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Takahashi Yusuke

Faculty of Engineering　Mechanical and Aerospace Engineering　Aerospace SystemsAssociate Professor

所属研究室

宇宙輸送工学研究室

計算流体工学研究室

Researcher basic information

■ Degree
  • Ph.D. in engineering, Kyushu University
■ URL
researchmap URLホームページURL■ Various IDs
Researcher number
  • 40611132
J-Global ID■ Research Keywords and Fields
Research Keyword
  • Arc-heated wind tunnel
  • Reentry vehicle
  • High enthalpy flow
Research Field
  • Frontier Technology (Aerospace Engineering, Marine and Maritime Engineering), Aerospace engineering
■ Educational Organization

Career

■ Career
Career
  • Apr. 2021 - Present
    Hokkaido University, Faculty of Engineering, Associate Professor
  • Dec. 2022 - Jan. 2023
    University of Stuttgart, Institute for Parallel and Distributed Systems, Visiting researcher, Germany
  • Apr. 2012 - Mar. 2021
    Hokkaido University, Faculty of Engineering, Assistant Professor
  • Jun. 2019 - Sep. 2019
    German Aerospace Center (DLR), Institute of Aerodynamics and Flow Technology, Supersonic and Hypersonic Technologies Department, Guest scientist, Germany
  • Apr. 2016 - Mar. 2017
    German Aerospace Center (DLR), Supersonic and Hypersonic Technologies Department of the Institute of Aerodynamics and Flow Technology, Guest scientist, Germany
  • Apr. 2011 - Mar. 2012
    Japan Aerospace Exploration Agency, 研究員
Committee Memberships
  • Apr. 2015 - Present
    日本航空宇宙学会, 宇宙航行部門委員会委員, Society
  • Apr. 2013 - Mar. 2019
    日本機械学会 計算力学技術者資格認定事業委員会, 熱流体力学分野小委員会 1級単相流 幹事, Society
  • Apr. 2015 - Mar. 2018
    日本機械学会北海道支部流体工学懇話会, 幹事, Society
  • Apr. 2014 - Mar. 2016
    日本機械学会流体工学部門, 講習会WG委員会委員, Society
  • Apr. 2013 - Mar. 2015
    日本機械学会流体工学部門, 広報委員会委員, Society

Research activity information

■ Awards
  • Apr. 2023, Hokkaido University, Distinguished Researcher
    高橋裕介
  • Mar. 2021, 北海道大学大学院工学研究院, 若手教員奨励賞
    高橋裕介
  • Apr. 2020, 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
    高橋裕介
  • Apr. 2018, The Japan Society of Mechanical Engineers, JSME Young Engineers Award
    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
    Yusuke Takahashi
  • Mar. 2018, 日本機械学会宇宙工学部門, 宇宙賞
    展開型エアロシェル実験超小型衛星(EGG) チーム
  • Oct. 2016, 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」
    高橋裕介
  • Feb. 2016, 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
    川崎重工業株式会社;北海道大学
■ Papers
  • Characteristics and modeling of dynamic instability in a thin aeroshell capsule with pitching oscillations in the transonic regime
    Hideto Takasawa; Shingo Matsuyama; Yusuke Takahashi; Kazuhiko Yamada
    Acta Astronautica, 245, 565, 575, Elsevier BV, Aug. 2026, [Peer-reviewed], [International Magazine]
    English, Scientific journal
  • Simultaneous Mitigation of Communication Blackout and Aerothermal Heating Through Film Cooling
    Takashi Miyashita; Yusuke Takahashi; Ciro Salvi; Oliver Hohn; Ali Gülhan
    AIAA Journal, 64, 6, 3116, 3126, American Institute of Aeronautics and Astronautics (AIAA), Jun. 2026, [Peer-reviewed], [Last author], ［Internationally co-authored］, [International Magazine]
    English, Scientific journal, The advancement of space transportation critically depends on addressing key challenges during atmospheric reentry, notably severe aerodynamic heating and radio frequency communication blackout caused by plasma formation. During reentry, high-velocity flight through the atmosphere induces extreme gas temperatures, which promote gas ionization, generating a plasma sheath that significantly attenuates electromagnetic waves. Therefore, this study investigates the effectiveness of gas film cooling as a simultaneous mitigation method for both aerodynamic heating and communication blackout. Experiments were performed in a large-scale arc-heated wind tunnel, producing high-enthalpy, weakly ionized flows representative of reentry conditions. A test model equipped with a gas injector and an onboard communication antenna was exposed to two freestream conditions: pure argon and an argon–nitrogen mixture. The pure argon flow produced a sufficiently high electron number density to reproduce a communication blackout. The addition of nitrogen reduces the electron number density in the plasma flow, thereby effectively suppressing communication blackout. Under pure argon flow, significant signal attenuation due to plasma was observed. Gas injection led to a measurable reduction in surface temperature and a marked improvement in signal strength. These findings demonstrate that gas injection offers a promising dual-purpose mitigation strategy, enhancing the safety and reliability of future atmospheric reentry missions.
  • Balloon Flight Demonstration for Deep Space Sample Return Capsule with Thin Aeroshell
    Hideto Takasawa; Yoichi Suenaga; Takashi Miyashita; Koshiro Hirata; Kaito Wakabayashi; Yusuke Takahashi; Yasunori Nagata; Kazuhiko Yamada
    Journal of Spacecraft and Rockets, 1, 9, American Institute of Aeronautics and Astronautics (AIAA), 31 Aug. 2025, [Peer-reviewed], [Last author]
    English, Scientific journal, A thin aeroshell capsule can decelerate from high altitude, which reduces aerodynamic heating, and can land without a parachute due to its low ballistic coefficient during entry, descent, and landing. However, the characteristics of its attitude are unclear, leading to capsule design issues. The Rubber Balloon Experiment for Reentry Capsule with Thin Aeroshell was conducted to confirm the stable flight of a capsule with a thin blunt nose at low speeds and demonstrate a low-cost balloon experiment with few constraints on the balloon launch. The capsule, with a mass of 1.56 kg and a diameter of 0.8 m, was released at an altitude of 25 km using a rubber balloon. The capsule experienced low-attitude oscillation and landed without becoming unstable. In balance with the air drag, the flowfield during flight had a maximum Mach number of 0.15 and Reynolds number of [Formula: see text], which is similar to the flowfield around an actual deep space sample return capsule descending at low speeds. The translational oscillation in the drag direction and rotational oscillations in pitch and yaw were dominant. The experiment suggested that the capsule of deep-space sample return capsule has the potential to undertake a dynamically stable flight in the low-speed region.
  • Fluid–structure interaction effects on attitude stability of an inflatable aerodecelerator
    Yosuke Fujita; Sanjoy Kumar Saha; Yusuke Takahashi; Kazuhiko Yamada
    Physics of Fluids, 37, 6, AIP Publishing, 01 Jun. 2025, [Peer-reviewed], [Last author, Corresponding author], [International Magazine]
    English, Scientific journal, As a new atmospheric-entry technology, the research and development of atmospheric-entry vehicles with flexible aeroshells has been rapidly expanding. A lightweight and large-area flexible aeroshell enables a low-ballistic coefficient of flight and an efficient aerodynamic deceleration, thereby reducing aerodynamic heating and communication blackouts. Aerodynamic forces deform flexible aeroshells, altering their aerodynamic characteristics. However, the manner in which the attitude characteristics change when the aeroshell undergoes significant shape deformation is not well understood. In this study, the attitude and aerodynamic characteristics of a flexible aeroshell were clarified using wind tunnel tests at a given angle of attack and corresponding fluid–structure interaction (FSI) analysis. The FSI analysis method is based on a partitioned coupling method for large-scale parallel computers that use open-source software. The FSI analytical model reasonably explained the aeroshell deformation and aerodynamic coefficient behavior, and its validity was confirmed by wind tunnel experiments. The shape deformation of the flexible aeroshell weakened its restoring motion, thus exhibiting attitude instability compared with those prior to deformation.
  • Communication blackout and aerodynamic heating reduction via air film for hypersonic spacecraft
    Takashi Miyashita; Yuji Sugihara; Yusuke Takahashi
    Journal of Applied Physics, 137, 17, AIP Publishing, 01 May 2025, [Peer-reviewed], [Last author], [International Magazine]
    English, Scientific journal, This study investigates the use of gas jet injection to mitigate both radio frequency blackouts and aerodynamic heating experienced by spacecraft during atmospheric reentry. The key concept behind this approach is that the injected gas forms a thin air film layer around the spacecraft. This air film acts as an insulating layer, reducing heat transfer and creating a low-plasma region, allowing electromagnetic waves to propagate through the surrounding plasma of the spacecraft. To assess the effectiveness of this method, a parametric study was conducted using computational fluid dynamics simulations on an actual reentry vehicle. The results indicate that gas injection from the vehicle’s leading edge provides a localized reduction in heat flux, while injection from the sidewall forms a more extensive protective air film along the vehicle surface, significantly reducing heat flux over a broader area. Furthermore, the formation of the air film creates a low-plasma region, facilitating the transmission of electromagnetic waves. These computational findings demonstrate that simultaneous mitigation of both heat flux and radio frequency blackouts is achievable under realistic atmospheric reentry conditions. This air film effect presents a promising solution to these two major challenges, potentially enhancing the flexibility of space transfer missions.
