠豊; 関口 長愛; 小久保 颯人; 前田 慎市; 小原 哲郎; 丹野 英幸
  Mar. 2022
  Japanese, Oral presentation
• Experimental and Numerical Study on Disc-RDE: Relation between Number of Detonation Wave and Pressure　　　　　　　　　　　　　　　
  A. Koichi Hayashi; Kodai Shimomura; Nobuyuki Tsuboi; Kohei Ozawa; Nicolas H. Jourdaine; Kazuhiro Ishii; Edyta Dzieminska; Tetsuro Obara; Shinichi Maeda; Toshiharu Mizukaki
  AIAA SciTech 2022 Forum, San Diego, CA & Virtual event, Jan. 2022
  Jan. 2022 - Jan. 2022, English, Oral presentation
• 粗い壁面を有する管内におけるエチレン・酸素混合気中のデフラグレーション・デトネーション遷移過程の化学発光計測　　　　　　　　　　　　　　　
  色川 正弘; 種市 大輝; 前田 慎市; 小原 哲郎
  Nov. 2021
  Nov. 2021 - Nov. 2021, Japanese, Oral presentation
• 単一障害物を有する流路におけるデトネーション遷移に関する実験　　　　　　　　　　　　　　　
  梶原 健吾; 大豆生田 駿; 前田 慎市; 小原 哲郎
  Nov. 2021
  Nov. 2021 - Nov. 2021, Japanese, Oral presentation
• Generation of planar blast waves using a gaseous detonation-driven blast simulator　　　　　　　　　　　　　　　
  Tomoki Takehara; Hayato Kameyama; Shinichi Maeda; Tetsuro Obara
  The 7th International Symposium on Energetic Materials and their Applications (ISEM2021), Virtual Symposium, Nov. 2021
  Nov. 2021 - Nov. 2021, English, Oral presentation
• Experimental study on deflagration‐to‐detonation transition in a channel with densely‐arranged roughness elements on the wall　　　　　　　　　　　　　　　
  Shinichi Maeda; Masahiro Irokawa; Daiki Taneichi; Tetsuro Obara
  The 7th International Symposium on Energetic Materials and their Applications (ISEM2021), Virtual Symposium, Nov. 2021
  Nov. 2021 - Nov. 2021, English, Oral presentation
• 3D numerical study on flow field in disc-RDE　　　　　　　　　　　　　　　
  A. Koichi Hayashi; Kodai Shimomura; Nobuyuki Tsuboi; Kohei Ozawa; Nicolas H. Jourdaine; Kazuhiro Ishii; Edyta Dzieminska; Tetsuro Obara; Shinichi Maeda; Toshiharu Mizukaki
  AIAA Propulsion and Energy 2021 Forum, Virtual event, Aug. 2021
  Aug. 2021 - Aug. 2021, English, Oral presentation
• 空冷機構を有する水素・空気パルスデトネーション燃焼器の作動実験　　　　　　　　　　　　　　　
  林 晃佑; 小池 匠; 田中 悠豊; 前田 慎市; 小原 哲郎
  Jun. 2021
  Jun. 2021 - Jul. 2021, Japanese, Oral presentation
• デトネーション管の内径が気体デトネーション駆動高速ガス銃の飛行体射出速度に与える影響　　　　　　　　　　　　　　　
  前田 慎市; 平岡 祐一; 渡邉 一樹; 羽生 直樹; 小原 哲郎
  Jun. 2021
  Jun. 2021 - Jul. 2021, Japanese, Oral presentation
• 回折したデトネーション波再開始距離の定量的評価（圧力変換器の自作）　　　　　　　　　　　　　　　
  久保 隼人; 西川 雄一郎; 前田 慎市; 小原 哲郎
  Mar. 2021
  Mar. 2021 - Mar. 2021, Japanese, Oral presentation
• 気体デトネーションを用いた平面状爆風波の生成装置における爆風特性に関する基礎実験　　　　　　　　　　　　　　　
  小宮 淳嗣; 竹原 智輝; 前田 慎市; 小原 哲郎
  Mar. 2021
  Mar. 2021 - Mar. 2021, Japanese, Oral presentation
• Experimental and Numerical Study on Disc-RDE: Flow Structure and its Performances　　　　　　　　　　　　　　　
  A. Koichi Hayashi; Kazuhiro Ishii; Tomohiro Watanabe; Nobuyuki Tsuboi; Kohei Ozawa; Nicola H. Jourdaine; Edyta Dzieminska; Xinmeng Tang; Tetsuro Obara; Shinichi Maeda; Toshiharu Mizukaki
