Updated on 2024/05/14

 
KITAGAWA Koki
 
Scopus Paper Info  
Total Paper Count: 0  Total Citation Count: 0  h-index: 8

Citation count denotes the number of citations in papers published for a particular year.

Affiliation
Faculty of Engineering Department of Space Systems Engineering
Job
Associate Professor
E-mail
メールアドレス
Laboratory
1-1 Sensui-cho, Tobata-ku, Kitakyushu-shi, Fukuoka
Phone
+81-93-884-3148
External link

Research Interests

  • Propulsion Engineering

  • Combustion

  • Energetic Materials

  • LASER

  • Rocket Propulsion

  • Hybrid Rocket

  • Rocket

Research Areas

  • Manufacturing Technology (Mechanical Engineering, Electrical and Electronic Engineering, Chemical Engineering) / Thermal engineering

  • Manufacturing Technology (Mechanical Engineering, Electrical and Electronic Engineering, Chemical Engineering) / Fluid engineering

  • Frontier Technology (Aerospace Engineering, Marine and Maritime Engineering) / Aerospace engineering

Degree

  • Tokyo Metropolitan Institute of Technology  -  Doctor of Engineering   2007.09

Biography in Kyutech

  • 2020.04
     

    Kyushu Institute of Technology   Faculty of Engineering   Department of Space Systems Engineering   Associate Professor  

Biography before Kyutech

  • 2010.01 - 2020.03   宇宙航空研究開発機構   宇宙科学研究所宇宙飛翔工学研究系   助教   Japan

  • 2013.12 - 2020.03   東京大学大学院   工学系研究科   助教   Japan

  • 2010.04 - 2013.11   The Graduate University for Advanced Studies   Assistant Professor   Japan

Academic Society Memberships

  • 2014.04   ISTS(International Symposium on Space Technology and Science) Space Transportationセッション小委員会委員   Japan

  • 2011.04   日本航空宇宙学会宇宙航行部門委員   Japan

  • 2010.01 - 2018.03   ハイブリッドロケット研究ワーキンググループ   Japan

  • 2001.04   日本航空宇宙学会   Japan

  • 2000.04   アメリカ航空宇宙学会(AIAA)   United States

Research Career

  • 火薬のレーザ点火の研究

    レーザ点火

    研究期間: 2018.04  - 

  • 固体ロケット推進薬の研究

    固体推進薬

    研究期間: 2010.01  - 

  • ハイブリッドロケット用液体酸素気化の研究

    液体酸素気

    研究期間: 2002.04  - 

  • 酸化剤流旋回型(SOFT)ハイブリッドロケットの研究

    ハイブリッドロケット

    研究期間: 2000.04  - 

Papers

  • Evaluation of Radiative Heat-Transfer Effect on Paraffin-Wax Regression Rate in Hybrid Rocket Reviewed International journal

    Naka G., Carmicino C., Messineo J., Kitagawa K., Shimada T.

    Journal of Propulsion and Power   39 ( 2 )   258 - 273   2023.03

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    Language:English   Publishing type:Research paper (scientific journal)

    DOI: 10.2514/1.B38728

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  • Function Test of Experimental System to Obtain Laser Ignition Characteristics of Low-Temperature Boron/Potassium Nitrate Reviewed International journal

    MATSUI Kohei, MATSUURA Yoshiki, TOKUDOME Shinichiro, KITAGAWA Koki

    Journal of Evolving Space Activities ( International Symposium on Space Technology and Science )   1 ( 0 )   n/a   2023.01

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    <p>In order to use laser ignition systems for solid rocket motors operating in deep space environments, it is necessary to elucidate the laser ignition characteristics of the ignition charge in low-temperature environments. This study aims to design an experimental system that can confirm the ignition threshold, ignition delay, and ignition temperature by irradiating an ignition charge with a diode laser in a low-temperature environment. Ignition experiments at room temperature were conducted. The data were evaluated statistically to obtain an ignition threshold with the maximum likelihood method. The relationship between the laser irradiation duration and the laser power with respect to the ignition threshold was obtained. The target value of the low-temperature environment temperature was determined as -50 °C. We examined the requirements of the experimental system and conceptually designed the system to simulate the low-temperature environment. It was confirmed that the constructed experimental system cooled the ignition charge to -50 °C. In the ignition experiment, the ignition charge was successfully ignited at room temperature and at low temperature. The ignition delay, the ignition temperature, and the high-speed image were obtained. Eventually, the validity of the experimental system was confirmed through the function tests.</p>

    DOI: 10.57350/jesa.17

    CiNii Research

  • Evaluation of Measurement System for Heat Transfer Characteristics ofLiquid Oxygen Flow in a Thin Tube under High Heat Flux Conditions Reviewed International journal

    KITAGAWA Koki, MATSUI Kohei

    Journal of Evolving Space Activities ( International Symposium on Space Technology and Science )   1 ( 0 )   n/a   2023.01

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    <p>Heat transfer characteristics of liquid oxygen under high pressure and high heat flux should be elucidated to design a regenerative cooling nozzle for a hybrid rocket. Previously, we developed an experimental system using Joule heating to a thin tube in which liquid oxygen flows. The objective of this study is the evaluation of the measurement system to obtain the heat transfer characteristic under high pressure and high heat flux. We conducted a cold flow experiment and an experiment of heat transfer characteristic measurement. The friction factor of the tube is estimated with the Colebrook-White equation. The heat transfer coefficient was calculated by solving the heat conduction equation in the tube and the conservation laws of the fluid. The calculated heat transfer coefficient is in the same order as the experimental value. Consequently, we confirmed that experimental and analytical methods are appropriate to obtain heat transfer characteristics.</p>

    DOI: 10.57350/jesa.45

    CiNii Research

  • Performance Evaluation of the Launch Vehicle Using WAX-Based Altering-Intensity Swirling-Oxidizer-Flow-Type Hybrid Rocket Engine by Means of Evolutionary Algorithms

    KANAZAKI Masahiro, IMAMURA Taro

    The Proceedings of OPTIS ( The Japan Society of Mechanical Engineers )   2022.14 ( 0 )   U00073   2022.01

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    <p>To improve the thrust by the O/F shift, which is one of the weak points of the hybrid rocket, a method with a variable oxidizer strength has been proposed. In this study, the superiority of this type of hybrid rocket over the conventional hybrid rocket without variable oxidizer supply was compared through several launch vehicle designs, such as altitude maximization by vertical launch and downrange extension problems with an optimized launch angle. A multi-objective evolutionary algorithm and the multi-disciplinary evaluation method of the launch vehicle were applied.</p>

    DOI: 10.1299/jsmeoptis.2022.14.u00073

    CiNii Research

  • Development Results of Laser Ignition System for Solid Rocket Motor Reviewed International journal

    MINAMI Keisuke, MATSUURA Yoshiki, KITAGAWA Koki, ARAKAWA Satoshi, MORISHITA Naoki, TAKEMAE Toshiaki, IWABUCHI Shota, WADA Asato, TOKUDOME Shinichiro

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN ( THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES )   19 ( 5 )   807 - 811   2021.01

