研究者業績

德留 真一郎

トクドメ シンイチロウ  (Shinichiro Tokudome)

基本情報

所属
国立研究開発法人宇宙航空研究開発機構 宇宙科学研究所 准教授
総合研究大学院大学 先端学術院 宇宙科学コース 准教授
学位
工学博士(1995年1月 東京大学)

J-GLOBAL ID
201701017821214557
researchmap会員ID
B000279353

主要な受賞

 10

主要な論文

 65
  • 徳留 真一郎, 丸 祐介, 野中 聡
    Space Policy 68 2024年6月13日  査読有り筆頭著者
    Highlights • Strategy formulated under Inter-University Research Institute System unique to Japan. • To develop a competitive space transportation system by using advanced technologies. • To “start small” for fulfilling our target to achieve innovations in human society. • “Fusion of transportation with exploration” in deep space exploration missions. • “Small flying test bed system” to conduct flying technology demonstrations. Abstract The Space Transportation System Committee of the Institute of Space and Astronautical Science (ISAS) of the Japan Aerospace Exploration Agency (JAXA) has been continuously formulating medium-to long-term strategies in the field of space transportation systems under the Inter-University Research Institute System of ISAS since FY2018. This committee is considering the role of ISAS in cooperation with the organization-wide activities of JAXA to formulate strategies in the field of space transportation systems. Among its previous achievements, the committee assembled a strategic target and scenario for the space transportation system research field at the end of FY2018 and has been continuously revising it. Based on the formulated mission scenario, the committee identified three priority areas related to system technologies that must be tackled. These are a “reusable orbit transportation system” aimed for highly frequent mass transportation from Earth to low Earth orbits, “deep space interorbital transportation system” aimed for a marked improvement in space science and exploration missions in terms of frequency and flexibility, and “small flying test bed system” for flight demonstrations, which is indispensable in the research and development of space transportation systems. In this paper, the authors summarize the medium-to long-term strategies and their concrete implementation measures over the next two decades. Keywords Strategic R&D, Space transportation system, Deep space exploration, Small flying test bed, Start small
  • MATSUI Kohei, MATSUURA Yoshiki, TOKUDOME Shinichiro, KITAGAWA Koki
    Journal of Evolving Space Activities 1 n/a 2023年6月  査読有り
    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.
  • Naoki MORISHITA, Yoshitaka MOCHIHARA, Satoshi ARAKAWA, Masashi MIURA, Yuki SAKAMOTO, Yoshiki MATSUURA, Masanori SAKAINO, Toshiaki TAKEMAE, Shinichi TAKEDA, Shinsaku HISADA, Hirotaka IGAWA, Shinichiro TOKUDOME, Takeshi TAKASHIMA
    The 34th International Symposium on Space Technology and Science 2023年6月  
    DESTINY+ requires a high-performance kick stage with a high mass ratio and high launch system safety. The kick stage requires a reliable laser ignition system, which is the subject of this study. Our development efforts included componentizing and dual redundancy elements, such as capacitors and laser diodes in the laser firing unit, which is designated LUUS. LUUS has two types of laser-initiated devices for motor ignition and separation device operation. An optical fiber path also enables a continuity check by an optical frequency domain reflectometry device. Further, we conducted continuity checks and laser ignition tests to validate the design in procedures simulating assembly- and launch-site operations. These tests successfully executed inspections and ignitions as planned. These results confirm the validity of our design, bringing us closer to realizing a reliable laser ignition system for launch operations applicable to DESTINY+. This contribution paves the way for future advances in high-performance, safe launch systems for solid rockets in space exploration.
  • Yoshiki MATSUURA, Koki KITAGAWA, Kohei MATSUI, Shinichiro TOKUDOME, Naoki MORISHITA
    The 34th International Symposium on Space Technology and Science 2023年6月  
    Laser-initiated ignition systems (LIISs) have been developed with the aim of providing essential immunity to electrical disturbances. In the basic configurations of such systems, the electric circuits for generating the laser and detonator signals are electrically separated by a non-conductive optical fiber, increasing the resistance to ignition stimuli other than laser light on the detonator side. In this study, the various environmental resistance tests required for the detonators currently used in rockets were conducted for a new laser-initiated detonator (LID). As all of the tests show results satisfying the requirements, it is considered that the LID has reached the stage of practical use.
  • Satoshi Hirakida, Hirohito Ohtsuka, Takamitsu Horiguchi, Naruhisa Sano, Koichiro Tani, Shinichiro Tokudome, Kensaku Tanaka
    The 34th International Symposium on Space Technology and Science 2023年6月  
    The S-520-RD1 was developed as a test-bed small launcher using the guidance and control system based on SS-520-5 for a cube-sat launcher and successfully launched a supersonic Combustion Tester on July 24, 2022. One of the key points of this launch success is the Rhumb-line control system to achieve the guidance target and the payload test conditions. This paper shows the outline of the guidance and control system and their development, and the flight results.
  • Kouichiro Tani, Masao Takegoshi, Koichi Takasaski, Shinichiro Tokudome
    25th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2023年5月  
