Papers - Matsuo, Akiko

Numerical investigation of the interaction between a shock wave and a particle cloud curtain using a CFD-DEM model (accepted)

Sugiyama, Y., Ando, H., Shimura, K., and Matsuo, A.

Shock Waves 29 ( 4 ) 499 - 510 2019

Research paper (scientific journal), Joint Work, Accepted

• Access to Document (DOI)

The effect of acceleration and exit velocity on hypersonic projectiles launched by a ground-based railgun

Kasahara H., Matsuo A.

AIAA Scitech 2019 Forum (AIAA Scitech 2019 Forum)   2019

ISSN  9781624105784

　View Summary

© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. In this paper, the effects of projectile acceleration profile on interior and transition ballistics are investigated in order to design HVP (Hyper-Velocity projectile) for railgun. Our railgun facilities accelerate projectile to 600 – 2501 m/s in order to evaluate the effect of exit velocity on sabot separation. However, sabot melt prevents us from observing detail sabot separation and shock wave interactions. Thus, in this paper, CFD-RBD method is applied to calculate the projectile acceleration and sabot separation motion due to unsteady aerodynamic force. In the interior calculation, acceleration behavior is approximated by the cubic spline interpolation using our experimental result in Vexit = 658, 1268, 1875, 2048, 2501 m/s. Firstly, in the interior ballistic calculation, the projectile and sabot induce compression waves due to acceleration. In 0.6 ms, the single normal shock wave stands ahead of projectile. The precursor shock wave reaches the end of tube and propagates outside of tube. When the precursor shockwave propagates outside of tube, Mach disk stands just before the precursor shock wave due to expansion. Especially, the cases of Vexit ≥ 1875 m/s show similar pressure distribution and precursor shock wave propagation outside of tube. On the other hand, supersonic exit velocity, in Vexit = 1268 m/s, increases distance between precursor shock wave and Mach disk. Also, in Vexit = 658 m/s, although Mach disk is close to the muzzle, precursor shock wave propagates far away from Mach disk, which generates completely different pressure distribution. Secondary, in transition ballistic calculation, sabot separation motion does not depend on projectile exit velocity in our railgun configuration. From this result, the design of HVP need not to consider sabot trajectory variation even if exit velocity changes from supersonic (Vexit = 658 m/s) to hypersonic (Vexit = 2501 m/s) regime.

• Access to Document (DOI)

Propulsion performance of inner-cylinder-less rotating detonation engine

Yokoo R., Goto K., Kim J., Kawasaki A., Matsuoka K., Kasahara J., Matsuo A., Funaki I.

AIAA Scitech 2019 Forum (AIAA Scitech 2019 Forum)   2019

ISSN  9781624105784

　View Summary

© 2019 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. We evaluated the propulsion performance of a nozzle-less, inner-cylinder-less rotating detonation engine (RDE). For a C2H4–O2 mixture, the RDE was tested in a low-back-pressure environment at several propellant mass flow rates ranging from 8 to 45 g/s. In high-speed imaging of the self-luminescence within the combustor, rotating luminous regions were observed at a mass flow rates greater than 22 g/s. The specific impulse efficiency was greater than 80% for all the mass flow rate, and approximately 90% in some cases, which is comparable with ones in conventional RDEs having inner cylinders. By the control surface analysis, it was clarified that propellants injection from the injector holes and pressure on the bottom of the combustion chamber account for the thrust. It was also suggested that the design of the outer cylinder of the combustion chamber and the injector arrangement may affect the thrust performance. Axial Mach number distributions within the engine were calculated under an assumption of isentropic expansion. As a result, the burned gas reached a sonic or supersonic velocity at the outlet of the combustion chamber. Axial pressure distributions also suggested that the acceleration of the burned gas was completed at a far-upstream region within the combustion chamber.

• Access to Document (DOI)

Experimental performance validation of a rotating detonation engine toward a flight demonstration

Goto K., Yokoo R., Kim J., Kawasaki A., Matsuoka K., Kasahara J., Matsuo A., Funaki I., Nakata D., Uchiumi M.