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    <p>This paper describes the development status of a laser ignition system for a solid rocket motor. This system is being developed as a simple, lightweight, and small design with a high resistance to electrical disturbances and a high level of safety. The most notable advantage of this system is that its high level of safety can decrease the cost of launching rockets into space. A laser initiator and a laser safe-and-arm device (laser S/A), which are essential components of the proposed system, were developed. In particular, prototypes of the laser initiator and laser S/A for the ignition of an upper stage rocket motor were manufactured, and some environmental tests, which are required for space rocket devices, were conducted. In addition, the lowest laser energy that is needed to ignite the laser initiator was determined by changing the laser power and operating time of the laser S/A. Furthermore, a small rocket motor vacuum fire test was successfully conducted.</p>

    DOI: 10.2322/tastj.19.807

    CiNii Article

    CiNii Research

    Other Link: https://ci.nii.ac.jp/naid/130008084441

  • Flight Results of Solid Propulsion Systems for Epsilon-4 Reviewed International journal

    KITAGAWA Koki, TOKUDOME Shinichiro, HORI Keiichi, UI Kyoichi, KINOSHITA Masahiro, HASHIMOTO Junichi, ICHIMURA Kotaro

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN ( THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES )   19 ( 3 )   400 - 406   2021.01

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    <p>Epsilon-4, which was the Enhanced Epsilon launch vehicle optional configuration with a multi-satellite mount structure, was successfully launched with seven satellites in January 2019. The seven satellites consist of 200 kg-class small-satellite, three micro-satellites and three CubeSats in the Innovative Satellite Technology Demonstration-1 program. The post flight analysis was conducted. The chamber pressure and thrust of three main motors and chamber pressure of SMSJ and SPM were analyzed to confirm the effectiveness of design and production methodologies. All solid propulsion systems for Epsilon-4 showed a very good behavior during the flight. As a result, the validity of the design and operation of the Enhanced Epsilon launch vehicle was confirmed.</p>

    DOI: 10.2322/tastj.19.400

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    Other Link: https://ci.nii.ac.jp/naid/130008034521

  • Reconstructed Ballistic Data Versus Wax Regression-Rate Intrusive Measurement in a Hybrid Rocket Reviewed International journal

    Jerome Messineo, Koki Kitagawa, Carmine Carmicino, Toru Shimada, Christian Paravan

    Journal of Spacecraft and Rockets ( American Institute of Aeronautics and Astronautics )   57 ( 6 )   1295 - 1308   2020.07

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    DOI: 10.2514/1.A34695

    DOI: 10.2514/1.A34695

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  • Prediction of space and time distribution of wax-based fuel regression rate in a hybrid rocket Reviewed

    Naka G., Messineo J., Kitagawa K., Carmicino C., Shimada T.

    AIAA Propulsion and Energy 2020 Forum   1 - 30   2020.01

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    A numerical set up has been developed to predict the axial distribution and time history of fuel regression rates with the aim of comparing numerical results with the experimental data. The numerical approach is based on a quasi-one-dimensional CFD strategy, which is coupled with chemical equilibrium combustion; the wax-fuel regression rate has been simulated with the liquefying fuel theory developed by Karabeyoglu. In this model, local radiation heat transfer from both the hot gas combustion molecules (CO, CO2, and H2O) and soot particles is considered. It is shown that, when radiation heating of the fuel is taken into account, the calculated fuel regression rates exhibit values and axial profiles close to the ones observed experimentally.

    DOI: 10.2514/6.2020-3768

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  • Evaluation of safety distance for blast of hybrid rocket propellants Reviewed

    Takahashi A., Kitagawa K., Shimada T.

    AIAA Propulsion and Energy Forum and Exposition, 2019   2019.01

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    For the purpose of constructing a reliable and reasonable evaluation method of the safety of hybrid rockets, the evaluation of the safety distance for blast wave is conducted. Physical phenomena leading to the blast of hybrid rocket propellants are extracted and modeled recognizing fuel fragmentation and dust explosion as key phenomena which cause blast waves. In order to evaluate the amount of fuel dust, of the particle size less than or equal to 500 μm, a particular correlation is used. The correlation between dust mass fraction and the ratio of the applied energy to the absorbed energy by the fuel is represented by utilizing existing experimental data. Also indefinite parameters, four energy efficiencies during the explosion processes, are identified by reproduction of existing experimental data of blast pressure measurement tests. It is found that, by using the adjusted model parameters, the present model can reproduce the existing safety distance data of hybrid rocket propellant blast for various impact velocities. The correlation about dust mass is valid for various fuels and, with this, it is also implied that the evaluation model for blast is applicable to various situations.

    DOI: 10.2514/6.2019-3917

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  • Development and Flight Results of Solid Propulsion System for Enhanced Epsilon Launch Vehicle Reviewed International journal

    KITAGAWA Koki, TOKUDOME Shinichiro, HORI Keiichi, TANNO Haruhito, NAKANO Nobuyuki

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN ( THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES )   17 ( 3 )   289 - 294   2019.01

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    <p>The development of enhanced propulsion system for the next Epsilon rocket was progressed. The development of Enhanced Epsilon is mainly the renewal of the second stage, and also includes each subsystem's improvement. The second stage motor M-35 was newly designed and manufactured. In order to verify the design, the static firing test of the second motor M-35 under the condition of vacuum ambient was conducted in 2015. The JAXA successfully launched the first Enhanced Epsilon launch vehicle. All solid propulsion systems for the Enhanced Epsilon launch vehicle showed a very good behavior during the flight</p>

    DOI: 10.2322/tastj.17.289

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    Other Link: https://ci.nii.ac.jp/naid/130007642475

  • Hybrid rocket firing experiments at various axial–tangential oxidizer-flow-rate ratios Reviewed

    Ozawa K., Kitagawa K., Aso S., Shimada T.

    Journal of Propulsion and Power   35 ( 1 )   1 - 15   2019.01

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    A breadboard model (BBM) of an altering-intensity swirling-flow-type (A-SOFT) hybrid rocket engine was recently developed, and static firing experiments of the BBM were performed under various axial and tangential oxidizer mass-flow rates. A-SOFTs are intended to control thrust at an optimal oxidizer-to-fuel-mass ratio and achieve a high baseline of regression rates with a fixed motor configuration. This is possible by controlling both the oxidizer mass-flow rate and the effective geometric swirl number. A simple model based on a continuous and monotonic function of oxidizer mass flux and effective geometric swirl number was able to accurately predict the performance of experiments conducted on the A-SOFT BBM. The local fuel regression behavior in the axial direction of the A-SOFT BBM was shown to be like that of a swirling-oxidizer-flow-type hybrid rocket engine. Combustion efficiency was evaluated indirectly using equations for the efficiencies of thrust and specific impulse to eliminate errors due to local pressure shifts and the centrifugal force in swirling flows. In most cases, this indirect method compensated for the overestimations of c efficiency that resulted by directly using chamber-pressure data.

    DOI: 10.2514/1.B36889

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  • Image analysis for velocity profile estimation in A-SOFT hybrid rocket combustor Reviewed International journal

    Kimura N., Obata K., Kitagawa K., Shimada T.