  2021 AIAA SciTech Forum (Virtual event), Jan. 2021
  English, Oral presentation
• 単一障害物を有する流路上における高反応性気体のデトネーション遷移過程　　　　　　　　　　　　　　　
  須田 優駿; 梶原 健吾; 加藤 由真; 前田 慎市; 小原 哲郎
  Dec. 2020
  Dec. 2020 - Dec. 2020, Japanese, Oral presentation
• 壁面上に微小な障害物が密に配置された管内における火炎加速過程の実験的調査　　　　　　　　　　　　　　　
  前田 慎市; 色川 正弘; 種市 大輝; 小原 哲郎
  Dec. 2020
  Dec. 2020 - Dec. 2020, Japanese, Oral presentation
• パルスデトネーション燃焼器の壁面温度の計測実験　　　　　　　　　　　　　　　
  小池 匠; 小杉 賢史; 林 晃祐; 前田 慎市; 小原 哲郎
  Sep. 2020
  Sep. 2020 - Sep. 2020, Japanese, Oral presentation
• 水素濃度勾配を有する可燃性混合気中を極超音速飛行する球体周りに形成される斜めデトネーション波の起爆・安定化に関する実験研究　　　　　　　　　　　　　　　
  渡邉 一樹; 原子内 滉也; 岩田 和也; 前田 慎市; 小原 哲郎
  Sep. 2020
  Sep. 2020 - Sep. 2020, Japanese, Oral presentation
• 気体デトネーションを用いた爆風生成装置の構築に向けた基礎実験　　　　　　　　　　　　　　　
  小宮 淳嗣; 津田 勇樹; 前田 慎市; 小原 哲郎
  May 2020
  May 2020 - May 2020, Japanese, Oral presentation
• 障害物上におけるデトネーション遷移に関する可視化観察（障害物形状の影響）　　　　　　　　　　　　　　　
  岡田 隆太; 須田 優駿; 加藤 由真; MUHAMMAD IZZUDDIN BIN ASH'ARI; 前田 慎市; 小原 哲郎
  Mar. 2020
  Japanese, Oral presentation
• 水素濃度勾配を有する可燃性混合気中における極超音速飛行体による斜めデトネーション波の起爆・安定化に関する実験研究　　　　　　　　　　　　　　　
  原子内 滉也; 渡邉 一樹; 西本 光佑; 森 健吾; 岩田 和也; 前田 慎市; 小原 哲郎
  Mar. 2020
  Japanese, Oral presentation
• PZT 素子を用いた圧力センサーの自作と性能評価　　　　　　　　　　　　　　　
  五十嵐 一樹; 久保 隼人; 前田 慎市; 小原 哲郎
  Mar. 2020
  Japanese, Oral presentation
• Disc型回転デトネーションエンジン(D-RDE)の研究　　　　　　　　　　　　　　　
  林 光一; 坪井 伸幸; 小澤 晃平; 石井 一洋; 小原 哲郎; 前田 慎市; ジェミンスカ エディータ; 水書 俊治
  Nov. 2019, [Domestic conference]
  Oral presentation
• 壁面上に微小な障害物を密に配置した管内における火炎加速とデトネーション遷移過程　　　　　　　　　　　　　　　
  平原 佳祐; 色川 正弘; 前田 慎市; 小原 哲郎
  Nov. 2019, [Domestic conference]
  Oral presentation
• 連続した障害物を有する流路におけるデトネーション遷移過程の数値シミュレーション　　　　　　　　　　　　　　　
  加藤 由真; 岡田 隆太; 須田 優駿; 小原 哲郎; 前田 慎市; 中森 一郎; 桐原 亮平
  Nov. 2019, [Domestic conference]
  Oral presentation
• A Study on Operating Conditions of Disk-Type Rotating Detonation Engine　　　　　　　　　　　　　　　
  Haruhiro Kawana; Wataru Kurata; Kanta Ohno; Kazuhiro Ishii; A. Koichi Hayashi; Nobuyuki Tsuboi; Kohei Ozawa; Tetsuro Obara; Shinichi Maeda; Edyta Dzieminska; Toshiharu Mizukaki
  Aug. 2019, [International conference]
  Oral presentation
• 直管形状のデトネーション駆動型爆風生成装置における駆動部長さが平面状爆風波の最大過剰圧に与える影響　　　　　　　　　　　　　　　
  津田 勇希; 小宮 淳嗣; 前田 慎市; 小原 哲郎
  Jul. 2019, [Domestic conference]
  Oral presentation
• 低圧縮空気源を用いた準バルブレス・パルスデトネーション燃焼器の作動実験　　　　　　　　　　　　　　　
  室井 優太; 小池 匠; 木村 朔; 前田 慎市; 小原 哲郎
  Mar. 2019, [Domestic conference]
  Oral presentation
• ディスク型燃焼器を用いた回転デトネーションエンジンに関する研究　　　　　　　　　　　　　　　
  川名 陽大; 倉田 航; 大野 寛太; 石井 一洋; 林 光一; 坪井 伸幸; ジェミンスカ・エディータ; 小原 哲郎; 水書 稔治; 前田 慎市; 小澤 晃
  Mar. 2019, [Domestic conference]
  Oral presentation
• 自作圧力センサーを用いたオーバードリブンデトネーション開始距離の評価　　　　　　　　　　　　　　　
  五十嵐 一樹; 渡辺 聡人; 前田 慎市; 小原 哲郎
  Mar. 2019, [Domestic conference]
  Oral presentation
• 5cm×5cmデトネーション駆動型爆風模擬装置測定部における流れ場の評価　　　　　　　　　　　　　　　
