研究者データベース

高橋 裕介(タカハシ ユウスケ)
工学研究院 機械・宇宙航空工学部門 宇宙航空システム
助教

基本情報

所属

  • 工学研究院 機械・宇宙航空工学部門 宇宙航空システム

職名

  • 助教

学位

  • 博士(工学)(九州大学)

ホームページURL

科研費研究者番号

  • 40611132

J-Global ID

研究キーワード

  • アーク加熱風洞   惑星大気再突入機   高エンタルピ流   

研究分野

  • フロンティア(航空・船舶) / 航空宇宙工学

職歴

  • 2012年04月 - 現在 北海道大学 大学院工学研究院 助教
  • 2016年04月 - 2017年03月 German Aerospace Center (DLR) Supersonic and Hypersonic Technologies Department of the Institute of Aerodynamics and Flow Technology Visiting Researcher
  • 2011年04月 - 2012年03月 独立行政法人宇宙航空研究開発機構 研究員

研究活動情報

論文

  • Yusuke Takahashi, Naoya Enoki, Hideto Takasawa, Nobuyuki Oshima,
    Journal of Physics D: Applied Physics 53 23 235203 - 235203 2020年04月 [査読有り][通常論文]
  • Naoya Enoki, Yusuke Takahashi, Nobuyuki Oshima, Kazuhiko Yamada, Kojiro Suzuki
    AIP Conference Proceedings 2132 100002  American Institute of Physics 2019年08月05日 [査読有り][通常論文]
  • Yusuke Takahashi, Taiki Koike, Nobuyuki Oshima, Kazuhiko Yamada
    Aerospace Science and Technology 92 858 - 868 2019年 [査読有り][通常論文]
  • Yusuke Takahashi, Manabu Matsunaga, Nobuyuki Oshima, Kazuhiko Yamada
    Journal of Spacecraft and Rockets 56 2 577 - 585 2019年 [査読有り][通常論文]
  • 田中真由子, 山田和彦, 高橋裕介, Yu Minghao, 手塚亜聖
    日本航空宇宙学会論文集 67 2 42 - 48 2019年 [査読有り][通常論文]
  • 福田泰久, 荒谷貴洋, 高橋裕介, 山田和彦, 小柳潤
    航空宇宙技術 18 127 - 131 2019年 [査読有り][通常論文]
  • Yusuke Takahashi, Kazuhiko Yamada
    Acta Astronautica 152 437 - 448 2018年11月 [査読有り][通常論文]
  • Tatsushi Ohashi, Yusuke Takahashi, Hiroshi Terashima, Nobuyuki Oshima
    Journal of Fluid Science and Technology 13 3 JFST0020 - JFST0020 2018年10月 [査読有り][通常論文]
  • Yusuke Takahashi, Kazuhiko Yamada
    Journal of Thermophysics and Heat Transfer 32 3 547 - 559 2018年07月 [査読有り][通常論文]
  • Jung Minseok, Kihara Hisashi, Ken-ichi Abe, Yusuke Takahashi
    Physics of Plasmas 25 1 013507  2018年01月 [査読有り][通常論文]
  • 高橋裕介, 松永学, 大島伸行, 山田和彦
    日本航空宇宙学会誌(特集) 65 12 370 - 376 2017年12月 [査読有り][通常論文]
  • Yusuke Takahashi, Burkard Esser, Lars Steffens, Ali Guelhan
    PHYSICS OF PLASMAS 24 12 123509  2017年12月 [査読有り][通常論文]
     
    In this study, we developed an analytical model for the flow field in the Huels-type arc-heated wind tunnel (L2K) of the German Aerospace Center. This flow-field model can be used to accurately reproduce the discharge behavior in the heating section and expansion in the nozzle section of L2K. It includes the radiation transport and turbulent flow as well as thermochemical nonequilibrium models, which are tightly coupled with electric field calculations. In addition, we considered the turbulent diffusion model for the mass conservation of the species and performed numerical simulations for several cases with and without the turbulent diffusion model. Computations were conducted to obtain the general characteristics of an arc-heated flow containing an arc discharge and supersonic expansion. We verified that radiation and turbulence play important roles in the transfer of heat from the high-temperature core flow to the outer cold gas in the heating section of L2K. In addition, we performed parametric studies that involved varying the degree of turbulent diffusion. The results showed that turbulent diffusion has a large influence on the formation of the arc discharge in the heating section and on the enthalpy distribution at the nozzle exit. Published by AIP Publishing.
  • Landon Kamps, Yuji Saito, Ryosuke Kawabata, Masashi Wakita, Tsuyoshi Totani, Yusuke Takahashi, Harunori Nagata
    Journal of Propulsion and Power 33 6 1369 - 1377 American Institute of Aeronautics and Astronautics 2017年11月 [査読有り][通常論文]
  • 山田和彦, 鈴木宏二郎, 安部隆士, 秋田大輔, 今村宰, 永田靖典, 高橋裕介
    日本航空宇宙学会誌(特集) 65 11 333 - 340 2017年11月 [査読有り][通常論文]
  • Yusuke Takahashi, Dongheun Ha, Nobuyuki Oshima, Kazuhiko Yamada, Takashi Abe, Kojiro Suzuki
    JOURNAL OF SPACECRAFT AND ROCKETS 54 5 993 - 1004 2017年09月 [査読有り][通常論文]
     
