研究者詳細 - 杵淵　紀世志

Two-photon absorption laser induced fluorescence with various laser intensities for density measurement of ground state neutral xenon 査読有り

Kinefuchi K., Nunome Y., Cho S., Tsukizaki R., Chng T.L.

Acta Astronautica 161 巻頁： 382 - 388 2019年8月

担当区分：筆頭著者記述言語：英語掲載種別：研究論文（学術雑誌）出版者・発行元：Acta Astronautica

Electrostatic plasma thrusters such as ion engines and Hall thrusters commonly use xenon as a propellant and several measurement techniques for xenon ions and metastable neutrals have been applied to evaluate the characteristics of the thrusters. Although density measurements of ground state neutral xenon can provide crucial information on the ionization characteristics and help explain charge exchange phenomenon, much less research is available due to its technical difficulty. Two-photon absorption laser induced fluorescence is promising because it allows access to ground state xenon atoms by using around 220–260 nm wavelength lasers which have become more readily available lately. In this study, observation of the fluorescence following two-photon excitation from a room temperature (cold) xenon gas cell is conducted with 249 and 252 nm wavelength excitation at xenon pressures of 0.1 and 10 Torr. The fluorescence signals are obtained against a wide range of laser intensities, and the resulting fluorescence response comprises of a few regimes – weak-excitation, saturation, and an intermediate regime. The natural lifetime and quenching rate are evaluated by analyzing the fluorescence decay, and the result is consistent with published literature. Finally, actual application to ground tests of Hall thrusters is discussed based on the experimental results, especially with respect to their fluorescence responses.

DOI： 10.1016/j.actaastro.2019.03.018

Development of a new MLI for orbital cryogenic propulsion systems-Thermal performance under one atmosphere to a vacuum 査読有り

Takeshi Miyakita, Kazuya Kitamoto, Kiyoshi Kinefuchi, Masanori Saitoh, Tomoyuki Hirai, Hiroyuki Sugita

IOP Conference Series: Materials Science and Engineering 502 巻 ( 1 ) 2019年6月

Investigation of cryogenic chilldown in a complex channel under low gravity using a sounding rocket 査読有り

Kinefuchi K., Sarae W., Umemura Y., Fujita T., Okita K., Kobayashi H., Nonaka S., Himeno T., Sato T.

Journal of Spacecraft and Rockets 56 巻 ( 1 ) 頁： 91 - 103 2019年

担当区分：筆頭著者記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）出版者・発行元：Journal of Spacecraft and Rockets

Torealize high-performance cryogenic propulsion systems, the chilldown sequence has to be improved. Because the chilldown is carried out under low gravity, the effect of gravity on the two-phase flow, especially at low flow rate, should be investigated. To understand the physics under low gravity, an experiment was conducted using a sounding rocket. Two identical test sections with different mass flow rates simulated part of a turbopump, each of which has a complex flowpath including slits and a dead end. Using liquid nitrogen, the flight experiment obtained data of temperatures, pressures, void fractions, and video frames of liquid motion. Then, the flight experiment data were compared to the ground data taken under normal gravity, revealing that the slits played an important role in the chilldown process and that the test sections were quickly chilled down under low gravity. The slits of the test sections formed liquid jets, and their behaviors were different from those in the ground experiment. In the flight experiment, the jets easily reached the dead end of the test sections and cooled down the whole walls due to the increase in inertia and wettability; however, such behaviors were hardly observed in the ground experiment. The difference between the ground and flight is significant at lower flow rate.

DOI： 10.2514/1.A34222

全電化衛星査読有り

杵淵紀世志

日本航空宇宙学会誌 67 巻 ( 6 ) 頁： 227(J‐STAGE) - 227 2019年

Thermal performance and flow visualization of a planar heat-pipe leading edge 査読有り

Kinefuchi K., Tamba J., Saito I.

Journal of Spacecraft and Rockets 56 巻 ( 3 ) 頁： 771 - 779 2019年

担当区分：筆頭著者記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）出版者・発行元：Journal of Spacecraft and Rockets

The sharp leading edges of a hypersonic vehicle are promising for the enhancement of its aerodynamic performance. However, they need a cooling mechanism because they are exposed to extremely high heat flux during reentry or hypersonic cruise, which easily heats up the surface materials beyond their temperature limits. This study explores the concept of a leading edge with planar heat-pipe cooling for which the whole inner surfaces are directly covered with a capillary wick. Its isothermal characteristic and simple configuration can provide robustness; however, due to the uniqueness of the planar type, the thermofluid characteristics should be investigated. Therefore, two kinds of heating tests (the inside visualization test and high-temperature test) were conducted using water as a working fluid. The gravity effects were surveyed, changing the test article attitude. The results showed that the planar concept worked as expected; no large temperature distribution was observed along both the chord and span directions, even in a nose-up attitude or a top heat configuration; the heat transfer performance was improved in nose-down attitude. During the heat-pipe operation, a heat transfer coefficient approximately 100 times higher than that of an evacuated operation was obtained. Visualizing inside the test article revealed that the screen mesh wick was properly covered with condensed water and that typical bubble formations of nucleate boiling were observed around the tip in some cases.