  加藤 明里; 森 美里; 岩崎 文彦; 沼田 大樹; 前田 慎市; 小原 哲郎; 水書 稔治
  Mar. 2019, [Domestic conference]
  Oral presentation
• 5cm×5cmデトネーション駆動型爆風模擬装置測定部における流れ場の可視化　　　　　　　　　　　　　　　
  岩崎 文彦; 加藤 明里; 森 美里; 前田 慎市; 小原 哲郎; 水書 稔治
  Mar. 2019, [Domestic conference]
  Poster presentation
• 平面衝撃波と干渉した火炎のデトネーション遷移過程　　　　　　　　　　　　　　　
  小野 涼; 篠崎 拓也; 小原 哲郎; 前田 慎市
  Mar. 2019, [Domestic conference]
  Oral presentation
• Development of a High Efficiency System with a Rotating Detonation Engine for a Gas Turbine Engine (RDE-GTE) using Pressure Gain Combustion　　　　　　　　　　　　　　　
  A. Koichi Hayashi; Nobuyuki Tsuboi; Kohei Ozawa; Kazuhiro Ishii; Tetsuro Obara; Shinichi Maeda; Edyta Dzieminska; Toshiharu Mizukaki
  Jan. 2019, [International conference]
  Oral presentation
• 障害物が流路壁面上に密に配置された場合の火炎加速とデトネーション遷移　　　　　　　　　　　　　　　
  家永 翔伍; 平原 佳祐; 秋元 皓志; 前田 慎市; 小原 哲郎
  Nov. 2018, [Domestic conference]
  Oral presentation
• RDEを用いたガスタービンエンジン開発に向けての研究　　　　　　　　　　　　　　　
  林 光一; 坪井 伸幸; 石井 一洋; ジェミンスカ エディータ; 小原 哲郎; 水書 稔治; 前田 慎市; 小澤 晃平
  Nov. 2018, [Domestic conference]
  Oral presentation
• Effect of sandpaper-like small wall roughness on deflagration-to-detonation transition in a hydrogen-oxygen mixture　　　　　　　　　　　　　　　
  Shinichi Maeda; Masashi Fujisawa; Shogo Ienaga; Keisuke Hirahara; Tetsuro Obara
  Jul. 2018, [International conference]
  Oral presentation
• 障害物を有する管内へのフレームジェット噴射によるデトネーション遷移過程　　　　　　　　　　　　　　　
  緒方 隆次; 前田 慎市; 小原 哲郎
  Jul. 2018, [Domestic conference]
  Oral presentation
• 炭化水素予混合気中における衝撃波/火炎干渉に関する二次元数値解析：燃料の違いの影響　　　　　　　　　　　　　　　
  坪井 伸幸; 岩井 麻衣子; 森井 雄飛; 小澤 晃平; 林 光一; 小原 哲郎; 前田 慎市
  Jul. 2018, [Domestic conference]
  Oral presentation
• 気体デトネーション駆動高速ガス銃を用いた高速飛行体周りの衝撃波誘起燃焼に関する研究　　　　　　　　　　　　　　　
  前田 慎市
  May 2018, [Invited], [Domestic conference]
  Invited oral presentation
• デトネーション駆動型爆風シミュレータ製作に向けた基礎検討　　　　　　　　　　　　　　　
  加藤 明里; 森 美里; 前田 慎市; 小原 哲郎; 水書 稔治
  Mar. 2018, [Domestic conference]
  Oral presentation
• 管内の気体爆発で起爆した平面状爆風波の圧力波形に関する研究　　　　　　　　　　　　　　　
  星野 隆介; 津田 勇希; 前田 慎市; 小原 哲郎
  Mar. 2018, [Domestic conference]
  Oral presentation
• 高速ガス銃の駆動源への気体デトネーション応用　　　　　　　　　　　　　　　
  前田 慎市; 冨田 啓太; 原子内 滉也; 小原 哲郎
  Mar. 2018, [Domestic conference]
  Oral presentation
• 縦型衝撃波管における微粒子拡散計測　　　　　　　　　　　　　　　
  森 美里; 加藤 明里; 前田 慎市; 小原 哲郎; 水書 稔治
  Mar. 2018, [Domestic conference]
  Poster presentation
• 流路壁面粗さが火炎加速とデトネーション遷移に与える影響　　　　　　　　　　　　　　　
  藤澤 昌志; 家永 翔伍; 平原 佳祐; 前田 慎市; 小原 哲郎
  Nov. 2017, [Domestic conference]
  Oral presentation
• デトネーション・アレスターの開発を目指した基礎実験　　　　　　　　　　　　　　　
  春山 晃寿; 上田 翔太; 前田 慎市; 小原 哲郎
  Nov. 2017, [Domestic conference]
  Oral presentation
• Effect of surface roughness of a channel wall on flame propagation and detonation transition in a fuel-oxygen mixture　　　　　　　　　　　　　　　
  Shinichi Maeda; Masashi Fujisawa; Shogo Ienaga; Keisuke Hirahara; Tetsuro Obara