AIAA Scitech 2019 Forum (AIAA Scitech 2019 Forum)   2019

ISSN  9781624105784

　View Summary

© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Thrust measurements of rotating detonation engine of (1) ethylene / gas-oxygen and (2) methane / gas-oxygen with various throat geometries in a vacuum chamber to simulate different back-pressure conditions ranging from 1.1-104 kPa were conducted. For throatless rotating detonation engine, we defined equivalent throat area as the detonation channel area, and then tested four nozzle contraction ratios of 1, 1.5, 2.5, and 8. Engines could be successfully ignited by electric ignitors when initial pressure was high enough to have, at least, one detonation cell in RDE channel. We measured the combustor pressure and reveled that it was almost proportional to the throat mass flux regardless of contraction ratios and the propellant combinations. The specific impulse of methane / gas-oxygen case could achieve 84 ± 1% of ideal specific impulse at the optimum expansion for each back pressure.

• Access to Document (DOI)

Numerical investigation on characteristic lengths for gaseous detonation with dilute water spray

Watanabe H., Matsuo A., Chinnayya A., Matsuoka K., Kawasaki A., Kasahara J.

AIAA Propulsion and Energy Forum and Exposition, 2019 (AIAA Propulsion and Energy Forum and Exposition, 2019)   2019

ISSN  9781624105906

　View Summary

© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Two-dimensional (2D) numerical simulations based on Eulerian-Lagrangian method are conducted to clarify the droplet behavior within its lifetime within the detonation cell. The simulation results are analyzed via 2D instantaneous flow fields and Favre spatiotemporal average technique, by applying the recycling block method. Gaseous detonation with dilute water droplets (WDs) propagates stably with a 4% velocity decrease compared to dry CJ velocity in the simulation conditions. From the instantaneous flow field analysis, the droplet breakup occurs primarily in jets, downstream of the transverse wave, nearby the collision of transverse waves, and the interaction between the transverse wave and the jets. The Favre average one-dimensional profiles by grouping WDs based on the initial shock strength that WDs experience reveal the droplet life inside the cellular structure. The mean equilibrium diameter after the breakup is not affected by the initial shock strength.

• Access to Document (DOI)

An experimental study of in-space rotating detonation engine with cylindrical configuration

Kawasaki A., Kim J., Yokoo R., Goto K., Matsuoka K., Kasahara J., Matsuo A., Funaki I.

AIAA Propulsion and Energy Forum and Exposition, 2019 (AIAA Propulsion and Energy Forum and Exposition, 2019)   2019

ISSN  9781624105906

　View Summary

© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Utilizing detonation in a combustor potentially leads to a compact and propellant-efficient rocket engine. A rotating detonation engine (RDE) is a form of such detonation engine. For a practical realization of the RDE, maturation of its thermal design is essential. In this study, a miniature cylindrical rotating detonation engine was tested in a low-pressure environment (~ 6 kPa) with a film-cooled wall. For the combustor, measurement of lateral wall temperature and high-speed imaging were conducted during combustion. As a result, it has been clarified that there exist an appropriate range in the coolant flow rate to maintain detonation combustion. Additionally, it has been also clarified that film cooling is effective even under detonation combustion.

• Access to Document (DOI)

Optical Measurement of Fluid Motion in Semi-Valveless Pulse Detonation Combustor with High-Frequency Operation

Kubota, A., Matsuoka, K., Kawasaki, A., Kasahara, J., Watanabe, H., Matsuo, A., and Endo, T.

Combustion Science and Technology 192 ( 2 ) 197 - 212 2018.12

Research paper (scientific journal), Joint Work, Accepted

• Access to Document (DOI)

Experimental investigation on detonation dynamics through a reactivity sink

Stéphane Boulal, Pierre Vidal, Ratiba Zitoun, Matsumoto, T., and Matsuo, A.