DOI： 10.2514/1.A34274

LE-5B-3地上燃焼試験用静電容量型ボイド率計の開発査読有り

坂本勇樹, 小林弘明, 東和弘, 長尾直樹, 杉森大造, 杵淵紀世志, 佐藤哲也

航空宇宙技術(Web) 18 巻 ( 0 ) 頁： 19‐28(J‐STAGE) - 28 2019年

記述言語：日本語掲載種別：研究論文（学術雑誌）出版者・発行元：一般社団法人日本航空宇宙学会

Many space vehicles are powered by liquid hydrogen and liquid oxygen. Such fuel are cryogenic fluids, so they are easy to boil and become gas-liquid two phase flow. The LE-5B-3 engine has the capability of the idle mode firing same as the LE-5B-2 engine. Assessment of flow condition at the inlet of fuel turbo pump is important to operate the engine, because the fuel may flow in saturated condition under the idle mode in principle. In a two-phase flow state, void fraction is one of the most important parameters to assess the flow. Although many types of void fraction sensors were proposed, the capacitive technique has advantages to mount on the engine from the viewpoint of size, weight, toughness. In this study, plural circular electrodes capacitive void fraction sensor is developed for LE-5B-3 engines' ground firing test. The sensor was designed based on electric field analysis, and the specification was assessed prior to the ground test. The sensor was used in qualification test, and it was succeeded in achieving stable measurement and it helped to understand the fluid state during the engine operation. The sensor design technique, the assessment results and the ground test results are discussed in this paper.

DOI： 10.2322/astj.JSASS-D-18-00017

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Numerical investigation of nanosecond pulsed plasma actuators for control of shock-wave/boundary-layer separation 査読有り Open Access

Kinefuchi K., Starikovskiy A.Y., Miles R.B.

Physics of Fluids 30 巻 ( 10 ) 2018年10月

担当区分：筆頭著者記述言語：英語掲載種別：研究論文（学術雑誌）出版者・発行元：Physics of Fluids

This study numerically explores the flow physics associated with nanosecond pulsed plasma actuators that are designed to control shock-wave induced boundary-layer separation in a Mach 2.8 supersonic flow. By using two dielectric barrier surface discharge actuator configurations, parallel and canted with respect to the flow velocity vector, a previous experiment suggested that the actuator worked in two ways to influence the interaction: boundary layer heating and vorticity production. The heating effect was enhanced with the parallel electrode and made the boundary-layer separation stronger, while the canted electrode produced vorticity and suppressed the boundary-layer separation due to the momentum transfer from the core flow. Because the detailed physical processes are still unclear, in this paper a numerical investigation is undertaken with a large eddy simulation and an energy deposition model for the plasma actuation, in which the dielectric barrier discharge produced plasma is approximated as a high temperature region. The flow characteristics without the plasma actuation correspond to the experimental observation, indicating that the numerical method successfully resolves the shock-wave/boundary-layer interaction. With the plasma actuation, complete agreement between the experiment and calculation has not been obtained in the size of the shock-wave/boundary-layer interaction region. Nevertheless, as with the experiment, the calculation successfully demonstrates definite difference between the parallel and canted electrodes: the parallel electrode causes excess heating and increases the strength of the interaction, while the canted electrode leads to a reduction of the interaction strength, with a corresponding thinning of the boundary layer due to the momentum transfer. The counter flow created by the canted actuator plays an important role in the vortex generation, transferring momentum to the boundary layer and, consequently, mitigating the shock induced boundary layer separation.

DOI： 10.1063/1.5051823

Theoretical and experimental study of the active control of bubble point pressure using a magnetic field and its applications 査読有り

Kinefuchi K., Kobayashi H.

