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1. Evaluation of Ionization Efficiency in a Carbon Dioxide Hall Thruster by 0-D Discharge Simulation

Author

Tokuda, Shu, Cho, Shinatora, Watanabe, Hiroki, Ohkawa, Yasushi, Matsui, Makoto, Kacprzyk, Janusz, Series Editor, Gomide, Fernando, Advisory Editor, Kaynak, Okyay, Advisory Editor, Liu, Derong, Advisory Editor, Pedrycz, Witold, Advisory Editor, Polycarpou, Marios M., Advisory Editor, Rudas, Imre J., Advisory Editor, Wang, Jun, Advisory Editor, Ono, Yukinori, editor, and Kondoh, Jun, editor

Published
2024
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2. Effects of Magnetic Field Configuration on the Performance of 100 W-Class Hall Thruster Using Carbon Dioxide

Author

Tsuchikawa, Seiya, Watanabe, Hiroki, Cho, Shinatora, Ohkawa, Yasushi, Matsui, Makoto, Kacprzyk, Janusz, Series Editor, Gomide, Fernando, Advisory Editor, Kaynak, Okyay, Advisory Editor, Liu, Derong, Advisory Editor, Pedrycz, Witold, Advisory Editor, Polycarpou, Marios M., Advisory Editor, Rudas, Imre J., Advisory Editor, Wang, Jun, Advisory Editor, Ono, Yukinori, editor, and Kondoh, Jun, editor

Published
2024
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4. Plume mode instability enhanced by emitter surface poisoning in hollow cathode.

Author

Suzuki, Atsuya, Cho, Shinatora, Watanabe, Hiroki, and Kinefuchi, Kiyoshi

Subjects
*CATHODES, *ELECTRON work function, *PLASMA instabilities, *ELECTRON emission, *PLASMA stability, *GLOW discharges, *ELECTRON temperature, *FIELD emission
Abstract

The unstable plume mode of hollow cathodes should be avoided in practical applications because it severely degrades the overall cathode lifetime. In this study, we investigate the spot-plume transition and plasma stability characteristics of an unused segmented lanthanum hexaboride emitter. The expansion of the unstable plume mode region is observed during a discharge experiment. Subsequently, the segmented emitter is retrieved, the inner surface of the emitter is observed, and the work function on the surface is measured at room temperature. The emitter surface exhibits color variations with oxygen and carbon detection. The downstream edge shows the original purple color and almost no degradation in the work function. The high temperature in this region promotes the desorption of carbon and oxygen. In the spot mode, this region mainly contributes to thermionic electron emission; therefore, the discharge voltage in the spot mode does not change during the discharge experiment. Carbon or carbide is detected in the middle of the axial direction on the emitter surface, where the surface temperature is not sufficiently high to desorb carbon during discharge. Based on the surface analysis results, the dominant substance in the region where carbon is detected was lanthanum carbide. An increase in the work function is indicated in the region, which appears to increase the plasma instability. According to previous studies, an increase in the work function results in a rise in the potential in the emitter, and an increase in the electron temperature in the outside plume region induces the plasma instability. Further investigation is needed to understand the mechanism connecting the rise in the work function and the rise in the electron temperature in the plume region. [ABSTRACT FROM AUTHOR]

Published
2024
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6. Dry ice propellant for electric propulsion with triple-point storage

Author

Maki, Tatsuro, Kinefuchi, Kiyoshi, Cho, Shinatora, Watanabe, Hiroki, Maki, Tatsuro, Kinefuchi, Kiyoshi, Cho, Shinatora, and Watanabe, Hiroki

Abstract

Dry ice has been proposed as a propellant for electric propulsion, as its use may facilitate the realization of a low-cost propulsion system compared to that based on a xenon propellant. In addition, dry ice can be obtained from space (e.g., from the atmosphere of Mars) and human exhalation. This study thus conducted experiments with dry ice storage and carbon dioxide gas supply using triple-point storage. With this method, a constant tank pressure and flow rate was achieved without the application of regulators or control valves. However, the triple-point state was unexpectedly halted, even though solid dry ice remained in the tank. An internal visual observation revealed that the solid phase was surrounded by the liquid phase, which prevented the solid phase from melting. Therefore, heat conduction fins were installed in the tank to enhance the melting process, which successfully extended the triple-point duration. The supply system was applied successfully to the operation of a 1 kW Hall thruster. Furthermore, a mathematical model for estimating the phase characteristics in the tank was developed, with an in-orbit operation analyzed based on the experimental results. The heat input to the tank and the mass flow rate or enthalpy to the thruster determined the phase characteristics in the tank, which means that implementing a thermal design that considers the flow rate to the thruster is crucial. The simulation demonstrated that dry ice can be consumed by controlling the three phases in the tank using an electrical heater. A gas phase separator concept consisting of the heat conduction fins and capillary screen mesh was proposed for orbital microgravity operation.