  • Free flight demonstration for sample return capsule with thin aeroshell using rubber balloon: RERA-4
    YOSHIO Tadayuki; YAMAMOTO Haruka; TAKANO Sota; MIYASHITA Ryo; MIKI Takahiro; MIYASHITA Takashi; TAMAI Ryota; TAKASAWA Hideto; SUENAGA Yoichi; TANNO Marie; TAKAHASHI Yusuke; NAGATA Yasunori; YAMADA Kazuhiko
    JAXA Research and Development Report, 24, 005, 19, 33, Japan Aerospace Exploration Agency (JAXA), 28 Feb. 2025, [Peer-reviewed], [Last author]
    Japanese, Scientific journal
  • Spatiotemporal mode extraction for fluid–structure interaction using mode decomposition
    Yusuke Takahashi
    Journal of Sound and Vibration, 118804, 118804, Elsevier BV, Nov. 2024, [Peer-reviewed], [Lead author, Last author, Corresponding author]
    English, Scientific journal
  • Mode decomposition to identify oscillation patterns of flexible aeroshell
    Sanjoy Kumar Saha; Yusuke Takahashi
    Physics of Fluids, 36, 11, AIP Publishing, 01 Nov. 2024, [Peer-reviewed], [Last author]
    English, Scientific journal, Flexible aeroshells, featuring deformable membrane surfaces supported by pressurized gas, offer a novel re-entry system for high-altitude deceleration during re-entry. The flexibility of structural components introduces unique challenges in predicting aerodynamic behavior, as deformations can significantly alter the flow field, affecting pressure distribution and potentially causing aerodynamic instabilities. Therefore, coupled analysis is crucial to ensure the performance reliability of inflatable aeroshells. This study investigates the unsteady aerodynamic behavior, considering structural deformation in a two-way partitioned coupled manner in transonic flow. The dominant deformation patterns are identified using dynamic mode decomposition and the greedy compressive sensing algorithm. The findings reveal that the primary deformation pattern combines axial deformation and swing oscillation. The dominant oscillation frequencies remain different from the eigenfrequencies, indicating that the aerodynamic force is the primary driving force of such oscillations. The time evolution of these dominant modes indicates purely oscillatory behavior rather than increasing or decreasing trends. These insights are critical for the design and reliability assessment of inflatable aeroshells in varying aerodynamic environments.
  • Aerostructural Analysis of a Deployable Aeroshell in Transonic Flow
    Sanjoy Kumar Saha; Yusuke Takahashi
    AIAA Journal, 1, 16, American Institute of Aeronautics and Astronautics (AIAA), 07 Oct. 2024, [Peer-reviewed], [Last author]
    English, Scientific journal, The deployable aeroshell, a contemporary reentry system, utilizes a thin flexible membrane surface sustained by pressurized gas to efficiently decelerate a reentry vehicle at high altitudes while enabling low-ballistic-coefficient flight. When an in-flight aerodynamic force is applied, the membrane structure undergoes large deformation that may affect its performance. Hence, a coupled analysis that considers the feedback effect of structural deformation is essential for accurately predicting the behavior of such reentry vehicles. In this study, a numerical framework for coupled aeroelastic analysis was constructed in a partitioned manner using open-source software to elucidate the combined effect of structural deformation and compressible flow dynamics and characterize the aerodynamic performance of reentry vehicles with inflatable structures. The results revealed that the membrane surface was deformed elastically by the aerodynamic force owing to the large difference in pressure distribution between the front and back of the aeroshell. Fluctuating behavior was observed in the aerodynamic coefficients owing to the small-amplitude oscillation of the capsule. This oscillation was induced by the large wake behind the vehicle. Several wrinkles and concave-shaped depressions formed on the membrane surface, which exhibited a circumferential movement tendency with time.
  • Atmospheric density estimation in very low Earth orbit based on nanosatellite measurement data using machine learning
    Tomoki Sakai; Yusuke Takahashi
    Aerospace Science and Technology, 153, 109418, 109418, Elsevier BV, Oct. 2024, [Peer-reviewed], [Last author]
    English, Scientific journal
  • Mitigation of reentry blackout via gas injection in arc-heating facility
    Takashi Miyashita; Yuji Sugihara; Yusuke Takahashi; Yasunori Nagata; Hisashi Kihara
    Journal of Physics D: Applied Physics, 57, 32, 325206, 325206, IOP Publishing, 20 May 2024, [Peer-reviewed], [Last author]
    English, Scientific journal, Abstract

    Communication blackouts during atmospheric reentry pose significant challenges to the safety and adaptability of spacecraft missions. This phenomenon, caused by the attenuation of electromagnetic waves by the plasma surrounding the spacecraft, disrupts communication with ground stations or orbiting satellites. Therefore, it is crucial to decrease the plasma density in the vicinity of the spacecraft to ensure an unobstructed electromagnetic wave communication path. This study proposes a methodology that involves the injection of gas from the vehicle’s wall to create an insulating layer near the surface. This thin layer maintains lower temperatures and reduced plasma density, enabling electromagnetic wave propagation without attenuation. Practical experiments were conducted in an arc-heating facility to simulate atmospheric reentry conditions. The results of the experiments provided empirical evidence of the effectiveness of the technique in mitigating communication blackout phenomena. Numerical fluid analysis within the wind tunnel chamber validated the formation of an air film layer near the experimental model owing to the injected gas. Schlieren imaging revealed distinctive jet shapes, which corroborated the findings of the numerical analysis. The wind tunnel tests that simulated atmospheric reentry environments confirmed the formation of an air film layer through gas injection, which substantiates the reduction in communication blackout. These results have the potential to improve communication reliability in space transport.
  • Static attitude stability of deep space sample return capsule with thin aeroshell
    Hideto Takasawa; Tomoya Fujii; Yusuke Takahashi; Takahiro Moriyoshi; Hiroki Takayanagi; Yasunori Nagata; Kazuhiko Yamada
    CEAS Space Journal, Springer Science and Business Media LLC, 26 Apr. 2024, [Peer-reviewed], [Last author]
    English, Scientific journal
  • Computational Study on Air Film Approach in Reentry Blackout Mitigation
    Takashi Miyashita; Hideto Takasawa; Yusuke Takahashi; Lars Steffens; Ali Gülhan
    AIAA Journal, 62, 2, 437, 448, American Institute of Aeronautics and Astronautics (AIAA), Feb. 2024, [Peer-reviewed], [Last author]
    English, Scientific journal, Communication blackouts during the atmospheric reentry phase are a significant challenge, as flight data are lost due to interruptions caused by plasma gas generated by aerodynamic heating. This study explores a novel mitigation method using an air film, a thin insulating coolant layer on the surface. The researchers successfully reduced the reentry blackout by employing a gas injection system. Through a coupled approach using computational fluid dynamics and a frequency-dependent finite-difference time-domain method, the plasma flow properties and electromagnetic propagation were analyzed around a test model in a wind tunnel in DLR (German Aerospace Center). The numerical results indicated that the injected nitrogen gas formed an insulating air film layer on the surface. The thin layer advected backward, maintaining a low temperature without ionization, and covered the object in the wake region. The electromagnetic waves propagated and reached a distant area because the electron density was low. It means that the air film layer acted as a propagation window for the telecommunication waves. Thus, communication blackouts will be avoidable because electromagnetic waves can transmit through the air-film layer. It concluded that the air film effect, developed as a thermal protection technique, is a novel mitigation scheme for reentry blackouts.
  • Free flight demonstrations for sample return capsules with thin aeroshell using rubber balloons: RERA-2 & RERA-3
    宮下岳士; 高澤秀人; 玉井亮多; 平田耕志郎; 若林海人; 吉雄忠行; 山本春佳; 丹野茉莉枝; 高橋裕介; 永田靖典; 山田和彦
    宇宙航空研究開発機構研究開発報告: 大気球研究報告, JAXA-RR-23-003, 59, 75, Feb. 2024, [Peer-reviewed], [Last author]
    Japanese, Scientific journal
  • Dynamic instability modeling on phase plane for thin aeroshell capsule with pitching motion at transonic speed
    Hideto TAKASAWA; Tomoya FUJII; Koshiro HIRATA; Takahiro MORIYOSHI; Yusuke TAKAHASHI; Yasunori NAGATA; Kazuhiko YAMADA
    Mechanical Engineering Journal, 11, 3, 24-00053, Japan Society of Mechanical Engineers, 2024, [Peer-reviewed], [Last author]
    English, Scientific journal
  • Numerical investigation of surface catalytic effect on the plasma sheath of a hypersonic re-entry capsule
    Yu Minghao; Qiu Zeyang; Yusuke Takahashi
    Physics of Fluids, 35, 5, AIP Publishing, 01 May 2023, [Peer-reviewed]
    English, Scientific journal, Radio frequency blackout indicates the communication interruption between signal monitoring sites and re-entry vehicles; it is a serious threat to the safety of astronauts and the space exploration missions. In this study, a surface catalytic model coupled with a thermochemical non-equilibrium computational fluid dynamic model is developed to study the catalytic wall effect on the plasma sheath of a hypersonic re-entry vehicle. The mechanism of the surface catalytic effect on the plasma sheath of a re-entry capsule is revealed by a comparative study. The flow-field characteristics simulated under conditions of the full-catalytic and non-catalytic walls are compared and discussed for the hypersonic atmospheric re-entry capsule at different altitudes. The chemical and physical mechanisms behind the surface catalytic effect of the re-entry capsule are analyzed. The experimental data of Radio Attenuation Measurement-C-II are used to validate the numerical model established in the present study. It is found that the numerical results simulated with the fully catalytic wall are more consistent with the experimental data. Near the capsule wall, the mole fractions of the species N, O, N+, and O+ decrease as the catalytic recombination coefficient increases. Because of the surface catalytic effect, the communication black is mitigated due to the reduction of the electron number density in the wake zone of the capsule.