    Journal of Fluid Science and Technology ( The Japan Society of Mechanical Engineers )   13 ( 4 )   JFST0029 - JFST0029   2018.01

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    <p>Altering-intensity Swirling-Oxidizer-Flow-Type (A-SOFT) hybrid rocket engine (HRE) was proposed as a technique to solve problems of current hybrid rockets. It uses axial and tangential oxidizer injections and their mass flow rates are manipulated independently to control the thrust and O/F. The visualization experiment of combustion of gaseous oxygen (GOX) and polymethyl methacrylate (PMMA) of A-SOFT HRE is carried out under combustion pressure of 1 bar. Combustion gas flow in the combustor is captured by high speed cameras whose fps is 30000. In order to capture the nature of the flow field quantitatively, obtaining velocity profiles by image analysis applied to its visualization images is effective. Basic image analysis method is Direct Cross Correlation method and, for high precision and spatial resolution, Correlation Based Correction is applied recursively. Averaged velocity profiles are obtained by averaging the calculation results of 10000 images corresponding to the actual time duration of 0.3 s. Flames with strong white light emission are characteristic of hybrid rockets and regarded as traceable markers for the image analysis. These luminous flames are considered to flow in the boundary layer and velocity of flames in the boundary layer is important to capture the characteristics of combustion flow field. Axial velocity of the luminous flame is proportional to the total mixed mass flow rate for each location x. Tangential velocity is proportional to angular momentum given by tangential GOX injection and inversely proportional to the total mixed mass flow rate for each location x. And how much GOX injected in axial and tangential directions are mixed is speculated by velocity profiles. It is found that mixing of GOX injected in axial and tangential directions occurs at almost the same constant rate regardless of the ratio of GOX mass flow rate injected in axial and tangential directions.</p>

    DOI: 10.1299/jfst.2018jfst0029

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  • Flight results of solid propulsion system for epsilon launch vehicle from the third flight Reviewed

    Kitagawa K., Tokudome S., Hori K., Ui K., Kinoshita M., Hashimoto J., Ichimura K.

    Proceedings of the International Astronautical Congress, IAC   2018-October   2018.01

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    The third Epsilon launch vehicle, which was the Enhanced Epsilon launch vehicle optional configuration, was successfully launched with the payload of ASNARO-2 in January 2018. The post flight analysis was conducted. The chamber pressure and thrust include residual thrust of three main motors and chamber pressure of SMSJ and SPM were analysed to confirm the effectiveness of design and production methodologies. All solid propulsion systems for the third Epsilon launch vehicle showed a very good behaviour during the flight.

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  • Design Methodology of a Hybrid Rocket-Powered Launch Vehicle for Suborbital Flight Reviewed

    Kanazaki M., Yoda H., Chiba K., Kitagawa K., Shimada T.

    Journal of Aerospace Engineering   30 ( 6 )   2017.11

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    DOI: 10.1061/(ASCE)AS.1943-5525.0000778

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  • Performance and regression rate characteristics of 5-kN swirling-oxidizer-flow-Type hybrid rocket engine Reviewed

    Sakurai T., Yuasa S., Ando H., Kitagawa K., Shimada T.

    Journal of Propulsion and Power   33 ( 4 )   891 - 901   2017.01

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    Burning tests were carried out for the 5-kN-Thrust swirling-oxidizer-flow-Type hybrid rocket engine to establish the engine technology and to obtain the fuel regression characteristics. The engine attained stable burning without any combustion oscillation and C efficiencies of more than 98% under the 5-kN-Thrust conditions. The maximum timeaveraged thrust realized was 4.4 kN, which was lower than 5 kN. This was attributed to the regression rate being lower than the value estimated by regression rate correlation. The fuel regression behavior of this engine was characterized as the flow-development region near the grain leading edge and the fully developed turbulent flow region. The axial length of the flow-development region varied from that observed in the laboratory-scale engine, and it depended on the oxidizer mass flow rate, grain initial port diameter, and swirl strength. The controlling parameter of the regression rate in the fully developed flow region was modified to correlate with the grain port diameter. By effecting these modifications, the accuracy of the regression rate prediction was improved. The range of the applicable controlling parameter of the modified regression rate correlations was extended for use for larger-scale engines.

    DOI: 10.2514/1.B36239

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  • Development of solid propulsion system for enhanced epsilon launch vehicle and epsilon's second launch results Reviewed

    Kitagawa K., Tokudome S., Hori K., Hashimoto J., Nakano N., Tanno H.

    Proceedings of the International Astronautical Congress, IAC   13   8590 - 8596   2017.01

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  • Structurisation and visualisation of design space for launch vehicle with hybrid rocket engine Reviewed International journal

    Kazuhisa Chiba; Masahiro Kanazaki; Shin'ya Watanabe; Koki Kitagawa; Toru Shimada

    International Journal of Automation and Logistics   2 ( 1/2 )   26 - 44   2016.02

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    DOI: 10.1504/IJAL.2016.074912

  • Design optimization of launch vehicle concept using cluster hybrid rocket engine for future space transportation Reviewed

    KANAZAKI Masahiro, ITO Shoma, KANAMORI Fumio, NAKAMIYA Masaki, KITAGAWA Koki, SHIMADA Toru

    Journal of Fluid Science and Technology   11 ( 1 )   JFST0003 - JFST0003   2016.01

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    DOI: 10.1299/jfst.2016jfst0003

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    Other Link: https://ci.nii.ac.jp/naid/130005126936

  • Static burning tests on a bread board model of altering-intenisty swirling-oxidizer-flow-type hybrid rocket engine Reviewed

    Ozawa K., Usuki T., Mishima G., Kitagawa K., Yamashita M., Mizuchi M., Katakami K., Maji Y., Aso S., Tani Y., Wada Y., Shimada T.

    52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016   2016.01

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    A bread board model of Altering-number Swirling Flow Type (A-SOFT) hybrid rocket engine has been newly developed and the static burning tests have been conducted. A-SOFT hybrid rocket engines have controllability of both thrust and O/F without any replacement of components in the engine. This advantage is acquired by controlling oxidizer mass flow rate and effective swirl number. The purpose of this set of experiments is to confirm the continuity, monotonousness and predictability of the performances of A-SOFTs. The A-SOFT BBM showed a favorable fuel regression behavior. The fuel regression averaged along spatial direction fit the shape of regression rate function proposed before the experiments within ±3.5% errors, and the fuel regression rates are continuous and monotonous along swirl number and oxidizer mass flux. The O/F and thrust data also respectively fit the prediction formulas within ±4.2% and ±4.7% errors. c* efficiency is evaluated with the Isp efficiency - nozzle efficiency ratio ηIsp/ ηCF in order to compensate the pressure sensing errors caused by the centrifugal forces of swirling flows. Though ηIsp/ ηCF in the cases of weak swirl injection was clearly larger than in the cases of axial injection, its dependence on effective geometric swirl number was not clear in strong swirl conditions.

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  • Effect of oxidizer particle orientation on burning rates of composite propellants Reviewed

    Hasegawa H., Fukunaga M., Kitagawa K., Shimada T.