Published
2025

9. Energetic ion and plasma oscillation measurements during plume mode operation of a hollow cathode

Author

Suzuki, Atsuya, Kinefuchi, Kiyoshi, Ichihara, Daisuke, Cho, Shinatora, Watanabe, Hiroki, Kubota, Kenichi, Suzuki, Atsuya, Kinefuchi, Kiyoshi, Ichihara, Daisuke, Cho, Shinatora, Watanabe, Hiroki, and Kubota, Kenichi

Abstract

Hollow cathodes are important devices used for spacecraft electric propulsion. The hollow cathode has two operational modes. One mode is a stable mode called the spot mode, and the other is an unstable mode called the plume mode. Operation in plume mode should be avoided since the instability causes high-energy ions that sputter-erode the cathode parts. In this study, the relationship between discharge oscillations and ion energy distribution in plume mode was investigated using a triple Langmuir probe and retarding potential analyzer for a 40-A class xenon hollow cathode with a lanthanum hexaboride emitter. The triple probe can measure unsteady electron temperature and plasma density oscillations. The electron temperature was not so high, 1 to 2 eV. Some instabilities were observed in the plume mode. The ionization instability with a low frequency oscillation of 30 kHz was the dominant mode. A broad spectrum around 330 kHz due to ion acoustic turbulence was observed. In addition, in the downstream plume region, oscillations around 120 kHz were observed owing to temporal change in anomalous resistivity. The 95% ion population voltage found to be 20 and 30 eV in spot and plume modes, respectively. The magnitude of the low frequency ionization oscillation was found to be inversely proportional to ion energy in plume mode. This indicates that the resonant energy transfer from the oscillation to the ion energy through Landau damping probably plays an important role in high energy ion generation in plume mode. A clear correlation between discharge current and electron temperature waveforms was found. The larger the electron temperature fluctuation, the stronger the correlation between discharge current and electron temperature, and the larger the phase difference deviation from 180°.

Published
2024

16. 電気推進搭載衛星による能動的デブリ除去技術の開発: デブリ捕獲シーケンスにおけるターゲットデブリの帯電緩和

Author

MURANAKA, Takanobu, CHO, Shinatora, OKUMURA, Teppei, and OKAWA, Yasushi

Abstract

第10回スペースデブリワークショップ (2022年11月28-30日. 主催: 宇宙航空研究開発機構研究開発部門(JAXA), 宇宙航空研究開発機構調布航空宇宙センター(JAXA)(CAC)), 調布市, 東京, The 10th Space Debris Workshop (November 28-30, 2022. Organizer: Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA), Chofu Aerospace Center, Japan Aerospace Exploration Agency (JAXA)(CAC)), Chofu, Tokyo, Japan, 混雑軌道における大型デブリの能動的除去（ADR）は，今後100 年にわたりスペースデブリの増加を抑制する有力な手法であると考えられている．JAXA では，混雑軌道に存在する大型デブリの除去技術のひとつとして，電気推進搭載衛星によるデブリの軌道遷移を提案し，実用化に向けた研究を進めている．軌道上のデブリとデブリ除去衛星は，宇宙環境プラズマによって各々が帯電すると考えられるが，両者に電位差がある場合，デブリ除去衛星がデブリを捕獲する際に放電事故が発生する可能性がある．とくに，これらが極域にあるときkeV オーダの高エネルギーをもつオーロラ電子に暴露され，帯電の絶対値も増加する．そこで，本研究では極軌道における宇宙機帯電の最悪ケースを想定し，プラズマシミュレーションでデブリ除去衛星の電気推進から放出される熱的イオンの挙動解析を実施し，ターゲットデブリに流入するイオン電流と，環境プラズマ電流とを比較し，デブリの帯電緩和を評価した．, Active debris removal (ADR) of large-scale debris is expected to suppress number of space debris in next 100 years. An ADR method is proposed by JAXA using electric propulsion to deorbit large-scale debris existing in congestion orbit. To prevent charging-arcing failure for deorbiting satellite at the debris capturing moment, we numerically studied charging mitigation by thermal ions produced in Hall thruster plasma plume on the target debris in polar orbit which is exposed by high-energy auroral electrons. In a debris capture sequence that the satellite approaches to the target from the direction of orbital motion of the target, it was obtained that the target debris could have a potential of ¬–100 V to that of the satellite due to lower incoming orbital ions compared to the satellite. Also, we obtained that thermal ions which were produced in the thruster plasma plume diffused toward the target debris and could mitigate the negative charging on the debris, although equivalent potential to the satellite could not be achieved in this case., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2230027005