Physics of Fluids 30 巻 ( 6 ) 2018年6月

担当区分：筆頭著者記述言語：英語掲載種別：研究論文（学術雑誌）出版者・発行元：Physics of Fluids

Space propulsion systems use screen mesh devices as filters to block contaminants and as propellant management devices to settle the propellants. The bubble point pressure indicates the basic capillary performance for liquid acquisition of screen meshes. Actively controlling the bubble point pressure can result in flexible and efficient operation of the propulsion systems. High-performance cryogenic propellants, such as liquid hydrogen and oxygen, exhibit magnetic properties. Therefore, a method to actively control the bubble point pressure of cryogenic propellants by applying a magnetic field is proposed in this study. The magnetic pressures affect the pressure balance around the gas-liquid interface separated by the screen mesh, which can thereby control the bubble point pressure. To demonstrate the concept and theoretical basis, a bubble point experiment is conducted using a ferrofluid and solenoid. This experiment proves that the magnetic field actively controls the bubble point pressure and performs both suppression and enhancement of the liquid acquisition performance of the screen mesh. The theory related to magnetic pressures is observed to successfully predict the experimental results. The feasibility of the active control of the bubble point pressure of liquid oxygen is discussed based on the validated theory, and two applications of this technique in cryogenic propulsion systems are depicted.

DOI： 10.1063/1.5034222

電気推進ロケットエンジンを用いたミッションの現状と今後 (小特集電気推進ロケットエンジン技術の現状と展望) 査読有り

西山和孝, 杵淵紀世志

プラズマ・核融合学会誌 = Journal of plasma and fusion research 94 巻 ( 2 ) 頁： 60 - 65 2018年2月

Control of shock-wave/boundary-layer interaction using nanosecond-pulsed plasma actuators 査読有り Open Access

Kinefuchi K., Starikovskiy A.Y., Miles R.B.

Journal of Propulsion and Power 34 巻 ( 4 ) 頁： 909 - 919 2018年

担当区分：筆頭著者記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）出版者・発行元：Journal of Propulsion and Power

Nanosecond-pulsed surface dielectric barrier discharge plasma actuators are used to control shock-wave/ boundary-layer interactions. Characterization of the separation region without plasma actuation is conducted to understand the interaction based on measurements of pressure distribution, schlieren imaging, and velocimetry by the femtosecond laser electronic excitation tagging technique. The results show a weak separation due to the interaction. Three types of plasma actuators are applied to control the separation. Schlieren images are taken by a high-speed camera to evaluate the magnitude of the interaction. It is shown that the plasma actuators affect the flow in two different ways: heat generation in the boundary layer, and generation of vorticity near the surface.When the first effect is dominant, the shock-wave/boundary-layer interaction becomes stronger and the size of the separation bubble increases. If the vorticity generation prevails, it suppresses the separation due to the momentum transfer from the main flow to the boundary layer. The experimental results of the three actuator's geometries provide the design guidelines for nanosecond-pulse-driven electrodes to control the interaction.An optimal actuation frequency is found through an investigation of the frequency response of the flow.

DOI： 10.2514/1.B36530

微小重力環境下における極低温二相流のボイド率計測査読有り

小林弘明, 小林弘明, 坂本勇樹, 杵淵紀世志, 佐藤哲也

日本航空宇宙学会論文集 66 巻 ( 6 ) 頁： 147‐152(J‐STAGE) - 152 2018年

記述言語：日本語掲載種別：研究論文（学術雑誌）出版者・発行元：一般社団法人日本航空宇宙学会

Reducing the amount of propellant for re-cooling is an important issue for the rocket propulsion system using cryogenic fuel. Immediately after the start of the engine, the liquid fuel boils and becomes two-phase flow. In the state of two-phase flow, the void fraction, which is the gas-liquid ratio, is one of the important value for flow control. For above problem, we are developing void fraction measurement system for the cryogenic fluid. These devices were attached to the S310-43 sounding rocket for the purpose of "measuring two-phase flow behavior and heat transfer characteristics during coasting flight." These devices withstood the vibration shock test of 40G and succeeded to measure the void fraction of liquid/gas nitrogen two phase flow under vacuumed and microgravity circumstance. This report explains development and experiment results of the void fraction sensor and a capacitance amplifier.

DOI： 10.2322/jjsass.66.147

200W級ホールスラスタの開発査読有り

長野公勇, 森田太智, 山本直嗣, 窪田健一, 藤井剛, 杵淵紀世志

プラズマ応用科学 25 巻 ( 2 ) 頁： 85‐88 - 88 2017年

記述言語：日本語掲載種別：研究論文（学術雑誌）出版者・発行元：宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)

令和元年度宇宙輸送シンポジウム（2020年1月16日-17日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県資料番号: SA6000147068レポート番号: STEP-2019-019