  • RERA: Rubber balloon Experiment for Reentry capsule with thin Aeroshell
    Hideto Takasawa; Yoichi Suenaga; Takahashi Miyashita; Koshiro Hirata; Kaito Wakabayashi; Yusuke Takahashi; Yasunori Nagata; Kazuhiko Yamada
    JAXA Research and Development Report, JAXA-RR-22-008, 37, 50, Feb. 2023, [Peer-reviewed], [Last author]
    Japanese, Scientific journal
  • Fluid-structure interaction characteristics of inflatable reentry aeroshell at subsonic speed
    Sanjoy Kumar Saha; Junki Tobari; Yusuke Takahashi; Nobuyuki Oshima; Takahiro Moriyoshi; Kazuhiko Yamada; Ryoichi Shibata
    Aerospace Science and Technology, 133, 108112, 108112, Elsevier BV, Feb. 2023, [Peer-reviewed], [Last author]
    English, Scientific journal
  • Numerical simulation of thermochemical non-equilibrium flow-field characteristics around a hypersonic atmospheric reentry vehicle
    Minghao Yu; Zeyang Qiu; Bowen Zhong; Yusuke Takahashi
    Physics of Fluids, 34, 12, 126103, 126103, AIP Publishing, Dec. 2022, [Peer-reviewed], ［Internationally co-authored］
    English, Scientific journal, A multi-physics thermochemical non-equilibrium model is established to study the flow characteristics of the plasma sheath around an atmospheric reentry demonstrator. This model includes the tight coupling of Navier–Stokes equations, 54 chemical reactions of air, and a four-temperature model. The processes of dissociation, ionization, and the internal energy exchanges of air components were successfully simulated during aerodynamic heating of the reentry vehicle. The distributions of plasma sheath temperature, the molar fraction of air species, stagnation pressure, surface pressure, and electron number density around the reentry vehicle were obtained at different flight altitudes. Additionally, to validate the numerical model developed in this study, the flow characteristics of the Radio Attenuation Measurement-C-II (RAM-C-II) vehicle are also simulated and then compared with corresponding experimental data. They show good consistency in general. It is found that when the vehicle is at a high flight altitude, there is a strong thermochemical non-equilibrium phenomenon around the vehicle. However, the plasma sheath tends to be in local thermal equilibrium at a low flight altitude. The distance from the shock layer to the stagnation point decreases with a decrease in reentry altitude from 90 to 65 km but increases with a decrease from 65 to 40 km. The electron number density in the shock layer is maximum. The distribution of the electron number density in the wake region differs significantly at different flight altitudes.
  • Propagation Path of Radio Waves in Nonequilibrium Reentry Plasma Around a Nanosatellite With an Inflatable Aeroshell
    Yusuke Takahashi
    IEEE Transactions on Aerospace and Electronic Systems, 58, 5, 4070, 4082, Institute of Electrical and Electronics Engineers (IEEE), Oct. 2022, [Peer-reviewed], [Lead author, Last author, Corresponding author]
    English, Scientific journal
  • Trajectory reconstruction for nanosatellite in very low Earth orbit using machine learning
    Yusuke Takahashi; Masahiro Saito; Nobuyuki Oshima; Kazuhiko Yamada
    Acta Astronautica, 194, 301, 308, Elsevier BV, May 2022, [Peer-reviewed], [Lead author, Last author, Corresponding author]
    English, Scientific journal
  • Nonequilibrium Shock Layer in Large-Scale Arc-Heated Wind Tunnel
    Yusuke Takahashi; Hideto Takasawa; Kazuhiko Yamada; Takayuki Shimoda
    Journal of Physics D: Applied Physics, 55, 23, 235205, 235205, IOP Publishing, 02 Mar. 2022, [Peer-reviewed], [Lead author, Last author, Corresponding author]
    English, Scientific journal, Abstract
    An arc-heated wind tunnel is one of the most important facilities to reproduce the high-temperature environment during atmospheric entry for plasma studies and spacecraft development. However, the properties of the plasma flow cannot be determined easily, because of the complex physical phenomena, such as arc discharge and supersonic expansion, occurring inside the tunnel. The shock-layer structure should be clarified to evaluate the aerodynamic characteristics, communication conditions, and thermal- protection performance in a high-temperature environment. In this study, shock-layer spectroscopic measurements of a plasma flow in a 1 MW-class arc-heated wind tunnel were performed. The γ-band system spectra of nitric oxide (NO) molecules in the ultraviolet region were measured, and the rotational temperature was determined via spectral fitting through comparison with numerical spectra. The rotational temperature of the NO molecules in the shock layer was 6,620±350 K, whereas that in the free jet was much lower at 770±60 K. This difference is attributed to the increase in translational temperature by flow stagnation across the shock wave, followed by the increase in rotational temperature owing to energy relaxation. A computational science approach revealed the detailed structure of the flow through comparisons with the spectroscopic measurement data. The wind tunnel flow became hypersonic with high temperature and low pressure due to the expansion and acceleration at the nozzle and test chamber. Although the temperature increased across the shock wave, the chemical reaction progressed slowly owing to the low-pressure environment. The rotational temperature in the shock layer increased with the translational temperature; this agrees with the trend of the measurement results. The arc-heated flow was found to be in strong thermo- chemical nonequilibrium in the shock layer. Through this study, a detailed structure of arc-heated flow was revealed and its methodology was also proposed.
  • Multiphysics Mathematical Modeling and Flow Field Analysis of an Inflatable Membrane Aeroshell in Suborbital Reentry
    Minghao Yu; Zeyang Qiu; Bo Lv; Yusuke Takahash
    Mathematics, 10, 5, 832, 846, 2022, [Peer-reviewed]
    English, Scientific journal
  • Experimental demonstration and mechanism of mitigating reentry blackout via surface catalysis effects
    Hideto Takasawa; Yusuke Takahashi; Nobuyuki Oshima; Hisashi Kihara
    Journal of Physics D: Applied Physics, 54, 22, 225201, 225201, 08 Mar. 2021, [Peer-reviewed], [Last author]
    English, Scientific journal
  • Fluid-Structure Interaction Analysis for Martian Exploration Parafoil with Deployable Structure by Coupling Library Precice
    K. Ishida; J. Tobari; Y. Takahashi; N. Oshima; R. Shibata
    14th WCCM-ECCOMAS Congress, CIMNE, 2021, [Peer-reviewed]
    International conference proceedings
  • Flow Enthalpy of Nonequilibrium Plasma in 1 MW Arc-Heated Wind Tunnel
    Yusuke Takahashi; Naoya Enoki; Taiki Koike; Mayuko Tanaka; Kazuhiko Yamada; Takayuki Shimoda
    AIAA Journal, 59, 1, 263, 275, Jan. 2021, [Peer-reviewed], [Lead author, Corresponding author]
    English, Scientific journal
  • Aerodynamic instability of an inflatable aeroshell in suborbital re-entry
    Yusuke Takahashi; Tatsushi Ohashi; Nobuyuki Oshima; Yasunori Nagata; Kazuhiko Yamada
    Physics of Fluids, 32, 7, 075114, 075114, 01 Jul. 2020, [Peer-reviewed], [Lead author, Corresponding author]
    English, Scientific journal
  • Surface catalysis effects on mitigation of radio frequency blackout in orbital reentry
    Yusuke Takahashi, Naoya Enoki, Hideto Takasawa, Nobuyuki Oshima,
    Journal of Physics D: Applied Physics, 53, 23, 235203, 235203, Apr. 2020, [Peer-reviewed], [Lead author, Corresponding author]
    English, Scientific journal
  • Aerodynamics of inflatable nano-satellite “EGG” in low earth orbit and reentry duration
    Naoya Enoki; Yusuke Takahashi; Nobuyuki Oshima; Kazuhiko Yamada; Kojiro Suzuki
    AIP Conference Proceedings, 2132, 100002, 05 Aug. 2019, [Peer-reviewed], [Corresponding author], [International Magazine]
    English, International conference proceedings
  • Aerothermodynamic Analysis for Deformed Membrane of Inflatable Aeroshell in Orbital Reentry Mission
    Yusuke Takahashi; Taiki Koike; Nobuyuki Oshima; Kazuhiko Yamada
    Aerospace Science and Technology, 92, 858, 868, 2019, [Peer-reviewed], [Lead author, Last author, Corresponding author]
    English, Scientific journal
  • Drag Behavior of an Inflatable Reentry Vehicle in the Transonic Regime
    Yusuke Takahashi; Manabu Matsunaga; Nobuyuki Oshima; Kazuhiko Yamada