Published
2023

17. JAXAにおける1kW級小型ホールスラスタシステム（ν800）の研究活動

Author

CHO, Shinatora

Abstract

令和4年度宇宙輸送シンポジウム（2023年1月12日-13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, Space Transportation Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA60001840109, STEP-2022-059

Published
2023

18. Operational demonstration of propellant supply system using dry ice as propellant in a vacuum environment

Author

NOSAKA, Shunsuke, KINEFUCHI, Kiyoshi, CHO, Shinatora, and WATANABE, Hiroki

Abstract

令和4年度宇宙輸送シンポジウム（2023年1月12日-13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, Space Transportation Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, Dry ice is proposed as an alternative to xenon, which is currently widely used as a propellant for electric propulsion, due to its overwhelmingly lower price. Furthermore, by storing CO2 in a triple point, it can be stored at low pressure and supplied to the propellant at a constant flow rate. A mathematical model has been developed to determine the phase characteristics in the tank, which are determined by the heat input to the tank and the propellant flow rate. In the mathematical model, the liquid phase decreases with propellant supply during on-orbit operation, and the triple point is finished. Therefore, an experiment was conducted in which the tank was placed in a vacuum and the propellant was discharged to compare with the mathematical model. In the experiment, when the propellant was discharged more than 147 sccm at 2W heat input, the pressure dropped along the vapor-liquid equilibrium line. In the mathematical model, the liquid phase decreases when discharging more than 110 sccm at 2W heat input, and this comparison shows that there is a difference of about 28% from the experimental value., 所属の誤記: The University of Nagoya, 資料番号: SA6000184055, STEP-2022-003

Published
2023

19. デブリ除去に向けた1kW級ホールスラスタシステムの研究開発

Author

CHO, Shinatora, WATANABE, Hiroki, MATSUNAGA, Yoshiki, TSUKIZAKI, Ryudo, OHKAWA, Yasushi, KONDO, Hiromasa, KUSAWAKE, Hiroaki, and YAMAMOTO, Toru

Abstract

第9回スペースデブリワークショップ (2021年2月24-26日. 宇宙航空研究開発機構調布航空宇宙センター(JAXA)(CAC), オンライン会議), 調布市, 東京, The 9th Space Debris Workshop (February 24-26, 2021. Chofu Aerospace Center, Japan Aerospace Exploration Agency (JAXA)(CAC), Online meeting), Chofu, Tokyo, Japan, JAXA では商業デブリ除去実証やその先のデブリ除去事業等を目指し、1kW 級ホールスラスタの研究開発を進めている。500 キログラム級の衛星により、数トン級のデブリの除去を実施するためには、MNs 級のトータルインパルスと、高い比推力が要求されるため電気推進の利用が望ましく、中でも推力電力比が高くミッション期間の制約を満たしやすいことから、1kW 級ホールスラスタが最有力候補と考えられる。ただし、同電力帯の既存ホールスラスタは一般に寿命が短く不足するため、JAXA では技術試験衛星9 号機で実証される長寿命ホールスラスタ技術をベースとして、低コスト長寿命な小型ホールスラスタシステムの実現を目指している。ホールスラスタヘッドや中和器だけでなく、電源や流量制御器を含めた推進システムとしての研究開発状況を報告する。, JAXA is conducting R&D on a 1kW-class Hall thruster system for active debris removal. The Commercial Removal of Debris Demonstration (CRD2) phase II mission target is several tons of weight, which requires MNs-class of total impulse and high-specific impulse to accomplish. In addition, mission duration is also important from a commercial perspective. Therefore, electric propulsion, especially Hall thruster is the first candidate because of its relatively high thrust-to-power ratio. Since life-limit is challenging for conventional small Hall thrusters, JAXA is targeting low-cost long-life 1kW-class Hall thruster system, utilizing technologies to be demonstrated on JAXA ETS-9 satellite. Research and development status of the system is reported., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2130003034, レポート番号: JAXA-SP-21-001

Published
2021

20. Control Algorithm for 6 kW Hall Thruster

Author

Matsunaga, Yoshiki, primary, Watanabe, Hiroki, additional, Cho, Shinatora, additional, Funaki, Ikkoh, additional, Kusawake, Hiroaki, additional, Kajiwara, Kazuhiro, additional, Kurokawa, Fujio, additional, and Takahashi, Toru, additional

Published
2022
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22. Effects of Cathode Type and Position on Thrust Performance of 1-kW Class Hall Thruster