    A flight experiment of an inflatable reentry vehicle, equipped with a thin-membrane aeroshell deployed by an inflatable torus structure, was performed using a Japan Aerospace Exploration Agency S-310-41 sounding rocket. The drag coefficient history was evaluated by analyzing the acceleration of the vehicle with the atmospheric density and temperature using a global reference atmospheric model. The vehicle successfully demonstrated deceleration. During the reentry flight, the position, velocity, and acceleration of the vehicle were obtained by using the Global Positioning System. The experimental drag coefficient had an almost constant value of 1.5 in the supersonic region but decreased to 1.0 in the subsonic region. In the transonic region, a steep decrease of the drag coefficient was confirmed. To study the detailed aerodynamics for the reentry vehicle, flowfield simulations were conducted with computational fluid dynamics techniques. The aerodynamic force acting on the vehicle was investigated with the measured data throughout the supersonic and subsonic regions. In the flowfield simulation, the computed result for the drag coefficient showed reasonable agreement with the experimental one. In addition, a compressible effect in front of the vehicle was seen to appear in the supersonic region and a vortex ring at the rear of the vehicle was formed in the subsonic region.
  • Minghao Yu, Kazuhiko Yamada, Yusuke Takahashi, Kai Liu, Tong Zhao
    PHYSICS OF PLASMAS 23 12 123523  2016年12月 [査読有り][通常論文]
     
    A numerical model for simulating air and nitrogen inductively coupled plasmas (ICPs) was developed considering thermochemical nonequilibrium and the third-order electron transport properties. A modified far-field electromagnetic model was introduced and tightly coupled with the flow field equations to describe the Joule heating and inductive discharge phenomena. In total, 11 species and 49 chemical reactions of air, which include 5 species and 8 chemical reactions of nitrogen, were employed to model the chemical reaction process. The internal energy transfers among translational, vibrational, rotational, and electronic energy modes of chemical species were taken into account to study thermal nonequilibrium effects. The low-Reynolds number Abe-Kondoh-Nagano k-epsilon turbulence model was employed to consider the turbulent heat transfer. In this study, the fundamental characteristics of an ICP flow, such as the weak ionization, high temperature but low velocity in the torch, and wide area of the plasma plume, were reproduced by the developed numerical model. The flow field differences between the air and nitrogen ICP flows inside the 10-kW ICP wind tunnel were made clear. The interactions between the electromagnetic and flow fields were also revealed for an inductive discharge. Published by AIP Publishing.
  • Minseok Jung, Hisashi Kihara, Ken-ichi Abe, Yusuke Takahashi
    JOURNAL OF THE KOREAN PHYSICAL SOCIETY 68 11 1295 - 1306 2016年06月 [査読有り][通常論文]
     
    A three-dimensional numerical simulation model that considers the effect of the angle of attack was developed to evaluate plasma flows around reentry vehicles. In this simulation model, thermochemical nonequilibrium of flowfields is considered by using a four-temperature model for high-accuracy simulations. Numerical simulations were performed for the orbital reentry experiment of the Japan Aerospace Exploration Agency, and the results were compared with experimental data to validate the simulation model. A comparison of measured and predicted results showed good agreement. Moreover, to evaluate the effect of the angle of attack, we performed numerical simulations around the Atmospheric Reentry Demonstrator of the European Space Agency by using an axisymmetric model and a three-dimensional model. Although there were no differences in the flowfields in the shock layer between the results of the axisymmetric and the three-dimensional models, the formation of the electron number density, which is an important parameter in evaluating radio-frequency blackout, was greatly changed in the wake region when a non-zero angle of attack was considered. Additionally, the number of altitudes at which radio-frequency blackout was predicted in the numerical simulations declined when using the three-dimensional model for considering the angle of attack.
  • Yusuke Takahashi, Reo Nakasato, Nobuyuki Oshima
    Aerospace 3 1 2 - 2 2016年01月 [査読有り][通常論文]
  • Yusuke Takahashi
    JOURNAL OF PHYSICS D-APPLIED PHYSICS 49 1 015201  2016年01月 [査読有り][通常論文]
     