    International Journal of Energetic Materials and Chemical Propulsion   15 ( 4 )   285 - 304   2016.01

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    Regarding center-perforated composite solid propellant grains, the radial linear burning rate of the propellant often depends on its location in the web. In most cases, the burning rate at the middle of the web is highest along the radial direction. This deviation of the linear burning rate along the radial direction is called the midweb anomaly, the hump effect, and so on. The phenomenon is the result of multiple factors (e.g., orientation of oxidizer particles, existence of binder layers, and the effect of those factors on combustion and heat conduction in the solid phase). The physical cause of this phenomenon has not been understood in sufficient detail. In this study, the effect of oxidizer particle orientation on the burning rate is studied. The particle orientation in inert solid propellant grains is observed by micro-focus X-ray computerized tomography. To simplify the indefinite shape of actual ammonium perchlorate particles, simple cylindrical inert particles were mixed into inert propellant slurry. As a result the particle orientations were observed in center-perforated and solid cylindrical inert grains. The orientation of the particles seemed to be along the isochronous surface, which is formed during the casting process. One physical correlation between the particle orientation and the mean or local burning rate is investigated by numerical simulation from the point of view of the combustion surface configuration, which is formed by the different burning rates of the propellant ingredients. The results of the simulation suggest that the orientation of oxidizer particles in line with the burning direction increase the mean burning rate by forming and developing uneven surfaces.

    DOI: 10.1615/IntJEnergeticMaterialsChemProp.2016014195

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  • Development of test facilities for 5 kn-thrust hybrid rocket engines and a swirling-oxidizer-flow-type hybrid rocket engine for technology demonstration Reviewed

    Kitagawa K., Yuasa S., Sakurai T., Hatagaki S., Shiraishi N., Ando H., Yagishita T., Suzuki N., Takayama A., Yui R., Shimada T.

    International Journal of Energetic Materials and Chemical Propulsion   15 ( 6 )   435 - 451   2016.01

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    DOI: 10.1615/IntJEnergeticMaterialsChemProp.2017011994

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  • Development of solid propulsion system for enhanced epsilon launch vehicle and M-35 static firing test Reviewed

    Kitagawa K., Tokudome S., Hori K., Tanno H., Nakano N.

    Proceedings of the International Astronautical Congress, IAC   2016.01

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  • Ascendancy of extinction-reignition on single-stage hybrid sounding rocket in view of fuels Reviewed

    Chiba K., Yoda H., Ito S., Kanazaki M., Watanabe S., Kitagawa K., Shimada T.

    57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference   2016.01

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    DOI: 10.2514/6.2016-0583

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  • Design Optimization of Single-Stage Launch Vehicle Using Hybrid Rocket Engine,” International Journal of Aerospace System Engineering Reviewed International journal

    Kanazaki, M., Ariyarit, A., Yoda, H., Ito, S., Chiba, K., Kitagawa, K., Shimada, T.

    International Journal of Aerospace System Engineering   2 ( 2 )   29 - 33   2015.12

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    DOI: 10.20910/IJASE.2015.2.2.029

  • Evolutionary algorithm applied to ballistic launch vehicle design using hybrid rocket engine evaluated by enhanced flight simulation Reviewed

    Yoda H., Ito S., Kanazaki M., Chiba K., Kitagawa K., Shimada T.

    2015 IEEE Congress on Evolutionary Computation, CEC 2015 - Proceedings   618 - 625   2015.09

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    A multi-objective genetic algorithm (MOGA) has been applied to the multidisciplinary design optimization (MDO) of a launch vehicle (LV) with a hybrid rocket engine (HRE) to investigate the ability of an HRE to serve as a sounding rocket from various perspectives. In this study, the flight evaluation was enhanced to 3-degree-of-freedom (3DoF) in order to consider the equations of motion for horizontal and vertical motion and rotation of the LV. In the consideration of the rotation of the LV, the time variation of the center of gravity due to the fuel burn was estimated. The non-dominated sorting genetic algorithm-II (NSGA-II) was used to solve multi-objective problems (MoPs). Four design problems were examined in order to understand the practical physics of hybrid rocket. As a result, tradeoff information was observed for all design problems. The results for the present four design problems indicate that economical performance of LV is limited with the HRE in terms of the maximum altitude and maximum downrange distances achievable. The hypervolume, which was used as the metric to evaluate the difficulty of the design problems, reveals that the convergence of the solutions for not only altitude maximization in the case of a vertical launch but also the maximization of downrange at higher target altitudes was affected by the severe limitation. To observe the dependence of the design problems on the constraint, the design problems were visualized using a colored parallel coordinates plot (PCP), and the LV geometries determined from the nondominated solutions were successfully examined.

    DOI: 10.1109/CEC.2015.7256948

    Scopus

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  • Multidisciplinary design exploration for sounding launch vehicle using hybrid rocket engine in view of ballistic performance Reviewed

    Chiba K., Kanazaki M., Ariyarit A., Yoda H., Ito S., Kitagawa K., Shimada T.

    International Journal of Turbo and Jet Engines   32 ( 3 )   299 - 304   2015.09

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    Conceptual design of a launch vehicle with a hybrid rocket engine (HRE) has been implemented using design informatics approach in order to investigate the feasibility of a single-stage hybrid rocket. Two test design problems were formulated by using two objective functions: maximization of downrange and minimization of initial gross weight, seven design variables which describe geometry and initial conditions, and one constraint relative to target altitude. The optimization result reveals the economical performance of hybrid rocket is limited with HRE in terms of the maximum downrange achievable. Moreover, the data-mining result indicates the mechanism of design-variable behavior.

    DOI: 10.1515/tjj-2015-0038

    Scopus

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  • Numerical analysis of multi-parallelized swirling flow inside a circular pipe Reviewed

    Takayama A., Kitagawa K., Shimada T.

    Journal of Mechanical Science and Technology   29 ( 3 )   951 - 962   2015.03

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    The flow field of multi-parallelized swirling flow inside a circular pipe was investigated numerically. Two types of swirling flow configuration are considered. One type is the co-rotating type. Four co-rotating swirls are arranged at the vertex position of square in this type. The other type is the counter-rotating type which consists of two pairs of swirls having opposite swirl rotations. Each pair is arranged diagonally at the vertex position of a square. By coupling the discrete vortex method and boundary element method, unsteady flow simulation is performed. Swirl modeling with vortex elements is used in this simulation and its validity is confirmed. From the simulation results, in the co-rotating type, the four swirls interact and their shape is deformed. Each vortex motion vanishes rapidly in the downstream region. Finally, they are turned into a single swirling flow. In counter-rotating type, each vortex motion is maintained a little bit longer than co-rotating type, and their shape is not so deformed. However, the flow patterns are changed completely in the downstream region. The swirling velocity of each swirl mostly vanishes. Finally, they are turned into an axial flow. For the investigation of the mixing promoting effect due to parallelizing swirls, particle tracking simulations are performed in the co-rotating type and the counter-rotating type. As a comparison, the simulation for single swirl flow is also performed. In these simulations, the particles are introduced in the vicinity of pipe inner wall. In addition, the assumption that particles follow the flow motion absolutely is used. From the results, the motion of particles in these three cases is completely different. For the co-rotating and counter-rotating type, the particle entrainment into the main axial flow is clearly observed. This indicates the mixing is improved compared to single swirl flow. The difference of particle entrainment motion between co-rotating and counter-rotating type is slight.