Author

WATANABE, Hiroki, CHO, Shinatora, MATSUNAGA, Yoshiki, and TSUKIZAKI, Ryudo

Abstract

令和3年度宇宙科学に関する室内実験シンポジウム（2022年2月28日-3月1日. オンライン開催), 2022 Symposium on Laboratory Experiment for Space Science (February 28-March 1, 2022. Online Meeting), 資料番号: SA6000178002, レポート番号: 2

Published
2022

24. Two-photon absorption laser induced fluorescence with various laser intensities for density measurement of ground state neutral xenon

Author

Chng, Tat Loon, Kinefuchi, Kiyoshi, Nunome, Yoshio, Cho, Shinatora, and Tsukizaki, Ryudo

Subjects
020301 aerospace & aeronautics, Materials science, Ion thruster, Aerospace Engineering, chemistry.chemical_element, 02 engineering and technology, Laser, 01 natural sciences, Two-photon absorption, law.invention, Xenon, 0203 mechanical engineering, chemistry, law, Ionization, Metastability, 0103 physical sciences, Atomic physics, Ground state, Laser-induced fluorescence, 010303 astronomy & astrophysics
Abstract

Accepted: 2019-03-05, 資料番号: SA1190046000

Published
2019

25. 大型ホールスラスタ用真空装置の整備と運転状況

Author

JAXAホールスラスタ研究開発チーム, Cho, Shinatora, and JAXA Hall Thruster R&D Team

Abstract

第16回試験技術ワークショップ (2018年11月28日. 宇宙航空研究開発機構筑波宇宙センター), つくば市, 茨城, 16th Workshop on Environmental Testing (November 28, 2018. Tsukuba Space Center, Japan Aerospace Exploration Agency (JAXA)), Tsukuba, Ibaraki, Japan, 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1830022004, レポート番号: JAXA-SP-18-010

Published
2019

28. 1kW級ホールスラスタの放電特性に対する陰極種類と位置の影響

Author

WATANABE, Hiroki, CHO, Shinatora, MATSUNAGA, Yoshiki, TSUKIZAKI, Ryudo, and OHKAWA, Yasushi

Abstract

令和2年度宇宙科学に関する室内実験シンポジウム（2021年3月5日. オンライン開催), 2021 Symposium on Laboratory Experiment for Space Science (March 5, 2021. Online Meeting), 資料番号: SA6000161015, レポート番号: 15

Published
2021

29. 1kW級ホールスラスタの100時間級作動試験と数値シミュレーション

Author

CHO, Shinatora, WATANABE, Hiroki, MATSUNAGA, Yoshiki, TSUKIZAKI, Ryudo, and OHKAWA, Yasushi

Abstract

令和二年度宇宙輸送シンポジウム（2021年1月14日-15日. オンライン開催), Space Transportation Symposium FY2020 (January 14-15, 2021. Online Meeting), 資料番号: SA6000160059, レポート番号: STEP-2020-021

Published
2021

30. International Space Exploration Scenario (Transportation Architecture) of JAXA

Author

NARITA, Shinichiro, IKENAGA, Toshinori, KINEFUCHI, Kiyoshi, CHO, Shinatora, IDEHARA, Toshihiro, MORITO, Toshiki, SAKAGUCHI, Takefumi, MIYAKITA, Takeshi, UMEMURA, Yu, FURIHATA, Hiroki, IKEDA, Naofumi, WADA, Masaru, SEKIYA, Yuta, HOSHINO, Takeshi, KOGA, Masaru, NAKAJIMA, Jun, and SATO, Naoki

Subjects
Lunar Surface Exploration, Pressurized Rover, In-Situ Resource Utilization, Human Lunar lander
Abstract

第63回宇宙科学技術連合講演会 (2019年11月6日-8日. アスティとくしま), 徳島市, 徳島県, The 63rd Space Sciences and Technology Conference (November 6-8, 2019. ASTY Tokushima), Tokushima, Japan, 著者名の誤記: NAKJIMA,Jun, 形態: カラー図版あり, The clerical error of an author's name: NAKJIMA,Jun, Physical characteristics: Original contains color illustrations, 資料番号: AC2100001000, レポート番号: JSASS-2019-4705

Published
2020

35. External Discharge Plasma Thruster

Author

Karadag, Burak, Cho, Shinatora, Funaki, Ikkoh, Hamada, Yushi, and Komurasaki, Kimiya

Subjects
010302 applied physics, Physics, Fuel Technology, Space and Planetary Science, Mechanical Engineering, 0103 physical sciences, Aerospace Engineering, Plasma, Atomic physics, 01 natural sciences, 010305 fluids & plasmas
Abstract