    An analysis model of plasma flow and electromagnetic waves around a reentry vehicle for radio frequency blackout prediction during aerodynamic heating was developed in this study. The model was validated based on experimental results from the radio attenuation measurement program. The plasma flow properties, such as electron number density, in the shock layer and wake region were obtained using a newly developed unstructured grid solver that incorporated real gas effect models and could treat thermochemically non-equilibrium flow. To predict the electromagnetic waves in plasma, a frequency-dependent finite-difference time-domain method was used. Moreover, the complicated behaviour of electromagnetic waves in the plasma layer during atmospheric reentry was clarified at several altitudes. The prediction performance of the combined model was evaluated with profiles and peak values of the electron number density in the plasma layer. In addition, to validate the models, the signal losses measured during communication with the reentry vehicle were directly compared with the predicted results. Based on the study, it was suggested that the present analysis model accurately predicts the radio frequency blackout and plasma attenuation of electromagnetic waves in plasma in communication.
  • Yusuke Takahashi, Kazuhiko Yamada, Takashi Abe, Kojiro Suzuki
    JOURNAL OF SPACECRAFT AND ROCKETS 52 6 1530 - 1541 2015年11月 [査読有り][通常論文]
     
    A demonstration flight of an advanced reentry vehicle was carried out using a sounding rocket. The vehicle was equipped with a flexible (membrane) aeroshell deployed by an inflatable torus structure. Its most remarkable feature was the low ballistic coefficient that enables reduction in aerodynamic heating and deceleration at a high altitude. During the suborbital reentry, temperatures at several locations on a backside of the flexible aeroshell and inside the capsule were measured by means of embedded thermocouples. The aerodynamic heating behavior of the vehicle was investigated using the measured temperature history, in combination with a numerical prediction in which a flow-field simulation of the heating was conducted. In this flow-field simulation, both laminar flow and turbulent flow were assumed, and the deformation of the flexible aeroshell was considered. A thermal model of the capsule and membrane aeroshell was developed, and the heat flux profiles of the vehicle surface during aerodynamic heating were constructed based on the measured temperatures. The measured temperature data were found to be in reasonable agreement with the predicted data if the flow field near the capsule of the vehicle was assumed to be laminar, with a transition to turbulent flow near the membrane aeroshell.
  • Yu Minghao, Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe, Kazuhiko Yamada, Takashi Abe, Satoshi Miyatani
    PLASMA SCIENCE & TECHNOLOGY 17 9 749 - 760 2015年09月 [査読有り][通常論文]
     
    Two-dimensional (2D) numerical simulations of thermochemical nonequilibrium inductively coupled plasma (ICP) flows inside a 10-kW inductively coupled plasma wind tunnel (ICPWT) were carried out with nitrogen as the working gas. Compressible axisymmetric NavierStokes (N-S) equations coupled with magnetic vector potential equations were solved. A fourtemperature model including an improved electron-vibration relaxation time was used to model the internal energy exchange between electron and heavy particles. The third-order accuracy electron transport properties (3rd AETP) were applied to the simulations. A hybrid chemical kinetic model was adopted to model the chemical nonequilibrium process. The flow characteristics such as thermal nonequilibrium, inductive discharge, effects of Lorentz force were made clear through the present study. It was clarified that the thermal nonequilibrium model played an important role in properly predicting the temperature field. The prediction accuracy can be improved by applying the 3rd AETP to the simulation for this ICPWT.
  • Minghao Yu, Hisashi Kihara, Ken-ichi Abe, Yusuke Takahashi
    JOURNAL OF THE KOREAN PHYSICAL SOCIETY 66 12 1833 - 1840 2015年06月 [査読有り][通常論文]
     
    A relatively simple method for calculating accurately the third-order electron transport properties of nitrogen and air thermal plasmas is presented. The electron transport properties, such as the electrical conductivity and the electron thermal conductivity, were computed with the best and latest available collision cross-section data in the temperature and pressure ranges of T = 300 - 15000 K and p = 0.01 - 1.0 atm, respectively. The results obtained under the atmospheric pressure condition showed good agreements with the experimental and the high-accuracy theoretical results. The presently-introduced method has good application potential in numerical simulations of nitrogen and air inductively-coupled plasmas.
  • Dongheun HA, Yusuke TAKAHASHI, Kazuhiko YAMADA, Takashi ABE
    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan 12 ists29 Po_2_57 - Po_2_62 2014年12月 [査読有り][通常論文]
  • Yusuke Takahashi, Kazuhiko Yamada, Takashi Abe
    JOURNAL OF SPACECRAFT AND ROCKETS 51 6 1954 - 1964 2014年11月 [査読有り][通常論文]
     