    Journal of Spacecraft and Rockets, 56, 2, 577, 585, 2019, [Peer-reviewed], [Lead author, Last author, Corresponding author]
    English, Scientific journal
  • Spectroscopic Measurement of Air Plasma Flow Generated by 10 kW Class ICP Heater
    Mayuko Tanaka; Kazuhiko Yamada; Yusuke Takahashi; Yu Minghao; Asei Tezuka
    Journal of the Japan Society for Aeronautical and Space Sciences, 67, 2, 42, 48, 2019, [Peer-reviewed]
    Japanese, Scientific journal
  • Experimental Estimation of Rear-side Heat Flux of Hayabusa Sample Return Capsule
    Yasuhisa FUKUDA; Takahiro ARAYA; Yusuke TAKAHASHI; Kazuhiko YAMADA; Jun KOYANAGI
    Koku-Uchu-Gijyutsu (Aerospace Technology Japan, the Japan Society for Aeronautical and Space Sciences), 18, 127, 131, 2019, [Peer-reviewed]
    Japanese, Scientific journal
  • Aerodynamic heating of inflatable aeroshell in orbital reentry
    Yusuke Takahashi; Kazuhiko Yamada
    Acta Astronautica, 152, 437, 448, Nov. 2018, [Peer-reviewed], [Lead author, Last author, Corresponding author]
    English, Scientific journal
  • Aerodynamic instability of flare-type membrane inflatable vehicle in suborbital reentry demonstration
    Tatsushi Ohashi; Yusuke Takahashi; Hiroshi Terashima; Nobuyuki Oshima
    Journal of Fluid Science and Technology, 13, 3, JFST0020, JFST0020, Oct. 2018, [Peer-reviewed], [Last author, Corresponding author]
    English, Scientific journal
  • Aerodynamic-heating analysis of sample-return capsule in future trojan-asteroid exploration
    Yusuke Takahashi; Kazuhiko Yamada
    Journal of Thermophysics and Heat Transfer, 32, 3, 547, 559, American Institute of Aeronautics and Astronautics Inc., 2018, [Peer-reviewed], [Lead author, Last author, Corresponding author]
    English, Scientific journal
  • Reentry blackout prediction for atmospheric reentry demonstrator mission considering uncertainty in chemical reaction rate model
    Minseok Jung; Hisashi Kihara; Ken-Ichi Abe; Yusuke Takahashi
    Physics of Plasmas, 25, 1, 013507, American Institute of Physics Inc., 01 Jan. 2018, [Peer-reviewed]
    English, Scientific journal
  • Aerodynamic Heating Analysis for Inflatable Reentry Vehicle
    高橋裕介; 松永学; 大島伸行; 山田和彦
    日本航空宇宙学会誌, 65, 12, 370, 376, Dec. 2017, [Peer-reviewed]
    Japanese, Scientific journal
  • Plasma flow modeling for Huels-type arc heater with turbulent diffusion
    Yusuke Takahashi; Burkard Esser; Lars Steffens; Ali Guelhan
    PHYSICS OF PLASMAS, 24, 12, 123509, Dec. 2017, [Peer-reviewed], [Lead author, Corresponding author], ［Internationally co-authored］
    English, Scientific journal
  • Methods for Determining Nozzle-Throat-Erosion History in Hybrid Rockets
    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, Nov. 2017, [Peer-reviewed]
    English, Scientific journal
  • Research, Development and Flight Demonstrations of Deployable Membrane Aeroshell for Atmospheric Entry System
    YAMADA Kazuhiko; SUZUKI Kojiro; ABE Takashi; AKITA Daisuke; IMAMURA Osamu; NAGATA Yasunori; TAKAHASHI Yusuke
    Aeronautical and Space Sciences Japan, 65, 11, 333, 340, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Nov. 2017, [Peer-reviewed]
    Japanese,

    展開型柔軟エアロシェルは，将来の革新的な大気圏突入システムとして期待されている．我々のグループでは，カプセル形状の本体の周りに取り付けられる円錐形状の薄膜フレアと，その外周に取り付けられたガス圧で展開し形状を維持するインフレータブルリングで構成される，薄膜フレア型の展開型柔軟エアロシェルに注目して研究開発を進めてきた．本技術に対する我々の研究開発活動の特徴は，大気球実験，観測ロケット実験，国際宇宙ステーション/「きぼう」からの超小型衛星の放出機会など，各種フライト機会を利用し，その都度，フライト実験機を開発し，実際に飛行させることで，各要素技術のフライト環境での実証や大気圏突入システムとしての機能検証を行ってきた点にある．本稿では，展開型大気圏突入機の研究開発の紹介とともに，我々がこれまでに行ってきた各種フライト試験の概要について紹介する．

  • Aerodecelerator Performance of Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry
    Yusuke Takahashi; Dongheun Ha; Nobuyuki Oshima; Kazuhiko Yamada; Takashi Abe; Kojiro Suzuki
    JOURNAL OF SPACECRAFT AND ROCKETS, 54, 5, 993, 1004, Sep. 2017, [Peer-reviewed]
    English, Scientific journal
  • Numerical simulation of plasma flows and radio-frequency blackout in atmospheric reentry demonstrator mission
    Minseok Jung; Minseok Jung; Hisashi Kihara; Hisashi Kihara; Ken Ichi Abe; Ken Ichi Abe; Yusuke Takahashi
    47th AIAA Fluid Dynamics Conference, 2017, 01 Jan. 2017, [Peer-reviewed]
  • LARGE-EDDY SIMULATION WITH A NEW FLAMELET MODEL FOR PARTIALLY PREMIXED COMBUSTION IN A GAS-TURBINE COMBUSTOR
    Keisuke Tanaka; Tomonari Sato; Nobuyuki Oshima; Jiun Kim; Yusuke Takahashi; Yasunori Iwai
    PROCEEDINGS OF THE ASME POWER CONFERENCE JOINT WITH ICOPE-17, 2017, VOL 1, 2017
    English, International conference proceedings
  • Flow-field differences and electromagnetic-field properties of air and N-2 inductively coupled plasmas
    Minghao Yu; Kazuhiko Yamada; Yusuke Takahashi; Kai Liu; Tong Zhao
    PHYSICS OF PLASMAS, 23, 12, 123523, Dec. 2016, [Peer-reviewed]
    English, Scientific journal
  • Numerical analysis on the effect of angle of attack on evaluating radio-frequency blackout in atmospheric reentry
    Minseok Jung; Hisashi Kihara; Ken-ichi Abe; Yusuke Takahashi
    JOURNAL OF THE KOREAN PHYSICAL SOCIETY, 68, 11, 1295, 1306, Jun. 2016, [Peer-reviewed]
    English, Scientific journal
  • Analysis of Radio Frequency Blackout for a Blunt-Body Capsule in Atmospheric Reentry Missions
    Yusuke Takahashi; Reo Nakasato; Nobuyuki Oshima
    Aerospace, 3, 1, 2, 2, Jan. 2016, [Peer-reviewed]
    English, Scientific journal
  • Advanced validation of CFD-FDTD combined method using highly applicable solver for reentry blackout prediction
    Yusuke Takahashi
    JOURNAL OF PHYSICS D-APPLIED PHYSICS, 49, 1, 015201, Jan. 2016, [Peer-reviewed]
    English, Scientific journal
  • Aerodynamic Heating Around Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry Demonstration Flight
    Yusuke Takahashi; Kazuhiko Yamada; Takashi Abe; Kojiro Suzuki
    JOURNAL OF SPACECRAFT AND ROCKETS, 52, 6, 1530, 1541, Nov. 2015, [Peer-reviewed]
    English, Scientific journal
  • Thermochemical Nonequilibriu.m 2D Modeling of Nitrogen Inductively Coupled Plasma Flow
    Yu Minghao; Yusuke Takahashi; Hisashi Kihara; Ken-ichi Abe; Kazuhiko Yamada; Takashi Abe; Satoshi Miyatani
    PLASMA SCIENCE & TECHNOLOGY, 17, 9, 749, 760, Sep. 2015, [Peer-reviewed]
    English, Scientific journal
  • Computation and analysis of the electron transport properties for nitrogen and air inductively-coupled plasmas
    Minghao Yu; Hisashi Kihara; Ken-ichi Abe; Yusuke Takahashi
    JOURNAL OF THE KOREAN PHYSICAL SOCIETY, 66, 12, 1833, 1840, Jun. 2015, [Peer-reviewed]
    English, Scientific journal
  • Accuracy verification of the turbulent flame les model by a methane/air burner flame
    Murase Kagenobu; Oshima Nobuyuki; Takahashi Yusuke
    ASME/JSME/KSME 2015 Joint Fluids Engineering Conference, AJKFluids 2015, 1A, American Society of Mechanical Engineers, 2015
    English, International conference proceedings
  • Numerical study of plasma flow around a reentry vehicle during atmospheric reentry with an unstructured grid solver
    Reo Nakasato; Yusuke Takahashi; Nobuyuki Oshima
    ASME/JSME/KSME 2015 Joint Fluids Engineering Conference, AJKFluids 2015, 1A, American Society of Mechanical Engineers, 2015
    English, International conference proceedings
  • Aerodynamic Simulation of Inflatable Re-Entry Vehicle Performance in Low Speed Wind Tunnel
    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, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Dec. 2014, [Peer-reviewed]
    English, Scientific journal, An inflatable re-entry vehicle is a candidate for future re-entry systems. Owing to the large area and configuration of the vehicle, it can afford a few advantages during the re-entry, descent, and landing approach, such as a decrease of aerodynamic heating and soft landing without requiring a parachute system. To investigate aerodynamic characteristics of inflatable reentry vehicle at low-Mach-number flight, wind tunnel tests were performed in JAXA Low-Speed-Wind tunnel. In this research, we investigated aerodynamic characteristics of 2 types of inflatable reentry vehicle, SMAAC and TITANS, at a low-Mach-number by using numerical simulation. Through the flow field simulation, it was indicated that the computed result of drag coefficient shows reasonable agreement with the experimental one. In the case of TITANS, the computed results showed good agreements compared with experimental results though it was confirmed that a blockage effect was observed.