Accepted: 2018-02-17, 資料番号: SA1180080000

Published
2018

36. New insights into electron transport due to azimuthal drift in a Hall effect thruster

Author

Hara, Kentaro, Yamashita, Yusuke, Tsikata, Sedina, Vincent, Benjamin, Mazouffre, Stéphane, Cho, Shinatora, Standford University, Department of Mathematics [Texas] (TAMU), Texas A&M University [College Station], The University of Tokyo (UTokyo), Institut de Combustion, Aérothermique, Réactivité et Environnement (ICARE), Université d'Orléans (UO)-Centre National de la Recherche Scientifique (CNRS)-Institut des Sciences de l'Ingénierie et des Systèmes (INSIS), Japan Aerospace Exploration Agency [Tokyo] (JAXA), and VINCENT, Benjamin

Subjects
[PHYS.PHYS.PHYS-PLASM-PH]Physics [physics]/Physics [physics]/Plasma Physics [physics.plasm-ph], [PHYS.PHYS.PHYS-PLASM-PH] Physics [physics]/Physics [physics]/Plasma Physics [physics.plasm-ph]
Abstract

International audience; Partially magnetized plasmas in the Hall effect thrusters remain poorly understood primarily due to the electron transport in the cross-field direction. It is recently discussed that the drift-diffusion approximation is invalid for the electron dynamics in the presence of a large drift velocity. It is therefore possible that the anomalous electron transport is strongly related with the presence of an azimuthal drift. In this paper, we discuss the importance of the azimuthal drift on cross-field electron transport based on some recent results from a one-dimensional particle-in-cell simulation, two-dimensional particle-in-cell simulation, and laser Thomson scattering measurements.

Published
2019

37. 100級小型ホールスラスタの2D全粒子シミュレーション

Author

Cho, Shinatora and Watanabe, Hiroki

Abstract

平成30年度宇宙輸送シンポジウム（2019年1月17日-18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, Space Transportation Symposium FY2018 (January 17-18, 2019. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000136095, レポート番号: STEP-2018-040

Published
2019

38. 低電力永久磁石型外部放電式ホールスラスタの地上評価実験

Author

Cho, Shinatora, Karadag, Burak, Oshio, Yuya, and Funaki, Ikkoh

Abstract

平成29年度宇宙科学に関する室内実験シンポジウム (2018年2月26日-27日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県, 2018 Symposium on Laboratory Experiment for Space Science (February 26-27, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000123016

Published
2018

39. 6kW級ホールスラスタの500時間耐久試験とシミュレーション

Author

Cho, Shinatora, Watanabe, Hiroki, Kubota, Kenichi, and Funaki, Ikkoh

Abstract

平成29年度宇宙輸送シンポジウム（2018年1月18日-19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, Space Transportation Symposium FY2017 (January 18-19, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000210124, レポート番号: STEP-2017-067

Published
2018

42. センターカソードを有するホールスラスタのHybrid-PIC解析

Author

Kubota, Kenichi, Funaki, Ikkoh, Cho, Shinatora, and Watanabe, Hiroki

Abstract

平成28年度宇宙輸送シンポジウム（2017年1月19日-20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, Space Transportation Symposium FY2016 (January 19-20, 2017. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000086055, レポート番号: STEP-2016-017

Published
2017

48. Initial Experiment Results of External Discharge Plasma Thruster

Author

Karadag, Burak, Cho, Shinatora, Oshio, Yuya, and Funaki, Ikkoh

Abstract

平成27年度宇宙科学に関する室内実験シンポジウム (2016年2月23日-24日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県, 2016 Symposium on Laboratory Experiment for Space Science (July 23-24, 2016. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000055014

Published
2016

49. ホールスラスタの推進性能に対するチャネル出口電位の影響

Author

Watanabe, Hiroki, Cho, Shinatora, Kubota, Kenichi, Fuchigami, Kenji, Tashiro, Yousuke, Iihara, Shigeyasu, and Funaki, Ikkoh

Abstract

平成27年度宇宙輸送シンポジウム（2016年1月14日-15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, Space Transportation Symposium FY2015 (January 14-15, 2016. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000050097, レポート番号: STEP-2015-033

Published
2016

50. ホローカソードのプラズマモデルにおけるグローバル感度解析

Author

Cho, Shinatora, Kubota, Kenichi, Watanabe, Hiroki, and Funaki, Ikkoh

Abstract

平成27年度宇宙輸送シンポジウム（2016年1月14日-15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, Space Transportation Symposium FY2015 (January 14-15, 2016. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000050069, レポート番号: STEP-2015-005

Published
2016

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