    A numerical simulation model that combines the plasma flows and electromagnetic waves around a reentry vehicle during atmospheric reentry was developed to evaluate the radio frequency blackout and plasma attenuation. The physical properties of the plasma flow in the shock layer and wake region were obtained using a computational fluid dynamics technique. The electromagnetic waves were expressed using a frequency-dependent finite difference time domain method with the plasma properties. Combined simulations were performed for the atmospheric reentry demonstrator of the ESA at various altitudes based on reentry orbit data. The electromagnetic wave behaviors around the vehicle during atmospheric reentry were investigated in detail. Moreover, a parametric analysis with different ionization reaction models was performed. It was confirmed that the vehicle is surrounded by the plasma and the propagation of the electromagnetic waves is prevented at high altitude. Then, the plasma is dissipated and the propagation recovers at low altitude. Validation of the simulation model was performed based on the plasma attenuation history of the experimental flight data. A comparison of the measured and predicted results showed good agreement. It was concluded that the combined simulation model could be an effective tool for investigating the radio frequency blackout and the plasma attenuation of radio wave communication.
  • Yu Minghao, Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe, Kazuhiko Yamada, Takashi Abe
    PLASMA SCIENCE & TECHNOLOGY 16 10 930 - 940 2014年10月 [査読有り][通常論文]
     
    Numerical simulations of 10 kW and 110 kW inductively coupled plasma (ICP) wind tunnels were carried out to study physical properties of the flow inside the ICP torch and vacuum chamber with air as the working gas. Two-dimensional compressible axisymmetric NavierStokes (N-S) equations that took into account 11 species and 49 chemical reactions of air, were solved. A heat source model was used to describe the heating phenomenon instead of solving the electromagnetic equations. In the vacuum chamber, a four-temperature model was coupled with N-S equations. Numerical results for the 10 kW ICP wind tunnel are presented and discussed in detail as a representative case. It was found that the plasma flow in the vacuum chamber tended to be in local thermochemical equilibrium. To study the influence of operation conditions on the flow field, simulations were carried out for different chamber pressures and/or input powers. The computational results for the above two ICP wind tunnels were compared with corresponding experimental data. The computational and experimental results agree well, therefore the flow fields of ICP wind tunnels can be clearly understood.
  • Naoya Hirata, Masataka Yamada, Hisashi Kihara, Ken-ichi Abe, Yusuke Takahashi
    Journal of Thermophysics and Heat Trasnfer, 28 4 709 - 803 2014年10月 [査読有り][通常論文]
  • Yusuke Takahashi, Kazuhiko Yamada, Takashi Abe
    JOURNAL OF SPACECRAFT AND ROCKETS 51 2 430 - 441 2014年03月 [査読有り][通常論文]
     
    Numerical simulations of the plasma flow and electromagnetic wave around a membrane-aeroshell type reentry vehicle were performed using various physical model combinations, and the possibility of radio frequency blackout of transceiver antenna embedded at the rear of the vehicle was investigated. The flowfield was assumed to be in thermochemical nonequilibrium, and it was described by the Navier-Stokes equations with a multitemperature model and the equation of state. The simulations were performed for several altitudes, including the highest heat flux point according to reentry orbit data. Through these computations, the detailed distributions of the flowfield properties in the shock layer and wake region were successfully obtained. To evaluate the possibility of radio frequency blackout during atmospheric reentry, the distribution of the electron number density around the inflatable vehicle was clarified. A frequency-dependent finite-difference time-domain method was used for simulations of electromagnetic waves, and the physical properties were obtained from the computational results of the plasma flow calculation. Electromagnetic wave behaviors in an ionized gas region behind the inflatable vehicle were investigated. It was found that the number density of electrons was sufficiently small and that the electromagnetic waves can propagate with no reflection and less attenuation. These results suggest that radio frequency blackout may not occur during the atmospheric reentry of the inflatable vehicle.
  • Yusuke Takahashi, Takashi Abe, Hiroki Takayanagi, Masahito Mizuno, Hisashi Kihara, Ken-ichi Abe
    JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER 28 1 9 - 17 2014年01月 [査読有り][通常論文]
     
    Turbulent plasma flows in arc heaters, such as Japan Aerospace Exploration Agency's 750 kW, NASA's 20 MW, and Kyushu University's 20 kW facilities, were investigated, and the distributions of the flowfield properties were successfully obtained. The arc discharge in the constrictor section and the expansion processes in the nozzle section played key roles in the formation of an arc-heated flow. Hence, for accurately predicting high-enthalpy flow properties, it was important to correctly model the complex phenomena observed in various-scale facilities. For this purpose, an integrated analysis model to simulate various-scale arc-heated flows with high accuracy was developed. The turbulent flowfield was described using the Reynolds-averaged Navier-Stokes equations with a multitemperature model, which was tightly coupled with electric-field and radiation-field calculations. A sophisticated and low-cost radiation model and a low-Reynolds-number two-equation turbulence model were introduced into the flowfield simulation. To validate the present integrated analysis model, the computed results were compared with the corresponding experimental data for the mass-averaged enthalpy, the translational and rotational temperatures, and the number density of nitrogen obtained through spectroscopic and laser-induced fluorescence techniques. Moreover, the mechanisms of energy input by discharge and energy loss are discussed, along with the distributions of the electronic excitation temperature and heat flux on the constrictor wall derived from the arc column. Although the results indicated that a relatively detailed discharge model is required to describe the arc discharge with relatively high accuracy, the present flowfield model was generally in good agreement with various operating conditions of the facilities.
  • Minghao Yu, Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe, Kazuhiko Yamada, Takashi Abe
    PROCEEDINGS OF THE 29TH INTERNATIONAL SYMPOSIUM ON RAREFIED GAS DYNAMICS 1628 1124 - 1131 2014年 [査読有り][通常論文]
     