  Nov. 2017, [International conference]
  Oral presentation
• Numerical Analysis on Shock Flame Interaction in Hydrocarbon/Oxygen Premixed Gas -Difference in the Propagation Types-　　　　　　　　　　　　　　　
  Maiko Iwai; Keisuke Yoshida; Youhi Morii; Nobuyuki Tsuboi; A. Koichi Hayashi; Tetsuro Obara; Shinichi Maeda
  Nov. 2017, [International conference]
  Oral presentation
• 水素濃度勾配中の球状発射体まわりに形成される自己保持斜めデトネーション　　　　　　　　　　　　　　　
  岩田 和也; 中谷 辰爾; 津江 光洋; 冨田 啓太; 吉木 一秀; 前田 慎市; 小原 哲郎
  Jun. 2017, [Domestic conference]
  Oral presentation
• 可燃性混合気中の超音速飛行体により誘起される振動燃焼の発生条件　　　　　　　　　　　　　　　
  冨田 啓太; 吉木 一秀; 菅野 祥一郎; 前田 慎市; 小原 哲郎
  Jun. 2017, [Domestic conference]
  Oral presentation
• 気体デトネーション波を開始源とする平面状爆風波の特性　　　　　　　　　　　　　　　
  前田 慎市; 星野 隆介; 大塚 一樹; 及川 陽介; 小原 哲郎
  May 2017, [Domestic conference]
  Oral presentation
• 火星大気を用いた金属燃料のデトネーション特性　　　　　　　　　　　　　　　
  加藤 明里; 前田 慎市; 小原 哲郎; 水書 稔治
  Mar. 2017, [Domestic conference]
  Poster presentation
• 衝撃波と火炎の干渉によるデトネーション遷移過程　　　　　　　　　　　　　　　
  倉持 悠希; 小野 涼; 前田 慎市; 小原 哲郎
  Mar. 2017, [Domestic conference]
  Oral presentation
• 反応性の高い予混合気体中におけるデフラグレーション−デトネーション遷移過程の可視化観測　　　　　　　　　　　　　　　
  藤澤 昌志; 家永 翔伍; 前田 慎市; 小原 哲郎
  Nov. 2016, [Domestic conference]
  Oral presentation
• 副室からのフレームジェットによるデトネーション開始過程　　　　　　　　　　　　　　　
  吉田 将敬; 緒方 隆次; 前田 慎市; 小原 哲郎
  Nov. 2016, [Domestic conference]
  Oral presentation
• 可燃性予混合気の規則性が球形飛行体周りの衝撃波誘起燃焼に与える影響　　　　　　　　　　　　　　　
  吉木 一秀; 菅野 祥一郎; 前田 慎市; 小原 哲郎
  Jul. 2016, [Domestic conference]
  Oral presentation
• デトネーション波と壁面の正面衝突により生成される衝撃波に関する研究　　　　　　　　　　　　　　　
  及川 陽介; 星野 隆介; 前田 慎市; 小原 哲郎
  Mar. 2016, [Domestic conference]
  Oral presentation
• 高速飛行体周りに誘起される燃焼現象の時系列可視化観測　　　　　　　　　　　　　　　
  前田 慎市; 菅野 祥一郎; 吉木 一秀; 小原 哲郎
  Nov. 2015, [Domestic conference]
  Oral presentation
• 衝撃波と火炎の干渉によるデトネーション遷移に関する可視化観察　　　　　　　　　　　　　　　
  藤井 貴文; 倉持 悠希; 小原 哲郎; 前田 慎市; 坪井 伸幸
  Nov. 2015, [Domestic conference]
  Oral presentation
• DDTにおける初期火炎形成と火炎成長に伴う火炎加速　　　　　　　　　　　　　　　
  長谷川 徒来; 朝原 誠; 八木 翔平; 前田 慎市; 坪井 伸幸
  Nov. 2015, [Domestic conference]
  Oral presentation
• Visualization of deflagration-to-detonation transitions in a channel with repeated obstacles　　　　　　　　　　　　　　　
  Shinichi Maeda; Shohei Minami; Daisuke Okamoto; Tetsuro Obara
  Aug. 2015, [International conference]
  Oral presentation
• 連続した障害物上を伝播するデトネーション波の挙動　　　　　　　　　　　　　　　
  Muhamad Bin Kamaruzaman; 前田 慎市; 小原 哲郎
  Jul. 2015, [Domestic conference]
  Oral presentation
• 気体デトネーション駆動型ガス銃における軽ガスを用いた射出性能の向上に関する研究　　　　　　　　　　　　　　　
  菅野 祥一郎; 吉木 一秀; 前田 慎市; 小原 哲郎
  Mar. 2015, [Domestic conference]
  Oral presentation
• 濃度勾配を有する予混合気中を伝播するデトネーション波の挙動　　　　　　　　　　　　　　　
  寺岡 拓海; 及川 陽介; 前田 慎市; 蔭山 健介; 小原 哲郎
  Mar. 2015, [Domestic conference]
  Oral presentation
• 副室から噴射されたフレームジェットによるデトネーション開始過程　　　　　　　　　　　　　　　
  青島 亮太; 黒澤 哲朗; 前田 慎市; 小原 哲郎
  Mar. 2015, [Domestic conference]