    DOI: 10.1007/s12206-015-0209-8

    Scopus

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  • Conceptual design of single-stage launch vehicle with hybrid rocket engine using design informatics Reviewed

    Chiba K., Kanazaki M., Kitagawa K., Shimada T.

    Computational Methods in Applied Sciences   36   369 - 384   2015.01

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    DOI: 10.1007/978-3-319-11541-2_24

    Scopus

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  • Evaluation of Multi-Time-Combustion-Type Hybrid Rocket by Means of Multi-objective Evolutionary Algorithm Reviewed

    Kanazaki Masahiro, Chiba Kazuhisa, Kitagawa Koki, Shimada Toru

    Transaction of the Japanese Society for Evolutionary Computation ( The Japanese Society for Evolutionary Computation )   6 ( 3 )   137 - 145   2015.01

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    Language:Japanese   Publishing type:Research paper (scientific journal)

    With the multi-combustion technology, the combustion in a hybrid rocket engine (HRE) can be temporarily stopped via oxidizer throttling. In this paper, two types of HREs, one with multi-combustion technology and the other without, are compared to investigate the effects of multi-combustion on the flight performance of launch vehicles (LVs). Non-dominated Sorting Genetic Algorithm-II (NSGA-II) which was a multi-objective evolutionary algorithm (MOEA) was applied to solve the design problems using real-number coding and the Pareto ranking method. To investigate the effects of the multi-combustion on flight performance of LV with HRE, three design problems were considered. The first case was the maximization of the flight altitude and the minimization of the gross weight. The second case was the minimization of the maximum acceleration and the minimization of the gross weight. The final case was the maximization of the flight downrange and the minimization of the gross weight. Many non-dominated solutions were obtained by NSGA-II, and a trade-off was observed between the two objective functions in each case. MOEA results were visualized using a parallel coordinate plot. According to the exploration result, it was found that the multi-combustion of HRE was effective to reduce the maximum acceleration. Such ability could be expected to reduce the shock load to payloads carried by the LV with HRE.

    DOI: 10.11394/tjpnsec.6.137

    CiNii Article

    Other Link: https://ci.nii.ac.jp/naid/130005114801

  • Performance calculations and burning tests on altering-intensity swirling oxidizer flow type hybrid rocket engines Reviewed

    Ozawa K., Kitagawa K., Shimada T.

    Proceedings of the International Astronautical Congress, IAC   9   7332 - 7345   2015.01

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    As a technique to eliminate O/F shifts, Altering-intensity Swirling Oxidizer Flow Type (A-SOFT) hybrid rocket is proposed using the combination axial and tangential oxidizer injection. In this paper, the possible geometric design point of the motor is considered about 2-tons class single stage A-SOFT hybrid rockets, and the nominal performance increase by eliminating O/F shifts is evaluated. The highest altitude of the A-SOFT is 450 [km] and the averaged ISP is 284[s] with 100[kg] payload, and this performance is several percent higher than the ones of S-520 with 95[kg] payload, Japanese 2-tons class solid sounding rocket. Though A-SOFTs increase the nominal flight performance by 1% from Swirling Oxidizer Flow Type hybrid rockets, which cannot O/F shift, their feedback control prevents the large performance losses caused by fuel regression errors and residuals, and this function is not found in the conventional hybrid rockets. In this paper, a planning of steady state burning tests of A-SOFT bread board model is also explained. The purpose of the burning tests are to demonstrate the concept of A-SOFTs. The test motor is 250[N] scale and uses polypropylene and GOX and its burning duration is 5[s]. In more than 10 times steady state tests, 50% throttling conditions with effective geometric swirl intensity between 0 and 37.3 are inculded.

    Scopus

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  • Conceptual Design of Single-stage Rocket Using Hybrid Rocket by Means of Genetic Algorithm Reviewed International journal

    Kanazaki M., Ariyairt A., Chiba K., Kitagawa K., Shimada T.

    Procedia Engineering ( Elsevier )   99   198 - 207   2015.01

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    DOI: 10.1016/j.proeng.2014.12.526

    DOI: 10.1016/j.proeng.2014.12.526

    Scopus

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  • Conceptual design: Dependence of parameterization on design performance of three-stage hybrid rocket Reviewed International journal

    Masahiro KANAZAKI, Fumio KANAMORI, Yosuke KITAGAWA, Masaki NAKAMIYA, Koki KITAGAWA, Toru SHIMADA

    Journal of Fluid Science and Technology ( The Japan Society of Mechanical Engineers )   9 ( 5 )   JFST0071   2014.11

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    DOI: 10.1299/jfst.2014jfst0071

    DOI: 10.1299/jfst.2014jfst0071

    Other Link: https://www.jstage.jst.go.jp/article/jfst/9/5/9_2014jfst0071/_article/-char/en

  • Structurization of Design Space for Launch Vehicle with Hybrid Rocket Engine Using Stratum-Type Association Analysis International journal

    Chiba K., Kanazaki M., Watanabe S., Kitagawa K., Shimada T.

    Adaptation, Learning and Optimization ( Springer )   1   509 - 521   2014.11

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    DOI: 10.1007/978-3-319-13359-1_39

  • 設計情報学を用いたハイブリッドロケットエンジン搭載単段式宇宙輸送機の概念設計 Reviewed

    千葉 一永, 渡邉 真也, 金崎 雅博, 北川 幸樹, 嶋田 徹

    日本機械学会論文集 ( 日本機械学会 )   80 ( 818 )   TRANS0287   2014.10

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    DOI: 10.1299/transjsme.2014trans0287

    Kyutacar

  • Diversity of Design Knowledge for Launch Vehicle in View of Fuels on Hybrid Rocket Engine Reviewed International journal

    Kazuhisa CHIBA, Masahiro KANAZAKI, Masaki NAKAMIYA, Koki KITAGAWA, Toru SHIMADA

    ( The Japan Society of Mechanical Engineers ) 8 ( 3 )   JAMDSM0023 - JAMDSM0023   2014.07

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    Language:English   Publishing type:Research paper (scientific journal)

    DOI: 10.1299/jamdsm.2014jamdsm0023

    DOI: 10.1299/jamdsm.2014jamdsm0023

    Other Link: https://www.jstage.jst.go.jp/article/jamdsm/8/3/8_2014jamdsm0023/_article/-char/en

  • 設計情報学による燃料種を考慮した科学観測用単段式ハイブリッドロケットの概念設計 Reviewed

    千葉 一永, 金崎 雅博, 中宮 賢樹, 北川 幸樹, 嶋田 徹

    航空宇宙技術 ( 日本航空宇宙学会 )   13   41 - 50   2014.06

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    Language:Japanese   Publishing type:Research paper (scientific journal)

    DOI: 10.2322/astj.13.41

    DOI: 10.2322/astj.13.41

  • Experimental Study of Fragmentation of Hybrid Rocket Fuel Reviewed International journal

    Koki KITAGAWA, Yoshio NAKAYAMA, Tomoharu MATSUMURA, Kunihiko WAKABAYASHI, Ryo TODA, Takakazu MORITA, Toru SHIMADA

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN ( The Japan Society for Aeronautical and Space Sciences )   12 ( ists29 )   Pa_15 - Pa_20   2014.05