  • Prediction Performance of Blackout and Plasma Attenuation in Atmospheric Reentry Demonstrator Mission
    Yusuke Takahashi; Kazuhiko Yamada; Takashi Abe
    JOURNAL OF SPACECRAFT AND ROCKETS, 51, 6, 1954, 1964, Nov. 2014, [Peer-reviewed]
    English, Scientific journal
  • Numerical Investigation of Flow Fields in Inductively Coupled Plasma Wind Tunnels
    Yu Minghao; Yusuke Takahashi; Hisashi Kihara; Ken-ichi Abe; Kazuhiko Yamada; Takashi Abe
    PLASMA SCIENCE & TECHNOLOGY, 16, 10, 930, 940, Oct. 2014, [Peer-reviewed]
    English, Scientific journal
  • Improvement of a Three-Band Radiation Model for Application to Chemical Nonequilibrium Flows
    Naoya Hirata; Masataka Yamada; Hisashi Kihara; Ken-ichi Abe; Yusuke Takahashi
    Journal of Thermophysics and Heat Trasnfer,, 28, 4, 709, 803, Oct. 2014, [Peer-reviewed]
    English, Scientific journal
  • Examination of Radio Frequency Blackout for an Inflatable Vehicle During Atmospheric Reentry
    Yusuke Takahashi; Kazuhiko Yamada; Takashi Abe
    JOURNAL OF SPACECRAFT AND ROCKETS, 51, 2, 430, 441, Mar. 2014, [Peer-reviewed]
    English, Scientific journal
  • Advanced Validation of Nonequilibrium Plasma Flow Simulation for Arc-Heated Wind Tunnels
    Yusuke Takahashi; Takashi Abe; Hiroki Takayanagi; Masahito Mizuno; Hisashi Kihara; Ken-ichi Abe
    JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER, 28, 1, 9, 17, Jan. 2014, [Peer-reviewed]
    English, Scientific journal
  • Numerical simulation of flow field around an inatable vehicle during a reentry demonstration flight
    Dongheun Ha; Yusuke Takahashi; Kazuhiko Yamada; Takashi Abe
    32nd AIAA Applied Aerodynamics Conference, American Institute of Aeronautics and Astronautics Inc., 2014
    English, International conference proceedings
  • LARGE-EDDY SIMULATION OF TRANSIENT BEHAVIOR IN A COMBUSTION FIELD FOR GAS-TURBINE ENGINE
    Yusuke Takahashi; Nobuyuki Oshima; Yasunori Iwai
    11TH WORLD CONGRESS ON COMPUTATIONAL MECHANICS; 5TH EUROPEAN CONFERENCE ON COMPUTATIONAL MECHANICS; 6TH EUROPEAN CONFERENCE ON COMPUTATIONAL FLUID DYNAMICS, VOLS V - VI, 5792, 5803, 2014
    English, International conference proceedings
  • Numerical Simulation of Nonequilibrium Inductive Plasma Flow Coupled with Electromagnetic Field Calculation
    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, [Peer-reviewed]
    English, International conference proceedings
  • Numerical prediction of test flow conditions for low density high enthalpy flow in an expansion tube facility
    Takanori Akahori; Katsumi Hiraoka; Yusuke Takahashi; Yasunori Nagata; Kazuhiko Yamada; Takashi Abe
    51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013, American Institute of Aeronautics and Astronautics Inc., 2013
    English, International conference proceedings
  • Aerodynamic heating around an inflatable vehicle during a reentry demonstration flight by a sounding rocket
    Yusuke Takahashi; Kazuhiko Yamada; Takashi Abe; Kojiro Suzuki
    AIAA Aerodynamic Decelerator Systems (ADS) Conference 2013, 2013, [Peer-reviewed]
    English, International conference proceedings
  • Improvement of Potential Drop Predictions for Plasma Wind Tunnels by Cathode Sheath
    Yusuke Takahashi; Hisashi Kihara; Ken-ichi Abe
    JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER, 26, 3, 540, 544, Jul. 2012, [Peer-reviewed]
    English, Scientific journal
  • Nonequilibrium plasma flow properties in arc-heated wind tunnels
    Yusuke Takahashi; Yusuke Takahashi; Takashi Abe; Takashi Abe; Hiroki Takayanagi; Hiroki Takayanagi; Masahito Mizuno; Masahito Mizuno; Hisashi Kihara; Hisashi Kihara; Ken Ichi Abe; Ken Ichi Abe
    50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 20 Jun. 2012, [Peer-reviewed]
  • Numerical study of pyrolysis gas flow and heat transfer inside an ablator
    N. Hirata; S. Nozawa; Y. Takahashi; H. Kihara; K. Abe
    Computational Thermal Sciences, 4, 3, 225, 242, 2012, [Peer-reviewed]
    English, Scientific journal
  • Radio frequency blackout possibility for an inflatable reentry vehicle
    Yusuke Takahashi; Kazuhiko Yamada; Takashi Abe
    42nd AIAA Fluid Dynamics Conference and Exhibit 2012, American Institute of Aeronautics and Astronautics Inc., 2012
    English, International conference proceedings
  • Turbulence and radiation behaviours in large-scale arc heaters
    Yusuke Takahashi; Hisashi Kihara; Ken-ichi Abe
    JOURNAL OF PHYSICS D-APPLIED PHYSICS, 44, 8, 085203, Mar. 2011, [Peer-reviewed], [Lead author, Corresponding author]
    English, Scientific journal
  • Numerical simulation of flow fields in large-scale segmented-type arc heaters
    Yusuke Takahashi; Hisashi Kihara; Ken Ichi Abe
    27th Congress of the International Council of the Aeronautical Sciences 2010, ICAS 2010, 2, 1470, 1479, 01 Dec. 2010, [Peer-reviewed]
  • The effects of radiative heat transfer in arc-heated nonequilibrium flow simulation
    Yusuke Takahashi; Hisashi Kihara; Ken-ichi Abe
    JOURNAL OF PHYSICS D-APPLIED PHYSICS, 43, 18, 185201, May 2010, [Peer-reviewed], [Lead author, Corresponding author]
    English, Scientific journal
  • Numerical Investigation of Nonequilibrium Plasma Flows in Constrictor- and Segmented-Type Arc Heaters
    Yusuke Takahashi; Hisashi Kihara; Ken-ichi Abe
    JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER, 24, 1, 31, 39, Jan. 2010, [Peer-reviewed], [Lead author, Corresponding author]
    English, Scientific journal
  • Numerical Investigation of Thermochemical Nonequililbrium Flow Field in a 20kW Arc Heater Coupled with Electric Field Calculation
    Yusuke Takahashi; Hisashi Kihara; Ken-ichi Abe
    RAREFIED GAS DYNAMICS, 1084, 883, 888, 2009
    English, International conference proceedings
■ Other Activities and Achievements
■ Books and other publications
  • Encyclopedia of Plasma Technology
    Yusuke Takahashi, Arc-Heated Wind Tunnel
    CRC Press, Taylor & Francis Group, Feb. 2017, 146650059X, 1728, English, [Contributor]
■ Lectures, oral presentations, etc.
  • Study on Mitigation of Reentry Blackout by Surface Catalysis Effects in Arc-Heated Wind Tunnel
    Hideto Takasawa; Yusuke Takahashi; Nobuyuki Oshima; Hisashi Kihara
    Aerospace Europe Conference 2020,, Feb. 2020, English, Oral presentation
    25 Feb. 2020 - 28 Feb. 2020, Bordeaux, France
  • 再突入ブラックアウト低減化に向けた数値的研究
    高橋裕介
    日本学術会議第9回計算力学シンポジウム, 11 Dec. 2019, Japanese, Invited oral presentation
    11 Dec. 2019 - 11 Dec. 2019, [Invited]
  • Numerical Analysis of Aerodynamic Instability for HAYABUSA Type Reentry Capsule
    Toru TSURUMOTO; Yusuke TAKAHASHI; Hiroshi TERASHIMA; Nobuyuki OSHIMA
    8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS), 01 Jul. 2019, English, Oral presentation
    01 Jul. 2019 - 04 Jul. 2019, Madrid, Spain
  • Aerodynamics of Inflatable Nano-Satellite “EGG” in Low Earth Orbit and Reentry Duration
    Naoya Enoki; Yusuke Takahashi; Nobuyuki Oshima; Kazuhiko Yamada; Kojiro Suzuki
    31st Internal Symposium on Rarefied Gas Dynamics, 23 Jul. 2018, English, Oral presentation
    [International presentation]
  • 大気再突入時における宇宙機の空力・空力加熱について
    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, 07 Mar. 2018, Japanese, Invited oral presentation
    07 Mar. 2018 - 07 Mar. 2018, [Invited]
  • Aerodynamic heating prediction of flare-type membrane inflatable reentry vehicle from low earth orbit
    Taiki Koike; Yusuke Takahashi; Nobuyuki Oshima; Kazuhiko Yamada
    AIAA Atmospheric Flight Mechanics Conference, 2018, 2018, American Institute of Aeronautics and Astronautics Inc, AIAA, English
    2018 - 2018, Aerodynamic heating around a flare-type membrane inflatable vehicle during Earth atmospheric reentry was investigated using numerical simulation approach. This vehicle, which is mainly composed of the capsule, membrane aeroshell and inflatable torus, has been developed by the Membrane Aeroshell for Atmospheric-entry Capsule (MAAC) group as a one of the innovative reentry systems. Analysis solver for reentry flows around the vehicle was RG-FaSTAR, which is a branch version of JAXA fast aerodynamic routine (FaSTAR). In addition, structure analysis solver also was used for membrane deformation in a loosely-coupled manner with the flow field. In the present research, the effects of angle of attack (AoA) and membrane aeroshell deformation on aerodynamic heating were investigated. The numerical results showed that heat flux distribution drastically varies with the increase in AoA because of changes of flow field, and heat flux value at the stagnation point for case of AoA of 40 degree was 3.09 times as high as that for 0 degree. Moreover, the deformed shapes for case of AoA of 0 and 40 degrees were calculated in the way which the pressure distributions obtained using initial (undeformed) shape were given as the aerodynamic force. The difference of heat fluxes between the deformed and initial shapes on the head capsule part was remarkable as 188.8% for case of AoA of 0 degree. On the other hand, it was indicated that membrane deformation for case of AoA of 40 degree insignificantly affects the peak heat flux value on the inflatable torus such as the case of the AoA of 0 degree.