Combustion and Flame (Combustion and Flame)  196   11 - 25 2018.10

Research paper (scientific journal), Joint Work, Accepted,  ISSN  00102180

　View Summary

© 2018 The Combustion Institute This article reports on an experimental investigation into dynamical behaviours of detonation in non-uniform mixtures, generated from stoichiometric propane–oxygen, oxygen and ethane, with initial temperature and pressure 290 K and 20 kPa, respectively. Composition gradients are parallel to the direction of detonation propagation, with an equivalence ratio (ER) that first decreases from lean values and then increases to rich ones. Composition distributions are characterized according to the depth of the ER sink. Gradients are generated in a 50 × 50-mm2-square cross-section and a 665-mm total length chamber. The mixture components are injected separately in the pre-evacuated chamber in their order of decreasing density through porous plates at the chamber top-end to ensure planar filling of the chamber. Non-uniform distributions are then precisely controlled as a function of time by means of optical oxygen sensors. A Chapman–Jouguet (CJ) detonation is transmitted at the chamber bottom-end from a 3.6-m-long driver tube. Fast pressure transducers, sooted plates and Schlieren visualizations coupled with high-speed cameras are used to characterize the longitudinal velocity, cellular structure and transmission, failure and re-initiation mechanisms of the detonation front. Shallowest ER sinks produce the supercritical transmission mode of the CJ detonation with continuous adaptation of velocity and multicellular structure to local composition. Deepest sinks lead to the subcritical behaviour characterized by sudden detonation failure from shock-flame decoupling when ER decreases, and without detonation re-initiation when ER increases again. Intermediate sink depths generate critical behaviour with detonation re-initiat ion at chamber walls from expanding combustion kernels and reflected transverse Mach waves and then from SWACER retro-active mechanism. An elaboration of the failure criterion used in a previous study is found to well predict conditions for shock-flame decoupling.

• Access to Document (DOI)

Two-dimensional explosion experiments examining the interaction between a blast wave and a sand hill

Sugiyama, Y., Izumo, M., Ando, H., and Matsuo, A.

Shock Waves (Shock Waves)  28 ( 3 ) 627 - 630 2018.05

Research paper (scientific journal),  ISSN  09381287

　View Summary

© 2018, Springer-Verlag GmbH Germany, part of Springer Nature. Two-dimensional explosion experiments were conducted to discuss the interaction between a blast wave and sand and show the mitigation effect of the sand on the blast wave. The explosive used was a detonating cord 1.0 m in length, which was initiated in a sand hill shaped like a triangular prism and whose cross section was an isosceles triangle with base angles of 30∘. Sand-hill heights of 30 and 60 mm were used as parameters to discuss the effect of sand mass upon blast-wave strength. The interaction of the blast wave with the sand/air interface causes multiple peaks in the blast wave, which are induced by successive transmissions at the interface. The increase in the sand mass further mitigates the blast parameters of peak overpressure and positive impulse. The results of this experiment can be utilized to validate the numerical method of solving the problem of interaction between a compressible fluid and a particle layer.

• Access to Document (DOI)

CFD-DEM Simulation for Gas-Particle Flow with Shock Waves (in Japanese)

Kimura, A., Shimura, K., and Matsuo, A.

Japanese Journal of Multiphase Flow 32 ( 1 ) 65 - 72 2018.03

Research paper (scientific journal), Joint Work, Accepted

Simplification Method for Thrust Estimation of External Nozzle in Under-Expansion Condition (in Japanese)

Mikoshiba, R., Matsuo, A., Tomioka, S., Fujikawa, T., Tsuchiya, T., and Isono, T.

Journal of the Japan Society for Aeronautical and Space Sciences 66 ( 1 ) 15 - 23 2018.02

Research paper (scientific journal), Joint Work, Accepted

• Access to Document (DOI)

Two-dimensional CFD-DEM simulation of vertical shock wave-induced dust lifting processes

Shimura, K., and Matsuo, A.

Shock Waves (Shock Waves)  28 ( 6 ) 1285 - 1297 2018

Research paper (scientific journal),  ISSN  09381287

　View Summary

© 2018, Springer-Verlag GmbH Germany, part of Springer Nature. This paper conducts a numerical study of particle dispersion by vertical shock waves using a combination of computational fluid dynamics and the discrete element method (DEM). The Magnus force is important for particle dispersion, and the DEM approach can consider the rotation of individual particles and provide a detailed analysis of particle–particle and particle–wall interactions. Simulations are conducted and the results are compared with those of previous experiments, showing that the models can capture the particle dispersion process and shock wave geometry inside the mixed gas–particle region. During the particle dispersion process, the contact force due to the particle–particle interactions causes the particles to move upward after the shock wave passes and then decreases rapidly due to the low collision frequency in the particle cloud. The Magnus force is initially lower and has little effect until the contact force decreases, when it becomes dominant and maintains the particles’ upward movement. It is mainly driven by the gas rotation above the dust layer, and the effect of particle rotation is relatively small in comparison. The gas velocity gradient above the dust layer in the particle dispersion region is caused by gas–particle interactions. The particle dispersion region becomes wider and thinner over time, meaning that the gas velocity gradient above the dust layer becomes small and hence that the Magnus force (which is driven by the gas rotation) also becomes small. In contrast, the downward drag force remains constant during the vertical motion because it is primarily affected by the velocity difference between the particles and the gas. This means that the drag and Magnus forces eventually balance, and the particles stop rising.