    Numerical investigation of nonequilibrium inductively coupled plasma (ICP) flow was carried out to study the physical properties of the flow inside a 10-kW ICP torch with the working gas being nitrogen. The flow field was described by two-dimensional compressible axisymmetric Navier-Stokes (N-S) equations that took into account 5 species and 8 chemical reactions. The magnetic vector-potential equations were tightly coupled with the flow-field equations to describe the heating process by inductive discharge. A four-temperature model was adopted to model thermal nonequilibrium process in the discharge torch. The characteristics of ICP flow such as thermal nonequilibrium, inductive discharge, and strong effects of Lorentz forces became clear through the present study.
  • Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe
    JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER 26 3 540 - 544 2012年07月 [査読有り][通常論文]
  • Naoya Hirata, Sohei Nozawa, Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe
    Computational Thermal Sciences 4 3 225 - 242 2012年 [査読有り][通常論文]
  • Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe
    JOURNAL OF PHYSICS D-APPLIED PHYSICS 44 8 085203  2011年03月 [査読有り][通常論文]
     
    Turbulent plasma flow in large-scale arc heaters such as JAXA 750 kW and NASA 20 MW facilities was investigated and distributions of flow-field properties were successfully obtained. The turbulent flow field was described by the Navier-Stokes equations with a multitemperature model, which was tightly coupled with electric-field and radiation-field calculations. An accurate and low-cost radiation model, and a low Reynolds number two-equation turbulence model were introduced into the flow-field simulation. It was confirmed that the plasma flows in the arc-heating facilities were in a highly thermochemical nonequilibrium state in the expansion section and that the arc discharge plays a critical role in the heating section. It was quantitatively clarified that radiation and turbulence phenomena were very important in transferring heat and momentum from the high-temperature flow near the core to the cold gas region near the facility wall. To confirm the effectiveness of the present numerical model, the obtained results were compared with experimental data for the arc voltage, mass-averaged enthalpy, chamber pressure and heat efficiency. The present flow-field model was found to give good agreement for various operating conditions of the facilities.
  • Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe
    JOURNAL OF PHYSICS D-APPLIED PHYSICS 43 18 185201  2010年05月 [査読有り][通常論文]
     
    Numerical simulation of a 20 kW constrictor-type arc-heated flow was carried out, and the distribution of the nonequilibrium flow-field properties was obtained. The flow field was described by the Navier-Stokes equations with a multi-temperature model, tightly coupled with the electric-field and radiation-field calculations. As a radiation model, an accurate and low-cost model was introduced into the flow-field simulation. It was confirmed that the plasma flow inside the arc-heated facility is in a state of high nonequilibrium and the arc discharge plays a critical role. By comparing the computational results with/without the radiation model, it was clarified that the radiation exerts significant effects on the heat transport in the constrictor section. Additionally, to validate the present numerical model, the numerical solutions were compared with the experimental data. It was indicated that the present flow-field simulation with a radiation model tends to be in good agreement with the corresponding experimental data.
  • Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe
    JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER 24 1 31 - 39 2010年01月 [査読有り][通常論文]
     
    Numerical simulations are carried out and the distributions of flowfield properties are obtained for nonequilibrium, flows in a 20 kW constrictor-type and a 750 kW segmented-type arc-heated wind tunnel. In these arc heaters, it is confirmed that each plasma flow is highly in nonequilibrium and are discharge plays critical roles. The flowfield is described by the Navier-Stokes equations with a multitemperature model. To validate the present numerical model, the numerical solutions are compared with the corresponding experimental data. The flow characteristics in the 20 and 750 kW arc heaters (e.g., the arc discharge and the supersonic expansion) become clear through the present simulations. In particular, the computed results for the 20 kW arc heater indicate almost full dissociation/ionization reactions and thermochemical equilibrium in the constrictor section, while strong nonequilibrium clearly appears in the nozzle section.
  • Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe
    RAREFIED GAS DYNAMICS 1084 883 - 888 2009年 [査読無し][通常論文]
     
    Numerical simulation is carried out and the distribution of flow field properties is obtained for nonequilibrium flow in a constrictor-type 20kW arc-heated wind tunnel. In the arc heater, plasma flow is highly in nonequilibrium and arc discharge plays a critical role. The flow field is described by the Navier-Stokes equations with a multi-temperature model. The flow field equations are solved with the governing equation for the electric field being coupled. Furthermore, to validate the present numerical model, the numerical solutions are compared with the corresponding experimental data. The flow characteristics in the 20kW arc heater, e.g., the arc charge and the supersonic expansion, become clear through the present simulation. Moreover, the computed results for the arc heater indicate almost full dissociation/ionization reactions and thermochemical equilibrium in the constrictor part, while strong nonequilibrium clearly appears in the nozzle section.

