Faculty Profiles - KITAGAWA Koki

Papers - KITAGAWA Koki

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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

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

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

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

Scopus

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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

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

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

Language：English Publishing type：Research paper (international conference proceedings)

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.

Scopus

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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

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

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

Scopus

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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

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

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

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

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

Language：English Publishing type：Research paper (international conference proceedings)

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

Language：English Publishing type：Research paper (international conference proceedings)

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

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

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

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

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

Language：English Publishing type：Research paper (international conference proceedings)

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

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

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

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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Papers - KITAGAWA Koki