DOI： 10.34377/aps.25.2_85

全電化衛星の世界動向査読有り

杵淵紀世志, 杵淵紀世志

日本航空宇宙学会誌 65 巻 ( 9 ) 頁： 274‐279(J‐STAGE) - 279 2017年

記述言語：日本語掲載種別：研究論文（学術雑誌）出版者・発行元：一般社団法人日本航空宇宙学会

全電化静止衛星では推進系としてイオンエンジン，ホールスラスタ等の電気推進のみを搭載し，軌道保持のみならず軌道上昇も電気推進にて行う．これにより従来の化学推進系に比して，長い遷移期間を要するものの大幅に搭載推薬量を削減することができる．2015年，米にて世界初の全電化静止衛星が打上げられ，イオンエンジンによる約半年間の軌道上昇後，静止軌道に到達した．これに追従すべく，各国で全電化静止衛星およびそれに搭載される電気推進の研究開発が活発化している．ホールスラスタはその高推力電力比により3～4カ月程度の短期間遷移を実現でき，さらに低コスト，ロバスト等の特徴も有し，全電化衛星向け電気推進の最有力候補とされる．本稿では全電化静止衛星の世界動向を俯瞰するとともに，全電化衛星への搭載が計画されているホールスラスタの開発動向についても概説する．

DOI： 10.14822/kjsass.65.9_274

Prediction of in-flight radio frequency attenuation by a rocket plume 査読有り

Kinefuchi K., Okita K., Funaki I., Abe T.

Journal of Spacecraft and Rockets 52 巻 ( 2 ) 頁： 340 - 349 2015年3月

担当区分：筆頭著者記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）出版者・発行元：Journal of Spacecraft and Rockets

During rocket flights, ionized exhaust plumes from solid rocket motors may interfere with radio frequency transmission under certain conditions. A computational fluid dynamics and finite difference time-domain method coupling approach was established for predicting interference and radio frequency attenuation levels during an actual rocket flight. The detailed plasma flowfield and radio frequency transmission characteristics were revealed in the calculations. The calculated far-field received levels were compared with the in-flight attenuation data at different look angles (angles between the vehicle axis and the line of sight of the antennas), and the calculated results showed good agreement with the flight data over a wide range of look angles. An adaptation of the model, based on the diffraction theory, proved appropriate both for rough estimation of attenuation and for conducting a preliminary analysis of signal/rocket plume interactions.

DOI： 10.2514/1.A32957

ロケット慣性飛行中の二相流挙動および熱伝達特性の観測実験~実験装置部の開発~ 査読有り

小林弘明, 杵淵紀世志, 更江渉, 梅村悠, 藤本圭一郎, 薮崎大輔, 杉森大造, 姫野武洋, 佐藤哲也, 北古賀智史, 角悠輝, 坂本勇樹, 野中聡, 藤田猛

日本航空宇宙学会論文集 63 巻 ( 5 ) 頁： 188-196 (J-STAGE) - 196 2015年

記述言語：日本語掲載種別：研究論文（学術雑誌）出版者・発行元：一般社団法人日本航空宇宙学会

The Japan Aerospace Exploration Agency launched the S-310-43 sounding rocket from the Uchinoura Space Center on Aug.04, 2014 for the purpose of investigating such behavior as boiling and flow of cryogenic liquid rocket propellant in an environment simulating coasting flight on orbit by using the sounding rocket's sub-orbital ballistic flight. In the low-gravity state, the cryogenic fluid (liquid nitrogen) was introduced into the test sections of similar shapes to the flow channels in the cryogenic propulsion systems. The boiling of liquid nitrogen inside the test-sections and the transition of flow regimes from gas/liquid two-phase flow to liquid mono-phase flow were visualized. The temperatures, pressures and void fractions of each channels were measured as well. Development of the experimental equipment for S-310-43 sounding rocket is described in this paper.

DOI： 10.2322/jjsass.63.188

Technical Challenges for Advanced Arcjets 査読有り

NAKATA Daisuke, KINEFUCHI Kiyoshi, HOSODA Satoshi, KINOSHITA Masahiro, KUNINAKA Hitoshi

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 12 巻 ( ists29 ) 頁： To_1_1 - To_1_5 2014年

記述言語：英語掲載種別：研究論文（学術雑誌）出版者・発行元：一般社団法人日本航空宇宙学会

Next generation arcjets should have light-weight design and prolonged lifetime. For the former topic, it is shown that the radiator mass can be drastically reduced by the effective use of propellant as a coolant at the lower temperature region on the radiator. Resulting thruster weight of 2.0 kg including the radiator is possible for 15 kWe arcjet. For the latter topic, replaceable cathode system is proposed and some key issues are mentioned.

DOI： 10.2322/tastj.12.to_1_1

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