書籍

  • Encyclopedia of Plasma Technology
    Yusuke Takahashi (担当:分担執筆範囲:Arc-Heated Wind Tunnel)
    CRC Press, Taylor & Francis Group 2017年02月 (ISBN: 146650059X) 1728

講演・口頭発表等

  • Study on Mitigation of Reentry Blackout by Surface Catalysis Effects in Arc-Heated Wind Tunnel  [通常講演]
    Hideto Takasawa, Yusuke Takahashi, Nobuyuki Oshima, Hisashi Kihara
    Aerospace Europe Conference 2020, 2020年02月 口頭発表(一般) Bordeaux
  • 再突入ブラックアウト低減化に向けた数値的研究  [招待講演]
    高橋裕介
    日本学術会議第9回計算力学シンポジウム 2019年12月 口頭発表(招待・特別)
  • Toru TSURUMOTO, Yusuke TAKAHASHI, Hiroshi TERASHIMA, Nobuyuki OSHIMA
    8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) 2019年07月 口頭発表(一般) Madrid
  • Aerodynamics of Inflatable Nano-Satellite “EGG” in Low Earth Orbit and Reentry Duration  [通常講演]
    Naoya Enoki, Yusuke Takahashi, Nobuyuki Oshima, Kazuhiko Yamada, Kojiro Suzuki
    31st Internal Symposium on Rarefied Gas Dynamics 2018年07月 口頭発表(一般)
  • 大気再突入時における宇宙機の空力・空力加熱について  [招待講演]
    高橋裕介, 小池太輝
    北海道大学-JAXA連携企画講演会・HASTIC学術技術講演会 2018年03月 口頭発表(招待・特別)
  • Aerodynamic Heating Prediction of Flare-type Membrane Inflatable Reentry Vehicle from Low Earth Orbit  [通常講演]
    Taiki Koike, Yusuke Takahashi, Nobuyuki Oshima, Kazuhiko Yamada
    2018 AIAA Atmospheric Flight Mechanics Conference, AIAA SciTech Forum 2018年01月 口頭発表(一般)
  • Aerodynamic Instability of Flare-type Membrane Inflatable Vehicle in Suborbital Reentry Demonstration  [通常講演]
    Tatsushi OHASHI, Manabu MATSUNAGA, Yusuke TAKAHASHI, Hiroshi TERASHIMA, Nobuyuki OSHIMA
    The Ninth JSME-KSME Thermal and Fluids Engineering Conference (TFEC9) 2017年10月 口頭発表(一般)
  • Prediction of electromagnetic waves around an inflatable reentry vehicle in an atmospheric reentry mission  [通常講演]
    Naoya ENOKI, Manabu MATSUNAGA, Yusuke TAKAHASHI, Hiroshi TERASHIMA, Nobuyuki OSHIMA, Kazuhiko YAMADA, Kojiro SUZUKI
    The Ninth JSME-KSME Thermal and Fluids Engineering Conference (TFEC9) 2017年10月 口頭発表(一般)
  • Large-Eddy Simulation with a New Flamelet Model for Partially Premixed Combustion in a Gas-Turbine Combustor  [通常講演]
    Keisuke Tanaka, Tomonari Sato, Nobuyuki Oshima, Jiun Kim, Yusuke Takahashi, Yasunori Iwai
    the ASME 2017 Power and Energy Conference 2017年06月 口頭発表(一般)
  • Numerical Simulation of Plasma Flows and Radio-Frequency Blackout in Atmospheric Reentry Demonstrator Mission  [通常講演]
    Minseok Jung, Hisashi Kihara, Ken-ichi Abe, Yusuke Takahashi
    47th AIAA Fluid Dynamics Conference, AIAA AVIATION Forum 2017年06月 口頭発表(一般)
  • Aerodynamic Heating Prediction of an Inflatable Reentry Vehicle in a Hypersonic Wind Tunnel  [通常講演]
    Manabu Matsunaga, Yusuke Takahashi, Nobuyuki Oshima, Kazuhiko Yamada
    55th AIAA Aerospace Sciences Meeting 2017年01月 口頭発表(一般)
  • NUMERICAL INVESTIGATION OF ABLATION EFFECT ON AERODYNAMIC HEATING FOR HIGH VELOCITY REENTRY CAPSULE  [通常講演]
    Manabu Matsunaga, Takahiro Sasaki, Yusuke Takahashi, Nobuyuki Oshima
    The 27th International Symposium on Transport Phenomena (ISTP27) 2016年09月 口頭発表(一般)
  • NUMERICAL ANALYSIS OF RADIO FREQUENCY BLACKOUT FOR ATMOSPHERIC REENTRY VEHICLE USING CFD-CEM COMBINED METHOD  [通常講演]
    Yusuke Takahashi, Reo Nakasato, Nobuyuki Oshima
    VII European Congress on Computational Methods in Applied Sciences and Engineering (ECCOMAS Congress 2016) 2016年06月 口頭発表(一般) Crete Island, Greece
  • Development of Analysis Tools for Space Vehicle in Atmospheric Reentry Mission  [招待講演]
    Yusuke Takahashi, Nobuyuki Oshima
    Korea-Japan CFD Workshop 2015 2015年12月 口頭発表(招待・特別)
  • Numerical Investigation of Turbulent Combustion Flow in Industrial Combustor with Flamelet Approach  [通常講演]
    Tenshi Sasaki, Yusuke Takahashi, Nobuyuki Oshima, Yasunori Iwai
    International Conference on Power Engineering-15 (ICOPE-15) 2015年11月 口頭発表(一般) Yokohama, Japan
  • Accuracy Verification of the Turbulent Flame LES Model by a Methane/Air Burner Flame  [通常講演]
    Kagenobu Murase, Nobuyuki Oshima, Yusuke Takahashi
    ASME-JSME-KSME Joint Fluids Engineering Conference 2015 2015年07月 口頭発表(一般) Seoul, Korea
  • Aerodynamic Simulation of Closed-Canopy-Type Parafoil for Martian Exploration Mission  [通常講演]
    Daiki Harada, Yusuke Takahashi, Nobuyuki Oshima, Kazuhiko Yamada
    ASME-JSME-KSME Joint Fluids Engineering Conference 2015 2015年07月 口頭発表(一般) Seoul, Korea