  • Aerodynamic Heating Prediction of Flare-type Membrane Inflatable Reentry Vehicle from Low Earth Orbit
    Taiki Koike; Yusuke Takahashi; Nobuyuki Oshima; Kazuhiko Yamada
    2018 AIAA Atmospheric Flight Mechanics Conference, AIAA SciTech Forum, Jan. 2018, English, Oral presentation
    [International presentation]
  • Aerodynamic Instability of Flare-type Membrane Inflatable Vehicle in Suborbital Reentry Demonstration
    Tatsushi OHASHI; Manabu MATSUNAGA; Yusuke TAKAHASHI; Hiroshi TERASHIMA; Nobuyuki OSHIMA
    The Ninth JSME-KSME Thermal and Fluids Engineering Conference (TFEC9), 27 Oct. 2017, English, Oral presentation
    [International presentation]
  • Prediction of electromagnetic waves around an inflatable reentry vehicle in an atmospheric reentry mission
    Naoya ENOKI; Manabu MATSUNAGA; Yusuke TAKAHASHI; Hiroshi TERASHIMA; Nobuyuki OSHIMA; Kazuhiko YAMADA; Kojiro SUZUKI
    The Ninth JSME-KSME Thermal and Fluids Engineering Conference (TFEC9), 27 Oct. 2017, English, Oral presentation
    [International presentation]
  • Large-Eddy Simulation with a New Flamelet Model for Partially Premixed Combustion in a Gas-Turbine Combustor
    Keisuke Tanaka; Tomonari Sato; Nobuyuki Oshima; Jiun Kim; Yusuke Takahashi; Yasunori Iwai
    the ASME 2017 Power and Energy Conference, 26 Jun. 2017, English, Oral presentation
    [International presentation]
  • Numerical Simulation of Plasma Flows and Radio-Frequency Blackout in Atmospheric Reentry Demonstrator Mission
    Minseok Jung; Hisashi Kihara; Ken-ichi Abe; Yusuke Takahashi
    47th AIAA Fluid Dynamics Conference, AIAA AVIATION Forum, 05 Jun. 2017, English, Oral presentation
    [International presentation]
  • Aerodynamic Heating Prediction of an Inflatable Reentry Vehicle in a Hypersonic Wind Tunnel
    Manabu Matsunaga; Yusuke Takahashi; Nobuyuki Oshima; Kazuhiko Yamada
    55th AIAA Aerospace Sciences Meeting, 09 Jan. 2017, English, Oral presentation
    [International presentation]
  • Aerodynamic heating prediction of an inflatable reentry vehicle in a hypersonic wind tunnel
    Manabu Matsunaga; Yusuke Takahashi; Nobuyuki Oshima; Kazuhiko Yamada
    AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting, 2017, American Institute of Aeronautics and Astronautics Inc., English
    2017 - 2017, Aerodynamic heating around an inflatable reentry vehicle was investigated using hypersonic wind tunnel and numerical approach. The inflatable reentry vehicle is mainly composed of the capsule, membrane aeroshell (rigid in the wind tunnel), and inflatable torus. Basic configuration of the reentry vehicle (HWT-MAAC) is a scaled-down model of SMAAC, which was used in demonstration mission with JAXA / ISAS S-310-41 sounding rocket. Spherical cap of the SMAAC model was replaced by blunt top. Freestream condition of Mach number of 10, reservoir pressure of 2.5 MPa, and reservoir temperature of 950 K was used in the hypersonic wind tunnel test. Heat flux distribution on the surface and density gradient around the HWT-MAAC were measured by infrared thermography and Schliren photograph techniques, respectively. It was found that heat flux distribution widely varies according to angle of attack of the vehicle and a recirculation region near the membrane aeroshell section of the vehicle can appear at high angle of attack. Flow field was also numerically simulated with computational fluid dynamics approach. Analysis solver used here in was RG-FaSTAR, which is a version of JAXA fast aerodynamic routine (FaSTAR). Structures of shock layer and expansion region around HWT-MAAC was discussed through the analysis approach and the wind tunnel results.
  • NUMERICAL INVESTIGATION OF ABLATION EFFECT ON AERODYNAMIC HEATING FOR HIGH VELOCITY REENTRY CAPSULE
    Manabu Matsunaga; Takahiro Sasaki; Yusuke Takahashi; Nobuyuki Oshima
    The 27th International Symposium on Transport Phenomena (ISTP27), 20 Sep. 2016, English, Oral presentation
    [International presentation]
  • NUMERICAL ANALYSIS OF RADIO FREQUENCY BLACKOUT FOR ATMOSPHERIC REENTRY VEHICLE USING CFD-CEM COMBINED METHOD
    Yusuke Takahashi; Reo Nakasato; Nobuyuki Oshima
    VII European Congress on Computational Methods in Applied Sciences and Engineering (ECCOMAS Congress 2016), 05 Jun. 2016, English, Oral presentation
    Crete Island, Greece, [International presentation]
  • Numerical analysis of radio frequency blackout for atmospheric reentry vehicle using CFD-CEM combined method
    Yusuke Takahashi; Reo Nakasato; Nobuyuki Oshima
    ECCOMAS Congress 2016 - Proceedings of the 7th European Congress on Computational Methods in Applied Sciences and Engineering, 2016, National Technical University of Athens, English
    2016 - 2016, Numerical simulations of electromagnetic waves around the atmospheric reentry demonstrator (ARD) of the European Space Agency (ESA) in an atmospheric reentry mission were conducted with a combined method of computational fluid dynamics (CFD) and computational electromagnetics (CEM). During the reentry mission, radio frequency blackout and plasma attenuation of radio waves in communications with a data-relay satellite were observed. Cut-off of waves propagation was caused by highly dense plasma formed by a strong shock wave formed in front of the vehicle due to orbital speed. In this study, the physical properties of the plasma flow in the shock layer and wake region of the ESA ARD were obtained using a high-enthalpy flow solver applicable unstructured grids. Moreover, electromagnetic waves were calculated using a frequency-dependent finite-difference time-domain method using the plasma properties. The present analysis model was validated based on experimental flight data of ESA ARD. Comparisons of the measured and predicted results showed good agreements. Attenuation and reflection by reentry plasma were clarified in detail using the present model. It was suggested that the analysis model could be an effective tool for investigating radio frequency blackout and plasma attenuation in radio wave communication. Behaviors of plasma and electromagnetic waves around ESA ARD for several altitudes were investigated using the proposed model in detail.