• Access to Document (DOI)

The effect of shape on the aerodynamic and thermal performance of hypersonic projectiles launched by a ground-based railgun

Kasahara H., Matsuo A.

AIAA Aerospace Sciences Meeting, 2018 (AIAA Aerospace Sciences Meeting, 2018)   ( 210059 )  2018

ISSN  9781624105241

　View Summary

© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. In this paper, the effect of hypersonic-projectile design upon its aerodynamic coefficient is investigated to optimize projectile shape for ground-based-railgun launch. Previous studies on railgun-launch systems have suggested that projectiles experience significant thermal and aerodynamic effects when exiting the launcher because of their hypersonic exit velocity and the high enthalpy flow in the standard atmospheric condition. When designing a hypersonic projectile, the aerodynamic coefficient and thermal protection are crucial for maximizing range and withstanding heat. Two conditions of hypersonic flight, such as free flight and transitional ballistics, are simulated herein. To investigate the projectile’s geometric effect in the steady-flight condition, projectiles designed based on theory and empirical observation are compared. The aerodynamic result suggests that sharper projectiles do not always have smaller drag coefficients in simulation and theory because of a tradeoff between maximum pressure at the tip and pressure distribution on the latter half of the front shape. While temperature shows a similar trend compared to pressure, the maximum-temperature point is affected by projectile bluntness. Therefore, to optimize hypersonic design for thermal effect, it is inappropriate to adopt excess thermal protection at the tip, and an accurate prediction of maximum-heat-flux point is important. In addition to free-flight simulation, a transitional-ballistics simulation is performed. The interior and transitional calculations indicate that the precursor shockwave and sabot affect the flow field around the projectile. The sabot-separation phase can be divided into four stages based on the characteristics of the flow field. In the first and second stages, before the projectile undergoes the precursor shockwave, its shape has little effect on drag or velocity. However, when the projectile interacts with the sabot in the third and fourth stages, geometric effects can be observed. The theoretically optimized projectile is found to keep the highest flight velocity from transitional ballistics to free-flight.

• Access to Document (DOI)

The effect of exit velocity and material on the sabot separation launched by ground-based railgun

Kasahara H., Matsuo A.

2018 Applied Aerodynamics Conference (2018 Applied Aerodynamics Conference)   2018

ISSN  9781624105593

　View Summary

© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. In this paper, the sabot separation process in super/hypersonic flight from 600 to 2501 m/s is numerically investigated by using CFD and RBD (Rigid Body Dynamics). Firstly, the motion of sabot separation is calculated for validating our in-house code. CFD-RBD code shows good agreements with Mehmet’s experiment. Secondary, the effects of exit velocity from muzzle are examined. While all sabot velocities differ, sabot separations indicate the same trajectory. The variation of sabot velocity can be eliminated by non-dimensionalization considering exit velocity. Finally, the effects of sabot material, which means mass density, are investigated with railgun acceleration condition. Sabot separation shows different motion completely depending on sabot material. However, non-dimensionalization eliminates the effect of sabot material on separation. Proposed non-dimensionalization method can represent the various sabot separation motions in unique one trajectory, considering exit velocity and sabot density in time term.

• Access to Document (DOI)

Preliminary experiments on rotating detonation rocket engine for flight demonstration using sounding rocket

Goto K., Nishimura J., Higashi J., Taki H., Ukai T., Hayamizu Y., Kikuchi K., Yamada T., Watanabe S., Hotta K., Inakawa T., Kubota A., Yamaguchi M., Daicho T., Kawasaki A., Matsuoka K., Kasahara J., Matsuo A., Funaki I., Yasuda K., Mori K., Yagihashi H., Nakata D., Uchiumi M., Higashino K.