  Oral presentation
• エチレン／空気均一予混合気中における衝撃波／火炎干渉の数値解析−爆轟遷移過程と火炎半径の影響−　　　　　　　　　　　　　　　
  荒木 孝行; 森井 雄飛; 坪井 伸幸; 林 光一; 小原 哲郎; 前田 慎市
  Dec. 2014, [Domestic conference]
  Oral presentation
• 六フッ化硫黄で希釈した可燃性予混合気体中を伝播するデトネーション波の実験研究　　　　　　　　　　　　　　　
  古藤 亮平; 佐藤 拓; 前田 慎市; 小原 哲郎
  Dec. 2014, [Domestic conference]
  Oral presentation
• 連続した障害物を有する流路におけるデトネーション遷移過程　　　　　　　　　　　　　　　
  南 翔平; 岡本 大祐; 前田 慎市; 小原 哲郎
  Dec. 2014, [Domestic conference]
  Oral presentation
• Experimental study on an acceleration of a projectile using a gaseous detonation　　　　　　　　　　　　　　　
  Shinichi Maeda; Shoichiro Kanno; Isshu Yoshiki; Tetsuro Obara
  Nov. 2014, [International conference]
  Oral presentation
• 無圧縮機型パルスデトネーションタービンエンジンの熱効率解析（Analysis on Thermal Efficiency of Non-Compressor Type Pulse Detonation Turbine Engines）　　　　　　　　　　　　　　　
  前田 慎市
  Apr. 2014, [Invited], [Domestic conference]
  Invited oral presentation
• 副室からの噴射によるデトネーション開始過程　　　　　　　　　　　　　　　
  青島 亮太; 市川 昌紀; 前田 慎市; 小原 哲郎
  Mar. 2014, [Domestic conference]
  Oral presentation
• 予混合気体への衝撃波入射による着火およびデトネーション遷移過程　　　　　　　　　　　　　　　
  永田 龍之輔; 吉本 和貴; 前田 慎市; 小原 哲郎
  Mar. 2014, [Domestic conference]
  Oral presentation
• 気体デトネーション駆動型ガス銃の射出性能の計測実験　　　　　　　　　　　　　　　
  前田 慎市; 菅野 祥一郎; 古藤 亮平; 小原 哲郎
  Mar. 2014, [Domestic conference]
  Oral presentation
• Reflection phenomena of oblique detonation wave around hypersonic spherical projectiles on plane plate　　　　　　　　　　　　　　　
  Satoshi Sumiya; Shinichi Maeda; Jiro Kasahara; Akiko Matsuo
  Jan. 2014, [Domestic conference]
  Oral presentation
• 凹凸壁を有するデトネーションアレスター装置による消炎過程　　　　　　　　　　　　　　　
  堀内智大; 渡邊清峻; 前田慎市; 小原哲郎
  Dec. 2013, [Domestic conference]
  Oral presentation
• Scale Effect of Spherical Projectiles for Stabilization of Oblique Detonation Waves　　　　　　　　　　　　　　　
  Shinichi Maeda; Satoshi Sumiya; Jiro Kasahara; Akiko Matsuo
  Aug. 2013, [International conference]
  Oral presentation
• 超音速球体周りに形成される振動燃焼の高時間分解能可視化観測　　　　　　　　　　　　　　　
  前田慎市; 住谷早俊; 笠原次郎; 松尾亜紀子
  Mar. 2013, [Domestic conference]
  Oral presentation
• Study on Detonation Wave Attenuation through Narrow Tube for Application to Explosion Safety and Detonation Engines　　　　　　　　　　　　　　　
  Tomoki Uruno; Shinichi Maeda; Jiro Kasahara; Akiko Matsuo
  Jan. 2013, [International conference]
  Oral presentation
• 極超音速飛行する球形飛行体直径が斜めデトネーション波安定化に与える影響　　　　　　　　　　　　　　　
  前田慎市; 住谷早俊; 笠原次郎; 松尾亜紀子
  Dec. 2012, [Domestic conference]
  Oral presentation
• Initiation and Sustaining Mechanisms of Stabilized Oblique Detonation Waves around Projectiles　　　　　　　　　　　　　　　
  Shinichi Maeda; Satoshi Sumiya; Jiro Kasahara; Akiko Matsuo
  Aug. 2012, [International conference]
  Oral presentation
• 対飛行方向45度可視化による斜めデトネーション波の軸対称性直接観測　　　　　　　　　　　　　　　
  住谷早俊; 前田慎市; 笠原次郎; 松尾亜紀子
  Mar. 2012, [Domestic conference]
  Oral presentation