  • Development of Analysis Tools for Space Vehicle in Atmospheric Reentry Mission
    Yusuke Takahashi; Nobuyuki Oshima
    Korea-Japan CFD Workshop 2015, 16 Dec. 2015, English, Invited oral presentation
    [Invited], [International presentation]
  • Numerical Investigation of Turbulent Combustion Flow in Industrial Combustor with Flamelet Approach
    Tenshi Sasaki; Yusuke Takahashi; Nobuyuki Oshima; Yasunori Iwai
    International Conference on Power Engineering-15 (ICOPE-15), 30 Nov. 2015, English, Oral presentation
    Yokohama, Japan, [International presentation]
  • Accuracy Verification of the Turbulent Flame LES Model by a Methane/Air Burner Flame
    Kagenobu Murase; Nobuyuki Oshima; Yusuke Takahashi
    ASME-JSME-KSME Joint Fluids Engineering Conference 2015, 26 Jul. 2015, English, Oral presentation
    Seoul, Korea, [International presentation]
  • Aerodynamic Simulation of Closed-Canopy-Type Parafoil for Martian Exploration Mission
    Daiki Harada; Yusuke Takahashi; Nobuyuki Oshima; Kazuhiko Yamada
    ASME-JSME-KSME Joint Fluids Engineering Conference 2015, 26 Jul. 2015, English, Oral presentation
    Seoul, Korea, [International presentation]
  • Numerical Study of Plasma Flow around a Reentry Vehicle during Atmospheric Reentry with an Unstructured Grid Solver
    Reo Nakasato; Yusuke Takahashi; Nobuyuki Oshima
    ASME-JSME-KSME Joint Fluids Engineering Conference 2015, 26 Jul. 2015, English, Oral presentation
    Seoul, Korea, [International presentation]
  • Large-Eddy Simulation of Transient Behavior in a Combustion Field for Gas-Turbine Engine
    Yusuke Takahashi; Nobuyuki Oshima; Yasunori Iwai
    ytakahashi@eng.hokudai.ac.jp, 20 Jul. 2014, English, Oral presentation
    [International presentation]
  • Numerical Simulation of Flow Field around an Inflatable Vehicle during a Reentry Demonstration Flight
    Dongheun Ha; Yusuke Takahashi; Kazuhiko Yamada; Takashi Abe
    AIAA-2014-3283, 16 Jun. 2014, English, Oral presentation
    [International presentation]
  • Numerical Investigation of Flow Fields in Inductively Coupled Plasma Wind Tunnel
    Minghao Yu; Yusuke Takahashi; Hisashi Kihara; Ken-ichi Abe; Kazuhiko Yamada; Takashi Abe
    4th Asian Symposium on Computational Heat Transfer and Fluid Flow, 03 Jun. 2013, English, Oral presentation
    [International presentation]
  • Aerodynamic Simulation of an Inflatable Re-Entry Vehicle Performance in Low Speed Wind Tunnel
    Dongheun Ha; Yusuke Takahashi; Kazuhiko Yamada; Takashi Abe
    29th International Symposium on Space Technology and Science, 02 Jun. 2013, English, Oral presentation
    [Domestic Conference]
  • Aerodynamic Heating around an Inflatable Vehicle during a Reentry Demonstration Flight by a Sounding Rocket
    Yusuke Takahashi; Kazuhiko Yamada; Takashi Abe; Kojiro Suzuki
    AIAA-2013-1303, 25 Mar. 2013, English, Oral presentation
    [International presentation]
  • Numerical Evaluation of Nonequilibrium Plasma Flow in 1kW Class Arc Thruster
    Minghao YU; Yusuke TAKAHASHI; Ken-ichi ABE; Hisashi KIHARA
    5th International Symposium on Advanced Plasma Science and its Applications for Nitrides and Nanomaterials, 28 Jan. 2013, English, Poster presentation
    [International presentation]
  • Numerical Prediction of Test Flow Conditions for Low Density High Enthalpy Flow in an Expansion Tube Facility
    Takanori Akahori; Katsumi Haraoka; Yusuke Takahashi; Yasunori Nagata; Kazuhiko Yamada; Takashi Abe
    AIAA-2013-1005, 07 Jan. 2013, English, Oral presentation
    [International presentation]
  • Validation of the Scale Effect for the Electrodynamic Interaction of a Magnetized Body in a Weakly-ionized Flow
    Morimasa Hattori; Aseu Tezuka; Hitoshi Makino; Yasunori Nagata; Yusuke Takahashi; Takashi Abe
    AIAA-2012-2738, 25 Jun. 2012, English, Oral presentation
    [International presentation]
  • Radio Frequency Blackout Possibility for an Inflatable Reentry Vehicle
    Yusuke Takahashi; Kazuhiko Yamada; Takashi Abe
    AIAA-2012-3110, 25 Jun. 2012, English, Oral presentation
    [International presentation]
  • Nonequilibrium Plasma Flow Properties in Arc-Heated Wind Tunnels
    Yusuke Takahashi; Takashi Abe; Hiroki Takayanagi; Masahito Mizuno; Hisashi Kihara; Ken-ichi Abe
    AIAA-2012-1240, 09 Jan. 2012, English, Oral presentation
    [International presentation]
  • Numerical Study of Pyrolysis Gas Flow and Heat Transfer inside an Ablator
    Naoya Hirata; Sohei Nozawa; Yusuke Takahashi; Hisashi Kihara; Ken-ichi Abe
    the Asian Symposium on Computational Heat Transfer and Fluid Flow, Sep. 2011, English
    [International presentation]
  • Numerical Simulation of Flow Field and Heat Transfer around HAYABUSA Reentry Capsule
    Masataka Yamada; Yohei Matsuda; Naoya Hirata; Sohei Nozawa; Yusuke Takahashi; Hisashi Kihara; Ken-ichi Abe
    the 28th International Symposium on Space Technology and Science, 05 Jun. 2011, English, Oral presentation
    [International presentation]
  • Numerical Simulation of Flow Fields in Large-Scale Segmented-Type Arc Heaters
    Yusuke Takahashi; Hisashi Kihara; Ken-ichi Abe
    27th Congress of the International Council of the Aeronautical Sciences, 19 Sep. 2010, English, Oral presentation
    [International presentation]
  • Numerical Investigation of Thermal Response of Ablator Exposed to Thermochemical Nonequilibrium Flow’
    Tadashi Kanzaka; Sohey Nozawa; Yusuke Takahashi; Hisashi Kihara; Ken-ichi Abe
    The 6th Asian-Pacific Conference on Aerospace Technology and Science, 15 Nov. 2009, English, Oral presentation
    [International presentation]
  • Numerical Investigation of Thermochemical Nonequilibrium Flow Field in a 20kW Arc Heater Coupled with Electric Field Calculation
    Yusuke Takahashi; Hisashi Kihara; Ken-ichi Abe
    26th International Symposium on Rarefied Gas Dynamics, 21 Jul. 2008, English, Oral presentation
    [International presentation]
  • Numerical Simulation of Plasma Flows in a 20kW Arc-Heated Wind Tunnel Using Multi-Temperature Model
    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), 03 Dec. 2007, English, Oral presentation
    [International presentation]
■ Syllabus
  • 流体工学特論, 2024年, 修士課程, 工学院
  • 大学院共通授業科目（一般科目）：自然科学・応用科学, 2024年, 修士課程, 大学院共通科目
  • 大気突入機設計特論, 2024年, 修士課程, 工学院
  • 宇宙探査工学特論, 2024年, 修士課程, 工学院
  • 流体工学特論, 2024年, 博士後期課程, 工学院
  • 大気突入機設計特論, 2024年, 博士後期課程, 工学院
  • 宇宙探査工学特論, 2024年, 博士後期課程, 工学院
  • 計測工学実験, 2024年, 学士課程, 工学部
  • 機械工学概論, 2024年, 学士課程, 工学部
■ Research Themes
  • Fluid-structure interaction in dynamic attitude instability of inflatable aeroshells
    Grants-in-Aid for Scientific Research
    01 Apr. 2024 - 31 Mar. 2028
    高橋 裕介; 山田 和彦; 永田 靖典
    Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (B), Hokkaido University, 24K01072
  • Study on the drag modulation aerocapture by a jettison of the inflatable and flexible aeroshell and flight demonstration using a sounding rocket.
    Grants-in-Aid for Scientific Research
    01 Apr. 2023 - 31 Mar. 2027
    山田 和彦; 永田 靖典; 高橋 裕介; 中尾 達郎; 高柳 大樹; 佐藤 泰貴
    Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (A), Japan Aerospace EXploration Agency, 23H00212
  • 植物空力予測のためのデジタルプラットフォームの構築
    2025年度 学際大規模情報基盤共同利用・共同研究拠点(JHPCN)公募型共同研究課題
    Apr. 2025 - Mar. 2026
    高橋裕介; 武田量; 中島大賢; 友部遼; 前田将輝
    一般財団法人 高度情報科学技術研究機構, 北海道大学, jh250024
  • 植物空力予測のためのデジタルプラットフォームの構築
    2024年度 学際大規模情報基盤共同利用・共同研究拠点(JHPCN)公募型共同研究課題
    Apr. 2024 - Mar. 2025
    高橋裕介; 武田量; 中島大賢; 友部遼; 前田将輝; Sanjoy Kumar Saha
    一般財団法人 高度情報科学技術研究機構, 北海道大学, jh240047
  • 流体-構造連成解析を基にした大動脈解離シミュレーション手法の発展
    2024年度 学際大規模情報基盤共同利用・共同研究拠点(JHPCN)公募型共同研究課題
    Apr. 2024 - Mar. 2025
    武田量; 佐々木克彦; 大島伸行; 横山博一; 黒田明慈; 柴田良一; 高橋裕介; 髙嶋英厳; 李辰宇
    一般財団法人 高度情報科学技術研究機構, 北海道大学, jh240082
  • Research on Advanced Applications of Deployable Aeroshell Technology to Realize Ultra-Small Planetary Probes