  • Numerical Study of Plasma Flow around a Reentry Vehicle during Atmospheric Reentry with an Unstructured Grid Solver  [通常講演]
    Reo Nakasato, Yusuke Takahashi, Nobuyuki Oshima
    ASME-JSME-KSME Joint Fluids Engineering Conference 2015 2015年07月 口頭発表(一般) Seoul, Korea
  • Large-Eddy Simulation of Transient Behavior in a Combustion Field for Gas-Turbine Engine  [通常講演]
    Yusuke Takahashi, Nobuyuki Oshima, Yasunori Iwai
    WCCM XI-ECCM V-ECFD VI 2014年07月 口頭発表(一般)
  • Numerical Simulation of Flow Field around an Inflatable Vehicle during a Reentry Demonstration Flight  [通常講演]
    Dongheun Ha, Yusuke Takahashi, Kazuhiko Yamada, Takashi Abe
    AIAA-2014-3283 2014年06月 口頭発表(一般)
  • Numerical Investigation of Flow Fields in Inductively Coupled Plasma Wind Tunnel  [通常講演]
    Minghao Yu, Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe, Kazuhiko Yamada, Takashi Abe
    4th Asian Symposium on Computational Heat Transfer and Fluid Flow 2013年06月 口頭発表(一般)
  • Aerodynamic Simulation of an Inflatable Re-Entry Vehicle Performance in Low Speed Wind Tunnel  [通常講演]
    Dongheun Ha, Yusuke Takahashi, Kazuhiko Yamada, Takashi Abe
    29th International Symposium on Space Technology and Science 2013年06月 口頭発表(一般)
  • Aerodynamic Heating around an Inflatable Vehicle during a Reentry Demonstration Flight by a Sounding Rocket  [通常講演]
    Yusuke Takahashi, Kazuhiko Yamada, Takashi Abe, Kojiro Suzuki
    AIAA-2013-1303 2013年03月 口頭発表(一般)
  • Numerical Evaluation of Nonequilibrium Plasma Flow in 1kW Class Arc Thruster  [通常講演]
    Minghao YU, Yusuke TAKAHASHI, Ken-ichi ABE, Hisashi KIHARA
    5th International Symposium on Advanced Plasma Science and its Applications for Nitrides and Nanomaterials 2013年01月 ポスター発表
  • Numerical Prediction of Test Flow Conditions for Low Density High Enthalpy Flow in an Expansion Tube Facility  [通常講演]
    Takanori Akahori, Katsumi Haraoka, Yusuke Takahashi, Yasunori Nagata, Kazuhiko Yamada, Takashi Abe
    AIAA-2013-1005 2013年01月 口頭発表(一般)
  • Validation of the Scale Effect for the Electrodynamic Interaction of a Magnetized Body in a Weakly-ionized Flow  [通常講演]
    Morimasa Hattori, Aseu Tezuka, Hitoshi Makino, Yasunori Nagata, Yusuke Takahashi, Takashi Abe
    AIAA-2012-2738 2012年06月 口頭発表(一般)
  • Radio Frequency Blackout Possibility for an Inflatable Reentry Vehicle  [通常講演]
    Yusuke Takahashi, Kazuhiko Yamada, Takashi Abe
    AIAA-2012-3110 2012年06月 口頭発表(一般)
  • Nonequilibrium Plasma Flow Properties in Arc-Heated Wind Tunnels  [通常講演]
    Yusuke Takahashi, Takashi Abe, Hiroki Takayanagi, Masahito Mizuno, Hisashi Kihara, Ken-ichi Abe
    AIAA-2012-1240 2012年01月 口頭発表(一般)
  • Numerical Study of Pyrolysis Gas Flow and Heat Transfer inside an Ablator  [通常講演]
    Naoya Hirata, Sohei Nozawa, Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe
    the Asian Symposium on Computational Heat Transfer and Fluid Flow 2011年09月
  • Numerical Simulation of Flow Field and Heat Transfer around HAYABUSA Reentry Capsule  [通常講演]
    Masataka Yamada, Yohei Matsuda, Naoya Hirata, Sohei Nozawa, Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe
    the 28th International Symposium on Space Technology and Science 2011年06月 口頭発表(一般)
  • Numerical Simulation of Flow Fields in Large-Scale Segmented-Type Arc Heaters  [通常講演]
    Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe
    27th Congress of the International Council of the Aeronautical Sciences 2010年09月 口頭発表(一般)
  • Numerical Investigation of Thermal Response of Ablator Exposed to Thermochemical Nonequilibrium Flow’  [通常講演]
    Tadashi Kanzaka, Sohey Nozawa, Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe
    The 6th Asian-Pacific Conference on Aerospace Technology and Science 2009年11月 口頭発表(一般)
  • Numerical Investigation of Thermochemical Nonequilibrium Flow Field in a 20kW Arc Heater Coupled with Electric Field Calculation  [通常講演]
    Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe
    26th International Symposium on Rarefied Gas Dynamics 2008年07月 口頭発表(一般)
  • Numerical Simulation of Plasma Flows in a 20kW Arc-Heated Wind Tunnel Using Multi-Temperature Model  [通常講演]
    Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe
    Third Asian-Pacific Congress on Computational Mechanics in conjunction with Eleventh International Conference on Enhancement and Promotion of Computational Methods in Engineering and Science (APCOM’07-EPMESC XI) 2007年12月 口頭発表(一般)