• Visualization of the Initiation and Stabilization Process of an Oblique Detonation Wave around a Projectile　　　　　　　　　　　　　　　
  Shinichi Maeda; Jiro Kasahara; Akiko Matsuo
  Jul. 2011, [International conference]
  Oral presentation
• Drag Coefficients of Hypervelocity Spherical Projectile Initiating Oblique Detonation Wave　　　　　　　　　　　　　　　
  Jeong-Yeol Choi; Shinichi Maeda; Jiro Kasahara; Akiko Matsuo
  Jul. 2011, [International conference]
  Poster presentation
• 多孔物質中を伝播するデトネーション波の減衰に関する研究　　　　　　　　　　　　　　　
  宇留野智紀; 前田慎市; 笠原次郎; 松尾亜紀子
  Jul. 2011, [Domestic conference]
  Oral presentation
• Unsteady Propagation Process of Oblique Detonation Waves Initiated by Hypersonic Spherical Projectiles　　　　　　　　　　　　　　　
  Shinichi Maeda; Jiro Kasahara; Akiko Matsuo
  Jun. 2011, [International conference]
  Oral presentation
• 間隙壁面中へ回折するデトネーション波の維持・減衰機構の解明　　　　　　　　　　　　　　　
  山本憲吾; 前田慎市; 笠原次郎; 松尾亜紀子
  Mar. 2011, [Domestic conference]
  Oral presentation
• 曲がり細管内を伝播するデトネーション波に関する研究　　　　　　　　　　　　　　　
  稲田龍一; 前田慎市; 笠原次郎; 松尾亜紀子
  Mar. 2011, [Domestic conference]
  Oral presentation
• デトネーション波利用推進エンジンの基礎・応用研究　　　　　　　　　　　　　　　
  笠原次郎; 前田慎市; 松岡健
  Jan. 2011, [Domestic conference]
  Oral presentation
• The Stabilized Oblique Detonation Wave and Unsteady Wave Structure Around Hyper-velocity Spherical Projectile　　　　　　　　　　　　　　　
  Shinichi Maeda; Ryuichi Inada; Jiro Kasahara; Akiko Matsuo; Ikko Funaki
  Jan. 2011, [International conference]
  Oral presentation
• 極超音速飛行体周りに形成される斜めデトネーション波の非定常現象　　　　　　　　　　　　　　　
  前田慎市; 稲田龍一; 笠原次郎; 松尾亜紀子
  Dec. 2010, [Domestic conference]
  Oral presentation
• Detonation Wave Diffraction in the Vicinity of Corners　　　　　　　　　　　　　　　
  Yuuto Nagura; Shinichi Maeda; Yusuke Kudo; Jiro Kasahara; Akiko Matsuo
  Sep. 2010, [International conference]
  Oral presentation
• Visualization of the Non-Steady State Oblique Detonation Wave Phenomena around Hypersonic Spherical Projectile　　　　　　　　　　　　　　　
  Shinichi Maeda; Ryuichi Inada; Jiro Kasahara; Akiko Matsuo
  Aug. 2010, [International conference]
  Oral presentation
• 側壁に回折間隙壁面を有するデトネーションエンジンに関する研究　　　　　　　　　　　　　　　
  前田慎市; 山本憲吾; 笠原次郎; 伊藤政範; 松尾亜紀子
  Jun. 2010, [Domestic conference]
  Oral presentation
• 多数の分岐部を有する管内を伝播するデトネーションの数値解析　　　　　　　　　　　　　　　
  伊藤政範; 松尾亜紀子; 前田慎市; 山本憲吾; 笠原次郎
  Mar. 2010, [Domestic conference]
  Oral presentation
• 極超音速飛行体周りに生成される斜めデトネーション波の非定常伝播機構の可視化実験　　　　　　　　　　　　　　　
  前田慎市; 稲田龍一; 笠原次郎; 松尾亜紀子
  Mar. 2010, [Domestic conference]
  Oral presentation
• 回折間隙壁面に支持されるデトネーション波に関する研究　　　　　　　　　　　　　　　
  山本憲吾; 前田慎市; 笠原次郎; 伊藤政範; 松尾亜紀子
  Mar. 2010, [Domestic conference]
  Oral presentation
• 小型タービンを用いた場合のパルスデトネーションタービンエンジンの性能試験　　　　　　　　　　　　　　　
  前田慎市; 笠原次郎; 田中克己; 松尾亜紀子; 遠藤琢磨
  Sep. 2006, [Domestic conference]
  Oral presentation
• 二段タービンを用いた場合のパルスデトネーションタービンエンジンの性能試験　　　　　　　　　　　　　　　