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    Authorship:Lead author, Corresponding author   Language:English   Publishing type:Research paper (scientific journal)

    DOI: 10.2322/tastj.12.Pa_15

    DOI: 10.2322/tastj.12.Pa_15

  • A Linear Stability Analysis of Oscillatory Combustion Induced by Combustion Time Delays of Liquid Oxidizer in Hybrid Rocket Motors Reviewed International journal

    Takakazu Morita, Koki Kitagawa, Toru Shimada, Shigeru Yamaguchi

    International Journal of Energetic Materials and Chemical Propulsion ( Begell House )   13 ( 1 )   83 - 96   2014.01

  • 科学観測用単段式ハイブリッドロケット概念設計への設計情報学の実運用 Reviewed

    千葉 一永, 金崎 雅博, 中宮 賢樹, 北川 幸樹, 嶋田 徹

    進化計算学会論文誌 ( 進化計算学会 )   4 ( 3 )   85 - 95   2013.11

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    Language:Japanese   Publishing type:Research paper (scientific journal)

    DOI: 10.11394/tjpnsec.4.85

    DOI: 10.11394/tjpnsec.4.85

  • CHARACTERISTICS OF CHEMICALLY MODIFIED AND NANOCOMPOSITE POLYMERS AS NOVEL FUELS FOR HYBRID ROCKET PROPULSION Reviewed International journal

    Koki Kitagawa, Paul Joseph, Vasily Novozhilov, Toru Shimada

    International Journal of Energetic Materials and Chemical Propulsion   11 ( 6 )   549 - 566   2013.11

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    Authorship:Lead author, Corresponding author   Language:English   Publishing type:Research paper (scientific journal)

    DOI: 10.1615/IntJEnergeticMaterialsChemProp.2013005406

    DOI: 10.1615/IntJEnergeticMaterialsChemProp.2013005406

  • Conceptual Design of Single-Stage Launch Vehicle with Hybrid Rocket Engine for Scientific Observation Using Design Informatics Reviewed International journal

    Kazuhisa CHIBA, Masahiro KANAZAKI, Masaki NAKAMIYA, Koki KITAGAWA, Toru SHIMADA

    Journal of Space Engineering ( The Japan Society of Mechanical Engineers )   6 ( 1 )   15 - 27   2013.09

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    DOI: 10.1299/spacee.6.15

    DOI: 10.1299/spacee.6.15

    Other Link: https://www.jstage.jst.go.jp/article/spacee/6/1/6_15/_article/-char/en

  • Burning rate anomaly of composite propellant grains Reviewed International journal

    H. Hasegawa, M. Fukunaga, K. Kitagawa, T. Shimada

    Combustion, Explosion, and Shock Waves   49 ( 5 )   583 - 592   2013.09

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  • Low-Frequency Feed-System-Coupled Combustion Instability in Hybrid Rocket Motors Reviewed International journal

    Takakazu MORITA, Saburo YUASA, Koki KITAGAWA, Toru SHIMADA, Shigeru YAMAGUCHI

    Journal of Thermal Science and Technology ( The Japan Society of Mechanical Engineers and The Heat Transfer Society of Japan )   8 ( 2 )   380 - 394   2013.07

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    DOI: 10.1299/jtst.8.380

    DOI: 10.1299/jtst.8.380

    Other Link: https://www.jstage.jst.go.jp/article/jtst/8/2/8_380/_article/-char/en

  • Multi-Stage Hybrid Rocket Conceptual Design for Micro-Satellites Launch using Genetic Algorithm Reviewed

    Yosuke KITAGAWA, Koki KITAGAWA, Masaki NAKAMIYA, Masahiro KANAZAKI, Toru SHIMADA

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   55 ( 4 )   229 - 236   2012.07

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  • LIQUID OXYGEN VAPORIZATION TECHNIQUES FOR SWIRLING-OXIDIZER-FLOW-TYPE HYBRID ROCKET ENGINES Reviewed International journal

    Saburo Yuasa, Koki Kitagawa, Toshiaki Sakurazawa, Ikuno Kumazawa, Takashi Sakurai

    International Journal of Energetic Materials and Chemical Propulsion   10 ( 2 )   155 - 168   2011.04

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    DOI: 10.1615/IntJEnergeticMaterialsChemProp.2012001351

    DOI: 10.1615/IntJEnergeticMaterialsChemProp.2012001351

  • 推力1500N級酸化剤流旋回型ハイブリッドロケットエンジン用LOX気化ノズルの評価燃焼実験 Reviewed

    北川 幸樹, 桜沢 俊明, 湯浅 三郎

    宇宙技術 ( 日本航空宇宙学会 )   6   47 - 54   2007.01

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    Authorship:Lead author   Language:Japanese   Publishing type:Research paper (scientific journal)

    液体酸素(LOX)を用いた酸化剤流旋回型ハイブリッドロケットエンジンでは,インジェクターより上流でLOXを気化する必要がある.筆者らは,LOXを気化する方法の一つとして,再生冷却方式のLOX気化ノズルを提案している.本研究では,推力1500N用のLOX気化ノズルを設計製作し,設計値より低い酸素流量と燃焼室圧条件において独立気化方式と再生冷却方式による気化燃焼実験を行った.独立気化方式の気化実験によって,LOXの気化とノズルの安全性が確認され,数値計算によるLOX気化ノズルの設計が適切であることが分かった.再生冷却方式の気化燃焼実験では,確実な着火と安定した燃焼が得られ,LOX気化ノズルを用いた酸化剤流旋回型ハイブリッドロケットエンジンの自立燃焼に成功した.また,LOXを気化させることで,LOXに直接旋回を与える場合より燃料後退速度やC*効率を向上できた.

    DOI: 10.2322/stj.6.47

    Kyutacar

  • Combustion Characteristics of Mg Vapor Jet Flames in CO2 Atmospheres Reviewed International journal

    Yuasa Saburo, Sakoda Kou, Aizawa Shinri, Kitagawa Koki

    Proceedings of the Combustion Institute ( Elsevier )   31 ( 2 )   2037 - 2044   2007.01

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    ドイツ   ハイデルベルグ  

    An experimental study was performed on the combustion characteristics of a jet diffusion flame of Mg vapor injected through a small nozzle into CO2 atmospheres at low pressures from 8 to 48 kPa with a view to using Mg as fuel for a CO2-breathing turbojet engine in the Mars atmosphere. The Mg vapor jet produced three types of the flame. At lower pressures and higher injection velocities, a red-heated jet flame formed, in which the injected Mg vapor was heated by spontaneous reactions, turning red. At medium pressures and injection velocities, a stable luminous lifted-like flame developed above the rim of the chimney, a tube-like combustion product for the Mg vapor passage that grew on the nozzle during combustion. The flame had similar flame length properties to laminar jet diffusion flames of gaseous fuels. At higher pressures and lower injection velocities, a stable luminous attached flame developed at the rim of the chimney. The same reactions, producing MgO(g), CO and MgO(c), proceeded preferentially for all flames and chimneys. Carbon was only subordinately generated. Burning behavior of Mg vapor jets in a CO2 atmosphere has been represented, including the homogeneous reaction of Mg vapor with CO2, the diffusion of CO2, and the condensation and deposit of MgO. The injection velocity of Mg vapor at the rim of the chimney and the exothermic reactions with diffused CO2 that occur there play a crucial role in the attachment and development of the flames. The flame structure may be explained in terms of the relatively low gas-phase reaction rate of Mg with CO2.