AIAA Aerospace Sciences Meeting, 2018 (AIAA Aerospace Sciences Meeting, 2018)   ( 210059 )  2018

ISSN  9781624105241

　View Summary

© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Rotating detonation engine (RDE) is a promising candidate for future upper stage motor because of its high theoretical efficiency and short combustor length. Technological demonstration in space will be necessary to evaluate the performance and flight dynamics of RDE as a space propulsion system. Toward a flight test, we built an open-structure, rocket RDE-powered vehicle to measure thrust to validate a feasibility of an onboard propulsion system. We carried out 4.4 s combustion test, and achieved over 73% of ideal specific impulse above 1.1 MPa of static pressure in the RDE combustor.

• Access to Document (DOI)

Numerical investigation of the gas-particle flow in the shock tube using discrete particle and continuum model

Kimura A., Matsuo A.

2018 Fluid Dynamics Conference (2018 Fluid Dynamics Conference)   2018

ISSN  9781624105531

　View Summary

© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. The numerical investigation of the gas-particle flow in the shock tube is conducted using the continuum model (Two-Fluid model) and the discrete particle model (CFD-DEM). From calculated results of both methods, particles are concentrated at downstream edge of particle bed and dispersed at upstream edge of particle bed with the passage of time. The incident shock wave is divided into the reflected shock and the transmitted shock because of interactions with particles. These flow field can be observed in the experiment conducted by Rogue et al., and Two-Fluid model and CFD-DEM can qualitatively reproduce the interaction phenomena between shock wave and particles. In the experiment, the pressure oscillations behind the reflected and the transmitted shock wave are observed as well as CFD-DEM, but no oscillation is seen in Two-Fluid model. Therefore, Two-Fluid model can qualitatively reproduce the interaction phenomena of shock wave and particles qualitatively, although the behavior of individual particle is neglected in the model.

• Access to Document (DOI)

Numerical analysis of the influence of the nose shape on the flight stability of the underwater projectile (in Japanese)

Okuno, K., and Matsuo, A.

Transactions of the JSME 83 ( 856 )  2017.12

Research paper (scientific journal), Joint Work, Accepted

• Access to Document (DOI)

Validation of Pulse Detonation Operation in Low-Ambient-Pressure Environment

Matsuoka, K., Takagi, S.,Kasahara, J., Matsuo, A., and Funaki, I.

Journal of Propulsion and Power (Journal of Propulsion and Power)  34 ( 1 ) 116 - 124 2017.06

Research paper (scientific journal), Joint Work, Accepted,  ISSN  07484658

　View Summary

© Copyright 2017 by Nagoya University. A pulse-detonation thruster can generate a high-repeatability small impulse at a high operating frequency. To operate a pulse-detonation cycle in a vacuum environment without a purging material, a liquid-purge method proposed by Matsuoka et al. ("Development of a Liquid-Purge Method for High-Frequency Operation of Pulse Detonation Combustor," Combustion Science and Technology, Vol. 187, No. 5, 2015, pp. 747-764) and throat at the exit of the combustor were introduced. In the demonstration experiment, gaseous ethylene-liquid nitrous oxide, as detonable mixture, and a throat having an inner diameter of 3.6 mm (blockage ratio = 87%) were used. The measured cyclic flame-propagation speeds were 2005 ± 90 m/s and 92 ± 4% of the estimated Chapman-Jouguet detonation speed. Consequently, a 50 Hz pulse-detonation operation without a purging material in the ambientpressure range of 0.035-1.5 kPa was confirmed. A quasi-steady model, in which gases in the combustor are in the stationary state, was newly developed to investigate the operating characteristic of the pulse-detonation thruster. The experimental pressure history in the combustor during the burned-gas blowdown process was in good agreement with that of the model. Moreover, using the model, the thrust performance of the pulse-detonation thruster with a converging-diverging nozzle was investigated. It was found that the estimated specific impulse was comparable with that of the theoretical steady-state rocket engine.

• Access to Document (DOI)

Supersonic Combustion Using Multiple Stinger-shaped Injectors

Kouchi, T., Tomioka, S., Hirano, K., Matsuo, A., and Masuya, G.

Transactions of JSASS 60 ( 1 ) 56 - 59 2017.01

Research paper (scientific journal), Joint Work, Accepted

Development of High-Frequency Pulse Detonation Combustor Without Purging Material

Matsuoka, K., Muto, K., Kasahara, J., Watanabe, H., Matsuo, A., and Endo, T.

Journal of Propulsion and Power, Special Section on Pressure Gain Combustion 33 ( 1 ) 43 - 50 2017.01

Research paper (scientific journal), Joint Work, Accepted

• Access to Document (DOI)