  前田慎市; 笠原次郎; 田中克己; 松尾亜紀子; 遠藤琢磨
  Mar. 2006, [Domestic conference]
  Oral presentation
• 不活性気体駆動弾道振子を用いたPDE部分充填推力増大効果の研究　　　　　　　　　　　　　　　
  笠原次郎; J.E. Shepherd; 田中克己; S. Browne; 前田慎市
  Jan. 2006, [Domestic conference]
  Oral presentation
• 自動車用ターボチャージャーを用いたパルスデトネーションタービンエンジンの熱効率計測　　　　　　　　　　　　　　　
  前田慎市; 笠原次郎; 松尾亜紀子; 遠藤琢磨
  Mar. 2005, [Domestic conference]
  Oral presentation
• パルスデトネーションタービンエンジンに関する実験的研究　　　　　　　　　　　　　　　
  笠原次郎; 前田慎市
  Jan. 2005, [Domestic conference]
  Oral presentation

• The Japan Society of Mechanical Engineers
• Japan Explosives Society
• Gas Turbine Society of Japan
• The Japan Society for Aeronautical and Space Sciences
• Combustion Society of Japan

• Pressure gain combustion in a rotating detonation engine　　　　　　　　　　　　　　　
  Japan Society for the Promotion of Science, Grants-in-Aid for Scientific Research, Grant-in-Aid for Scientific Research (B), Apr. 2024 - Mar. 2027
  Yokohama National University, Coinvestigator
  Grant amount(Total)：18590000, Direct funding：14300000, Indirect funding：4290000
  Grant number：24K01077
• 渦巻き形の溝を用いたデトネーション・アレスター技術の確立と消炎メカニズムの解明　　　　　　　　　　　　　　　
  Apr. 2024 - Mar. 2027
  Coinvestigator
  Grant amount(Total)：4550000, Direct funding：3500000, Indirect funding：1050000
  Grant number：24K07337
• デトネーション管による液体燃料平面デトネーション波の伝播特性・燃焼特性の評価　　　　　　　　　　　　　　　
  Nov. 2024 - Mar. 2025
• マルチ・チャンバ型気体デトネーション駆動高速ガス銃：飛行体射出性能の飛躍的向上　　　　　　　　　　　　　　　
  Apr. 2022 - Mar. 2025
  Principal investigator
  Grant amount(Total)：4160000, Direct funding：3200000, Indirect funding：960000
  Grant number：22K03920
• 再使用型宇宙輸送システムにおける大気アシスト飛行の実証研究　　　　　　　　　　　　　　　
  Jun. 2024 - Feb. 2025
• デトネーション管による液体燃料平面デトネーション波の伝播特性・燃焼特性の評価　　　　　　　　　　　　　　　
  Nov. 2023 - Mar. 2024
• サブオービタル飛行を想定した宇宙往還機のエンジンに関する研究　　　　　　　　　　　　　　　
  Jun. 2023 - Mar. 2024
• Clarification of detonation transition mechanisms over obstacle (effects of obstacle position and height)　　　　　　　　　　　　　　　
  Japan Society for the Promotion of Science, Grants-in-Aid for Scientific Research, Grant-in-Aid for Scientific Research (C), Apr. 2021 - Mar. 2024
  Obara Tetsuro, Saitama University, Coinvestigator
  Grant amount(Total)：4160000, Direct funding：3200000, Indirect funding：960000
  A combustion wave propagating in combustible premixed gas is classified into a deflagration wave and detonation wave, and deflagration-to-detonation transition processes are experimentally investigated. Firstly, one obstacle is installed in a detonation tube and deflagration-to-detonation transition processes are visualized using schlieren optical method. Next, 28 pieces of multiple ion-probes are flush mounted on a bottom surface. It is clarified that the combustion wave propagating velocity on the bottom surface is almost same as Chapman-Jouguet detonation velocity.