    DOI: 10.1016/j.proci.2006.07.192

  • 液体酸素旋回型ハイブリッドロケットエンジンの燃焼特性 Reviewed

    北川 幸樹, 湯浅 三郎

    日本航空宇宙学会論文集 ( 日本航空宇宙学会 )   54 ( 629 )   242 - 249   2006.06

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    We have proposed a swirling oxidizer type hybrid rocket engine. In this paper, liquid oxygen (LOX) was used as oxidizer. Combustion tests of a hybrid rocket engine with a swirling LOX flow were conducted by changing the swirl strength. Ignition was rapid and reliable, and combustion of PMMA with swirling LOX was stable. Fuel regression rates, C* efficiency and specific impulse of the hybrid rocket engine with swirling LOX flow were smaller than those with swirling gaseous oxygen (GOX). This low performance may be restraint of atomization and vaporization of LOX by formation of a liquid layer on the PMMA fuel and a decline of angular momentum of the swirling LOX during vaporization. Combustion oscillation occurred when the ratios of differential pressure between injector pressure and chamber pressure to chamber pressure were small. This combustion oscillation was confirmed to be a “Chugging” mode due to combustion time lag of LOX.

    DOI: 10.2322/jjsass.54.242

    Kyutacar

  • 大学における小型再使用打上げシステムの開発研究その2:酸化剤旋回型小型ハイブリッドロケットの開発と打上げ Reviewed

    湯浅 三郎,山本 研吾,蜂谷 仁司,北川 幸樹

    日本航空宇宙学会誌   53 ( 616 )   13 - 19   2005.05

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    Kyutacar

  • Current Status of Rocket Developments in Universities -Development of a Small Hybrid Rocket with a Swirling Oxidizer Flow Type Engine Reviewed

    Saburo YUASA, Koki KITAGAWA

    The Journal of Space Technology and Science ( 日本ロケット協会 )   21 ( 1 )   1_1 - 1_11   2005.01

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    Language:English   Publishing type:Research paper (scientific journal)

    To develop an experimental small hybrid rocket with a swirling gaseous oxygen flow type engine, we made a flight model engine. Burning tests of the engine showed that a maximum thrust of 692 N and a specific impulse of 263 s (at sea level) were achieved. We designed a small hybrid rocket with this engine. The rocket measured 1.8 m in length and 15.4 kg in mass. To confirm the flight stability of the rocket, wind tunnel tests using a 112-scale model of the rocket and simulations of the flight attitude and trajectory were carried out. A flight test was conducted at Taiki-cho, Hokkaido, Japan on March 2001. The rocket reached an altitude of about 600 m, thus recording the first successful flight of a hybrid rocket in Japan. For the next stage, future issues to develop larger hybrid rockets using a swirling liquid oxygen flow type engine are discussed, and preliminary burning tests of the engine have been carried out.

    DOI: 10.11230/jsts.21.1_1

    Kyutacar

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Publications (Books)

  • Elucidation of Influence of Fuels on Hybrid Rocket Using Visualization of Design-Space Structure

    Chiba K., Watanabe S., Kanazaki M., Kitagawa K., Shimada T.(Joint author)

    Springer Netherland  2019.01 

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    Total pages:16   Responsible for pages:43-488   Language:Japanese

    The stratum-type association analysis as a new data mining technique has been applied to the conceptual design of a single-stage launch vehicle with hybrid rocket engine. The conceptual design was performed by using design informatics, which has three points of view, i.e., problem definition, optimization, and data mining. The primary objective of the present design is that the down range and the duration time in the lower thermosphere are sufficiently secured for the aurora scientific observation, whereas the initial gross weight is held down to the extent possible. The multidisciplinary design optimization was performed by using a hybrid evolutionary computation. Data mining was also implemented by using the stratum-type association analysis. Consequently, the design information regarding the tradeoffs has been revealed. The hierarchical dendrogram generated by using the stratum-type association analysis indicates the structure of the design space in order to improve the objective functions. Furthermore, the assignments of the stratum-type association analysis have been obtained.

    Scopus

  • Genetic Algorithm Applied to Design Knowledge Discovery of Launch Vehicle Using Clustered Hybrid Rocket

    Kanazaki M., Chiba K., Ito S., Nakamiya M., Kitagawa K., Shimada T.(Joint author)

    Springer Netherland  2019.01 

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    Total pages:17   Responsible for pages:519-535   Language:English

    The conceptual design of a multi-stage launch vehicle (LV) using a clustered hybrid rocket engine (HRE) is carried out through multi-disciplinary design optimization. This LV designed in this study can deliver micro-satellites to sunsynchronous orbits (SSO). The optimum size of each component, such as an oxidizer tank containing liquid oxidizer, a combustion chamber containing solid fuel, a pressurizing tank, and a nozzle, should be strictly optimized because of the combustion mechanism is different from existent liquid/solid rocket engines. In this study, the semi-empirical based evaluation is applied to the design optimization of the multi-stage LV. For clustered HRE, paraffin (FT-0070) is used as a propellant for the HRE, and three cases are compared to examine the commonization effect of the engine for each stage: In the first case, HREs are optimized for each stage. In the second case, HREs are optimized together for the first and second stages but separately for the third stage. In the third case, HREs are optimized together for each stage. The optimization results show that the performance of the design case that uses the same HREs in all stages is 40% reduced compared with the design case that uses optimized HREs for each stage.

    Scopus

  • Hybrid Propulsion Technology Development in Japan for Economic Space Launch

    Shimada T., Yuasa S., Nagata H., Aso S., Nakagawa I., Sawada K., Hori K., Kanazaki M., Chiba K., Sakurai T., Morita T., Kitagawa K., Wada Y., Nakata D., Motoe M., Funami Y., Ozawa K., Usuki T.(Joint author)

    Springer Nature  2017.01 

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    Total pages:31   Responsible for pages:545-575   Language:English

    The demand for the economic and dedicated space launchers for vast amount of lightweight, so-called nano-/microsatellites, is now growing rapidly. There is a strong rationale for the usage of the hybrid propulsion for economic space launch as suggested by the assessment conducted here. A typical concept of development of such an economic three-stage launcher, in which clustering unit hybrid rocket engines are employed, is described with a development scenario. Thanks to the benefits of hybrid rocket propulsion, assuring and safe, economic launcher dedicated to lightweight satellites can be developed with a reasonable amount of quality assurance and quality control actions being taken in all aspects of development such as raw material, production, transportation, storage, and operation. By applying a multi-objective optimization technique for such a launch system, examples of possible launch systems are obtained for a typical mission scenario for the launch of lightweight satellites. Furthermore, some important technologies that contribute strongly to economic space launch by hybrid propulsion are described. They are the behavior of fuel regression rate, the swirling-oxidizer-flow-type hybrid rocket, the liquid oxygen vaporization, the multi-section swirl injection, the low-temperature melting point thermoplastic fuel, the thrust and O/F simultaneous control by altering-intensity swirl-oxidizer-flow-type (A-SOFT) hybrid, the numerical simulations of the internal ballistics, and so on.