その他活動・業績

受賞

  • 2020年04月 文部科学省 令和2年度科学技術分野の文部科学大臣表彰 若手科学者賞
     大気再突入宇宙機の高速気流 とマルチフィジクスの研究 
    受賞者: 高橋裕介
  • 2018年04月 日本機械学会 奨励賞(研究)
     数値流体・電磁場解析による宇宙機の再突入ブラックアウト予測の研究 
    受賞者: 高橋裕介
  • 2018年03月 日本機械学会宇宙工学部門 宇宙賞
     
    受賞者: 展開型エアロシェル実験超小型衛星(EGG) チーム
  • 2016年10月 HPCI利用研究課題成果報告会 平成27年度実施課題における「京」を含むHPCI利用研究課題優秀成果賞
     「惑星大気再突入機に対する通信ブラックアウト評価ツールの構築」 
    受賞者: 高橋裕介
  • 2016年02月 一般財団法人コージェネレーションエネルギー高度利用センター 平成27年度コージェネ大賞 技術開発部門特別賞
     
    受賞者: 川崎重工業株式会社;北海道大学

教育活動情報

主要な担当授業

  • Introduction to Flight Dynamics(飛翔体工学E)
    開講年度 : 2018年
    課程区分 : 修士課程
    開講学部 : 工学院
  • 飛翔体工学特論
    開講年度 : 2018年
    課程区分 : 修士課程
    開講学部 : 工学院
  • 大学院共通授業科目(一般科目):自然科学・応用科学
    開講年度 : 2018年
    課程区分 : 修士課程
    開講学部 : 大学院共通科目
  • Introduction to Flight Dynamics(飛翔体工学E)
    開講年度 : 2018年
    課程区分 : 博士後期課程
    開講学部 : 工学院
  • 飛翔体工学特論
    開講年度 : 2018年
    課程区分 : 博士後期課程
    開講学部 : 工学院
  • 熱流体力学演習Ⅱ
    開講年度 : 2018年
    課程区分 : 学士課程
    開講学部 : 工学部
    キーワード : 蒸気、湿り空気、ガスサイクル、蒸気サイクル ナビエ・ストークス方程式、レイノルズ数、粘性摩擦抵抗、境界層、乱流、運動量・角運動量理論

大学運営

委員歴

  • 2015年04月 - 現在   日本航空宇宙学会   宇宙航行部門委員会委員
  • 2014年04月 - 2016年03月   日本機械学会流体工学部門   講習会WG委員会委員
  • 2013年04月 - 2015年03月   日本機械学会流体工学部門   広報委員会委員


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