  Grant number：21K03870
• 再使用型宇宙輸送システムにおける大気アシスト飛行の実証研究　　　　　　　　　　　　　　　
  Jul. 2023 - Feb. 2024
• 同軸熱電対の評価委託　　　　　　　　　　　　　　　
  Jan. 2022 - Mar. 2022
• 新たな手法として気体爆轟を用いた爆風シミュレータ：実現象再現度の飛躍的向上　　　　　　　　　　　　　　　
  Japan Society for the Promotion of Science, Grants-in-Aid for Scientific Research Grant-in-Aid for Early-Career Scientists, Grant-in-Aid for Early-Career Scientists, 01 Apr. 2018 - 31 Mar. 2021
  Saitama University
  Grant amount(Total)：4030000, Direct funding：3100000, Indirect funding：930000
  Grant number：18K13681
• デトネーションアレスター装置における消炎メカニズム　　　　　　　　　　　　　　　
  Apr. 2015 - Mar. 2021
• 回転デトネーションの伝播モードダイナミクス解明と燃焼器設計指針の確立　　　　　　　　　　　　　　　
  Japan Society for the Promotion of Science, Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (B), Grant-in-Aid for Scientific Research (B), 01 Apr. 2017 - 31 Mar. 2020
  Yokohama National University
  Grant amount(Total)：16380000, Direct funding：12600000, Indirect funding：3780000
  Grant number：17H03478
• 安全な水素エネルギー社会の実現に向けたハイブリッドデトネーションアレスターの開発　　　　　　　　　　　　　　　
  Japan Society for the Promotion of Science, Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (C), Grant-in-Aid for Scientific Research (C), 01 Apr. 2017 - 31 Mar. 2020
  Saitama University
  Grant amount(Total)：4810000, Direct funding：3700000, Indirect funding：1110000
  Grant number：17K06142
• Detonation combustor initiated by a high-speed projectile: experimental study on instantaneous combustion process for generating high-pressure burned gas　　　　　　　　　　　　　　　
  Japan Society for the Promotion of Science, Grants-in-Aid for Scientific Research Grant-in-Aid for Young Scientists (B), Grant-in-Aid for Young Scientists (B), 01 Apr. 2014 - 31 Mar. 2017
  MAEDA Shinichi, Saitama University, Principal investigator
  Grant amount(Total)：3900000, Direct funding：3000000, Indirect funding：900000
  The high-speed projectile was launched into the combustor in order to form the strong shock wave in the combustible mixture, and we experimentally demonstrated the initiation of combustion wave or detonation wave around the projectile. The high-speed gas gun, which was driven by detonation combustion, was constructed, and we obtained the projectile velocity of 1400 m/s or 2500 m/s in the single-stage or the two-stage gas gun, respectively. Several types of combustion mode were observed around the projectile launched into the combustor, and the two dimensionless-parameters were proposed in order to express the occurrence condition of each combustion mode. The experiment was also carried out under the gradient field of the fuel concentration. The detonation wave could be sustained around the projectile in the gradient field. The result indicated that the fuel concentration in the vicinity of the projectile was important factor for initiating the detonation.
  Competitive research funding, Grant number：26870096
• Elucidation of MHz-Class Detonation Engine Physics Mechanism: Valve Resonance and Rotating Detonation Type Engines　　　　　　　　　　　　　　　
  Japan Society for the Promotion of Science, Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (A), Grant-in-Aid for Scientific Research (A), 01 Apr. 2012 - 31 Mar. 2016
  Kasahara Jiro; Matsuo Akiko; Funaki Ikkoh; Nishioka Makihito; Sakakita Hajime; Maeda Shinichi; Matsuoka Ken
  Grant amount(Total)：46410000, Direct funding：35700000, Indirect funding：10710000
  In the present study, we elucidated performance of rotating detonation engines experimentally and numerically. We made models for predicting the stabilization condition in which detonation waves can propagate in the rotating detonation engines. We also elucidated the mechanism of detonation generation and quench. In the two flat disc shaped rotating detonation engine, we show the whole structure of the flow field including injection, mixing of fuel and oxidizer. We discovered a new detonation wave (forward tilting detonation wave) in this disc shaped engine. By the two-dimensional computational fluid dynamics analysis, we elucidated the effect of injector shapes and burned gases on detonation waves. We successfully performed the flight test of a pulse detonation engine and the sled test of a rotating detonation engine.
  Grant number：24246137
• デトネーション波を利用した点火プラグ評価　　　　　　　　　　　　　　　
  2015
• None　　　　　　　　　　　　　　　
  Japan Society for the Promotion of Science, Grants-in-Aid for Scientific Research Grant-in-Aid for JSPS Fellows, Grant-in-Aid for JSPS Fellows, Apr. 2011 - Mar. 2013
  University of Tsukuba, Principal investigator
  Grant amount(Total)：1400000, Direct funding：1400000
  Grant number：11J00852
• 49th AIAA Aerospace Sciences Meeting　　　　　　　　　　　　　　　
  Jan. 2011