    Scopus

Conference Prsentations (Oral, Poster)

  • [2022-o-1-21] Evaluation of Heat Transfer Characteristics of Liquid Oxygen Flow in a Thin Tube under High Heat Flux Conditions

    Koki Kitagawa, Kohei Matsui

    33rd International Symposium on Space Technology and Science  2022.03 

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    Event date: 2022.02.28 - 2022.03.04   Language:English   Country:Japan  

  • [2022-a-33] Laser Ignition Characteristics of Low-Temperature Boron/Potassium Nitrate

    Kohei Matsui, Yoshiki Matsuura, Koki Kitagawa

    33rd International Symposium on Space Technology and Science  2022.03 

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    Event date: 2022.02.28 - 2022.03.04   Language:English   Country:Japan  

  • HR-2021-06 酸化剤流旋回流中におけるニクロム線の寸法および酸素流量の着火特性への影響

    福永 裕生,北川 幸樹

    第4回 ハイブリッドロケット シンポジウム  2022.02  JAXA

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    Event date: 2022.02.14   Language:Japanese  

  • HR-2021-18 LOXの熱伝達特性計測システムの改良と評価実験

    福田 次朗,松井 康平,北川 幸樹

    第4回 ハイブリッドロケット シンポジウム  2022.02  JAXA

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    Event date: 2022.02.14   Language:Japanese  

  • STEP-2021-045 LSDにおけるレーザ強度および比熱比の爆風波変換効率への影響

    新井 天,松井 康平,北川 幸樹

    令和3年度 宇宙輸送シンポジウム  2022.01  JAXA

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    Event date: 2022.01.13 - 2022.01.14   Language:Japanese  

  • JSASS-2021-S021 低温環境における火薬のレーザ点火実験システムの構築

    椎 優一朗,松井 康平,松浦 芳樹,北川 幸樹

    日本航空宇宙学会西部支部講演会(2021)  2021.11  日本航空宇宙学会 西部支部

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    Event date: 2021.11.19   Language:Japanese  

  • HR-2020-09 LOXの熱伝達特性計測予備実験

    北川 幸樹, 中 源也, 嶋田 徹

    第3回 ハイブリッドロケット シンポジウム  JAXA

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    Event date: 2020.11.27   Language:Japanese  

  • OS4-5 Development of Experimental System to Measure Heat Transfer Characteristics of LOX

    K. Kitagawa , G. Naka, T. Shimada

    Seventeenth International Conference on Flow Dynamics  Tohoku University

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    Event date: 2020.10.28 - 2020.10.30   Language:English  

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Contracts

  • 低温環境下におけるボロン硝酸カリウム火薬のレーザ点火に関する研究

    2021.12 - 2022.03

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    Grant type:Joint research

    ペルチェ素子を用いて火薬を冷却する実験装置を構築し,火薬を-50℃程度に冷やした状態で火薬にレーザを集光し点火させる.高速度カメラ,放射温度計を用いて着火遅れおよび着火温度を取得する.着火限界についてはレーザ強度を変化させて実験を行い,着火/不着火データから統計的手法を用いて評価を行う.以上より,深宇宙環境下でも確実に動作できるレーザ点火装置設計に関する知見を得る.

  • レーザを用いた固体ロケット点火システムにおける点火限界に関する調査

    2021.01 - 2021.03

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    Grant type:Joint research

  • デトネーションキックモーター観測ロケット軌道投入実証

    2020.12 - 2023.02

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    Grant type:Joint research

    デトネーションエンジンを使用した高性能キックモーターを開発する。開発したキックモーターを観測ロケットで実証し、軌道投入実証プログラムの採択を目指す。
    本研究では、デトネーションエンジンシステムに関して、ノズル最適化とアレイ化、革新的熱制御、タンク込みシステム開発といった課題を解決し、軌道投入ミッションが可能な段階へと技術のステップアップ研究を実施する。また、2024 年度打に観測ロケットで打ち上げが予定されている、液体推進剤を搭載したデトネーションエンジンシステムのEM開発を行う。その後、デトネーションエンジンキックモーターを軌道実証(2025年度)に採択を目指す。九州工業大学では、液体酸素供給システムの検討および開発研究を実施する。

  • レーザ点火における火薬類の点火限界に関する研究

    2020.12 - 2021.03

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    Grant type:Joint research

Other External Funds

  • 火薬のレーザ着火に関わる物理過程の実験的評価

    2022.04 - 2023.03

    2022年度公益財団法人火薬工業技術奨励会研究助成金   燃焼工学

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    本研究では 着火過程を明らかにするために ,それぞれの物理現象がどのような過程を経て発生するか定量的に評価することを目的とする.具体的には,火薬のレーザ着火特性を解明するために,レーザ加熱による火薬の赤熱,化学反応による急激な温度上昇,火薬表面からの燃焼ガス生成がどのようなタイムスケールで発生しているかを明らかにする.着火遅れを各物理現象に切り分けて評価するというアプローチは,単一の手法で 着火遅れを取得している従来研究と比較して独創的かつ新規性があり,火薬のレーザ着火現象解明に寄与できる.

Career of Research abroad

  • ハイブリッドロケットエンジン用ポリマ燃料の熱分解特性に関する研究

    アルスター大学  Project Year:  2011.02.01 - 2011.10.01

Activities of Academic societies and Committees

  • 日本航空宇宙学会 宇宙航行部門委員会   部門委員長  

    2022.04

  • 第68回宇宙科学技術連合講演会実行委員会   実行委員長  

    2022.04 - 2025.03

  • 日本航空宇宙学会 西部支部   日本航空宇宙学会 西部支部 第49期会計幹事  

    2021.03 - 2022.03

  • 第65回宇宙科学技術連合講演会実行委員会   委員  

    2021.01 - 2022.03

  • 第3回 ハイブリッドロケットシンポジウム   世話人、司会  

    2020.05 - 2020.11

  • 日本航空宇宙学会 西部支部   日本航空宇宙学会 西部支部委員  

    2020.04

  • 第62回宇宙科学技術連合講演会実行委員会   委員  

    2018.01 - 2019.03

  • 第59回宇宙科学技術連合講演会実行委員会   委員  

    2015.01 - 2016.03

  • ISTS Space Transportation セッション小委員会   委員  

    2014.01

  • 日本航空宇宙学会 宇宙航行部門委員会   委員  

    2012.04 - 2022.03

  • 第56回宇宙科学技術連合講演会実行委員会   委員  

    2012.01 - 2013.03

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Social activity outside the university

  • 北九州ゆめみらいワーク2021への出展 「先進的ロケットの研究」

    北九州市産業経済局雇用政策課  北九州ゆめみらいワーク2021  西日本総合展示場A~C  2021.12.02 - 2021.12.03

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    Audience: Schoolchildren, Junior students, High school students, Guardians, General

    Type:Other

  • 2021年度 オンラインオープンキャンパス 公開講義 誰もが気軽に宇宙へ行くための 先進的ハイブリッドロケットシステムの研究

    Role(s):Lecturer

    2021年度 オンラインオープンキャンパス 公開講義  九工大  2021.08.07

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    Audience: High school students, Guardians

    Type:Other