    Grants-in-Aid for Scientific Research
    01 Apr. 2020 - 31 Mar. 2023
    山田 和彦; 永田 靖典; 高橋 裕介; 佐藤 泰貴
    本研究課題は、新しい大気圏突入技術として注目されている展開型柔軟エアロシェル技術をさらに進化させて、新たな応用範囲を切り開くことを目的としている。特に、１）大気圏突入中に展開エアロシェルを切り離すことで、探査機を惑星周回軌道投入を実現できる抗力変調型のエアロキャプチャ技術と、２）超軽量で、シンプルかつロバストな展開型エアロシェルが実現できる可能性があるSMA（形状記憶合金）型の展開エアロシェル技術に取り組んでいる。
    2021年度の最も重要な成果は2021年12月に実施した極超音速風洞試験である。上記の1),2)の両テーマともに、2020年度に実施した極超音速風洞試験の結果を踏まえて改良した模型や試験システムを用いて、JAXA調布のΦ1.27m極超音速風洞にて風洞試験を実施した。1)の抗力変調型のエアロキャプチャに関しては、６分力測定、及び、画像計測系を改善し、エアロシェル分離時の挙動をより詳細に測定することに成功した。また、エアロシェルサイズを変更した実験を行い、2020年度の成果と併せて、エアロシェル形状の影響についても知見を取得できた。2)のSMA型エアロシェルについては、2020年度の試験時の課題であったフラッタ現象は、模型を改良することで回避でき、極超音速気流中での空力加熱によるSMA型エアロシェルの完全受動展開実験に成功した。展開中の流れ場の可視化、６分力測定、温度履歴の測定を実施し、模型形状と展開挙動の関係や空力特性を取得することができた。
    それと平行して、抗力変調型エアロキャプチャに関しては、火星以外の天体（金星）への適用について、軌道解析による評価を行った。また、FSI(Fluid-structure Interaction)解析による柔軟エアロシェルと高速流体の連成解析ツールの構築も進め、これらの現象をより深く理解するための準備を整えた。
    Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (B), Japan Aerospace EXploration Agency, 20H02360
  • Evaluation of Aortic Dissections and Treatment Methods using Numerical Simulation
    FY 2022 Joint Usage/Research Center for Interdisciplinary Large-scale Information Infrastructures (JHPCN)
    Apr. 2022 - Mar. 2023
    武田量; 佐々木克彦; 大島伸行; 横山博一; 黒田明慈; 柴田良一; 高橋裕介; 髙嶋英厳; 李辰宇
    Research Organization for Information Science and Technology, Hokkaido University, jh220026
  • 大型プラズマ風洞を用いた再突入ブラックアウト低減化研究の深化と加速
    科学研究費助成事業
    2018 - 2022
    高橋 裕介
    大気再突入時に高温プラズマに包まれた宇宙機が、地上局やデータ中継衛星との通信途絶現象（通信ブラックアウト）に陥ることがある。通信ブラックアウト低減化は着地着水点の高精度予測や再突入中のデータ送受信の上で重要な課題である。これまで磁場印加や、柔軟構造再突入機、テラヘルツ波など様々な低減化手法が提案されている。いま課題実施者の研究グループでは、表面触媒性を用いた宇宙機後流プラズマ密度低下を利用することによる新しい通信ブラックアウト低減を提案している。ここでは表面効果による通信ブラックアウト低減化メカニズムおよび低減化技術の指針を見出すことを目的とする。
    再突入機近傍のプラズマ諸量分布や電磁波挙動の正確な予測が難しく、通信ブラックアウト低減に繋がる知見の探索が困難な状況であった。この問題を緩和するために、再突入時における宇宙機近傍の電磁波挙動を明らかにすることは有効である。本課題実施者は、これまでプラズマ流解析・電磁波解析ソフトウェアを開発し、再突入時における宇宙機近傍の電磁波解析を明らかにしてきた。ここではそれをコア技術として、大型風洞による低減化実証と合わせて研究を推進する。
    昨年度に引き続き本年度でもドイツ航空宇宙センター（DLR）に滞在し通信ブラックアウト低減化研究を実施する予定だったが、新型コロナウイルス感染症拡大防止方策に伴う海外移動制限から今年度も残念ながら断念した。一方でDLR研究者との議論は継続しつつ、現所属機関（北海道大学）において遂行可能な低減化研究の実施を行った。それはJAXAプラズマ風洞における実証試験とスーパーコンピューター富岳などを用いた大規模数値計算である。主にはこれら２つのアプローチを用いて従来課題の低減化手法の研究を行うとともに、新しい低減化技術の実験的・数値的実証も実施した。
    日本学術振興会, 国際共同研究加速基金(国際共同研究強化), 北海道大学, 17KK0123
  • Study on Reduction of Reentry Blackout by Surface Catalysis Effect
    Grants-in-Aid for Scientific Research
    01 Apr. 2017 - 31 Mar. 2020
    Takahashi Yusuke
    The radio frequency (RF) blackout for telecommunications between a reentry vehicle and a ground station hinders the accurate prediction of landing sites and increases the recovery cost. A mitigation method of RF blackout has been demanded. In this study, I proposed and demonstrated the new mitigation method using the surface catalysis effects with numerical simulation approach and wind tunnel experiments. The communication situation in reentry plasma was experimentally reproduced by 1 MW arc-heated wind tunnel, which generates high-temperature flows on the ground. Comparative tests were performed by two test models with high and low catalysis material of surfaces. The results indicated that the test model having high catalysis improves the communication situation, that is, mitigation of RF blackout. In addition, the mechanism to mitigating the RF blackout was clarified by the use of numerical analysis.
    Japan Society for the Promotion of Science, Grant-in-Aid for Young Scientists (B), Hokkaido University, 17K14871
  • Study on behavior of a spacecraft with membrane aeroshell in super low earth orbit and flight demonstration using a nanosatellite.
    Grants-in-Aid for Scientific Research
    01 Apr. 2015 - 31 Mar. 2018
    YAMADA Kazuhiko; SUZUKI Kojiro; IMAMURA Osamu; AKITA Daisuke; ISHIMURA Kosei; NAKASHINO Kyoichi
    In this study, the behavior of a spacecraft with low-mass and large membrane aeroshell in super low earth orbit is measured in real flight using the nanosatellite EGG. The group of attitude sensors including inertial sensor, optical sensor and faraday cup sensors which can be installed in nanosatellite EGG was developed. In EGG’s flight operation, we acquired a lot of valuable flight data related to attitude motion and orbit change of a spacecraft with a membrane aeroshell. For example, an orbit change history of EGG by the aerodynamic force acting on the membrane aeroshell in rarefied flow was observed continually. These flight data are expected to be useful for the development of an important technology for nano-satellite, that is, an orbit collapse technology to prevent from becoming space debris.
    Japan Society for the Promotion of Science, Grant-in-Aid for Scientific Research (B), Japan Aerospace EXploration Agency, 15H04205
  • A Study on Radio Frequency Blackout of Planetary Atmospheric Reentry Vehicle
    Grants-in-Aid for Scientific Research
    01 Apr. 2014 - 31 Mar. 2016
    Takahashi Yusuke
    An analysis model of plasma flow and electromagnetic waves around a reentry vehicle for radio frequency blackout prediction was developed. The plasma flow properties 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 nonequilibrium flow. To predict the electromagnetic waves in plasma layer, a frequency-dependent finite-difference time-domain method was used. The combined model was validated based on experimental results in atmospheric reentry missions. The prediction performance of the combined model was evaluated with profiles and peak values of the electron number density. The signal losses measured during communication were directly compared with the predicted results. Based on the study, it is suggested that the analysis model could be an effective tool for investigating radio frequency blackout and plasma attenuation in radio wave communication.
    Japan Society for the Promotion of Science, Grant-in-Aid for Young Scientists (B), Hokkaido University, 26820366
  • A study of plasma flow field around dielectric barrier discharge plasma actuator for high velocity flow condition
    Grants-in-Aid for Scientific Research
    2011 - 2012
    TAKAHASHI Yusuke
    Final goal of the present research is to develop a high-performance plasma actuator which is applicable for a condition of high-velocity flow. In the present study, to describe plasma flow behavior and potential drop by cathode sheath, numerical simulation models of plasma flow generated by dielectric barrier discharge plasma actuator and plasma near an electrode has been suggested and developed.
    Japan Society for the Promotion of Science, Grant-in-Aid for Research Activity Start-up, 23860077
  • アーク加熱風洞を用いた高性能アブレータ開発に関する基礎研究
    科学研究費助成事業
    2009 - 2011
    高橋 裕介
    本研究の目的を,再突入時の高温環境を模擬できるアーク加熱風洞を用いてアブレータ内部現象の定量的な調査を進めるとともに,軽量で耐熱性に優れるアブレータ材料とその形状モデルの指針を見出すことに設定し,本年度における研究を実施した.これまでの成果として,九州大学20kWアーク加熱風洞の加熱部における幅射熱輸送の役割について数値解析を用いて定量的に明らかにした.さらに,JAXA 750kWアーク加熱風洞や,NASA20 MW Aerodynamic Heating Facility,NASA60 MW Interaction Heating Facilityなど,多様な大型アーク加熱風洞に対して,加熱部における乱流・幅射熱輸送の挙動を数値的に調査し,その挙動を明らかにする成果を上げた.ただし,本解析モデルを用いた解析結果は,実験直に比べてアーク電圧を過少予測する傾向にあることがわかった.その理由のひとつとして,電極近傍におけるシースを考慮していなかったことが挙げられる.したがって,アーク加熱風洞の電極近傍におけるシースモデルを提案し,電圧降下及びアーク電圧の評価を行った.
    また,軽量アブレータが20kW及び750kWアーク加熱気流にさらされる条件下において,内部の熱分解ガス流動を考慮した内部熱応答解析モデルおよび周囲の高温気体との連成解析モデルの構築を行い,アブレータ熱応答解析モデルの高精度化を行った.解析結果と実験結果は良好な一致を示し,より高精度なアブレータ熱応答解析コードが開発された.
    本研究を通して開発されたアーク加熱気流解析コード及びアブレータ熱応答解析コードによって,多様な風洞気流の諸量分布を提供することや,アブレータ内部の現象を定量的に調査することが可能になった.したがって,アーク加熱風洞を用いた様々な耐熱材料試験や開発を進める上で,これらは有効なツールになると考えられる.
    日本学術振興会, 特別研究員奨励費, 九州大学, 09J01898
■ Academic and Social Contribution Activities/Other
Others
  • Apr. 2021 - Apr. 2021
    Reviewer Awards (Plasma Science and Technology 2020)
    https://publishingsupport.iopscience.iop.org/questions/plasma-science-and-technology-2020-reviewer-awards/