    To reduce the cost of space transportation, JAXA continues studying fully reusable space transporters with hypersonic airbreathing engines. To fulfill the requirement of acceleration capability from zero to hypersonic speed, the rocket-based combined cycle (RBCC) engine is one of the promising candidates and has been studied in JAXA Kakuda Space Center. In the researches of the engine, the specialized wind tunnel for the airbreathing engines (Ramjet Engine Test Facility, RJTF) has been always a practical tool to investigate the performance and detailed flow phenomena inside the engine. However, to simulate the hypersonic, high enthalpy flow, the wind tunnel uses gas hydrogen and oxygen to heat the flow, resulting the air contamination by water which affects to the combustion phenomenon. To clarify the effect of the contamination, series of the cooperative researches have been conducted in JAXA and universities. The final goal of the researches are to create the adjustment tools for contamination effects, which ensure more accurate estimation for the performances of engine in the real flight. For validating the tools, the real flight data are quite essential. In the researches, a flight experiment had been also planned to get combustion data during hypersonic flight to compare the results in the wind tunnel and estimated values by the tools. In this report, the flight experiment with “S-520-RD1” is described. In early phase of the development, several rocket systems, flight trajectories and flight test bed configurations were explored. For the experiment, the attitude control of the flight test bed was required and it was achieved by the rhumb line device. The flight conditions inwhich actual combustion experiment was conducted were determined by the air data system specifically designed and integrated into the test bed. The duration time for the combustion test reached as long as 5.8 sec, with highest Mach No. of 5.8. The summery of the results of combustion test is also presented.
  • Yuichiro Ide, Yu‐ichiro Izato, Mitsuo Koshi, Atsumi Miyake, Hiroto Habu, Shinichiro Tokudome
    Propellants, Explosives, Pyrotechnics 48(2) 2023年2月  査読有り最終著者
    The ammonium dinitramide-based ionic liquid propellant (ADN-based ILP), which is a mixture of ADN, monomethylamine nitrate (MMAN), and urea, is a low toxic monopropellant with a higher performance than that of hydrazine. To clarify the combustion wave structure of ADN-based ILP, which has low volatility, we focused on the relationship between the phase state and temperature in ADN-based ILP combustion and on clarifying the gas-liquid phase reaction. The combustion still image and temperature distribution of ADN-based ILP were obtained by strand burning tests with a high-speed camera. As a result, two stages of the stable temperature region were found in the gas-liquid phase. The pressure dependences of temperature in the stable temperature region were compared with the vapor pressure curves of some chemical substances and with the decomposition temperatures of ADN, MMAN, and urea. Then, it was inferred that the thermal decompositions of ADN, MMAN, and urea, as well as the evaporation of urea had occurred at the first stage of the stable temperature region. Also, it was found that the liquid ammonium nitrate had been dissociated at the second stage of the stable temperature region. For a report on the existence of dissociation products of MMAN and urea vapor on the burning surface at 1.2 MPa, the dissociation of MMAN and evaporation of urea would occur at the first stage of the stable temperature region at 1.2 MPa. As stated above, the combustion wave structure of ADN-based ILP was developed at 1.2 MPa.
  • Y. Matsuura, K. Nitta, H. Ikeda, M. Kinoshita, K. Ui, S. Tokudome, and K. Hori
    AIAA SCITECH 2023 Forum 2023年1月19日  
  • 徳留 真一郎
    第5回観測ロケットシンポジウム 2023年  招待有り筆頭著者責任著者
    宇宙科学研究所(ISAS)の宇宙輸送系専門委員会において策定されている宇宙科学・探査分野における宇宙輸送系の中長期ミッションシナリオでは,2040年頃の達成を目指すミッションを「多様な宇宙科学の世界をカバーする軌道間輸送ネットワークを構築する」ことと設定している. ミッション達成に向けて,地上から地球周回軌道へ高頻度に大量の物資や人員を輸送する宇宙往還機を実現するためには,往還飛行において「極超音速飛行」を避けることはできない.本稿では,主に宇宙往還機の実現と競争力向上に資する極超音速エンジンの技術実証を中心に,極超音速飛行に係る技術課題に実証的に取り組むための飛行実験機の目的と検討例について紹介する.
  • Shinichiro Tokudome, Yusuke Maru, Satoshi Nonaka
    73rd International Astronautical Congress (IAC), Paris, France, 18-22 September 2022. 2022年9月20日  筆頭著者責任著者
    The Space Transportation System Committee of the Institute of Space and Astronautical Science of JAXA (ISAS/JAXA) continuously draws up the Medium- to long-term strategy for the research field of space transportation system in ISAS/JAXA since FY2018. The committee is also considering about an ISAS’ role in JAXA in cooperation with a JAXAs organization-wide activity to formulate strategy for the space transportation system field in JAXA. The strategy planning in ISAS/JAXA was begun with the three documents as the point of departure; ”Long-term Vision for Space Transportation System” established by the space policy committee of the Cabinet Office, ”ISAS’ Missions”, and ”Strategic Scenario over the Next Medium- to Long-term Programs for the research field of Space and Astronautical Science” drawn up by the ISAS. As current achievements, the committee have drawn up a strategic target and scenario for the space transportation system research field at the end of last fiscal year and is continuously revising it. Based on the scenario formulated, the committee identified three major research field to be tackled. They are ”reusable orbit transportation system” becoming the key to the activation of space development and utilization, ”inter-orbit and interplanetary transportation systems” effectively supporting deep space explorations, and ”small flying test bed system” promoting the advancement of space transportation system technology. The authors introduce the summary of the medium- to long-term strategy and some medium-term research activities toward the realization of it.
  • 徳留真一郎
    航空原動機・宇宙推進講演会講演論文集(CD-ROM) ROMBUNNO.2A15 2022年  筆頭著者責任著者
  • Keisuke MINAMI, Yoshiki MATSUURA, Koki KITAGAWA, Satoshi ARAKAWA, Naoki MORISHITA, Toshiaki TAKEMAE, Shota IWABUCHI, Asato WADA, Shinichiro TOKUDOME
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19(5) 807-811 2021年  査読有り
    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.
  • Shinichiro TOKUDOME, Tsuyoshi YAGISHITA, Ken GOTO, Naohiro SUZUKI, Takayuki YAMAMOTO, Yasuhiro DAIMOH
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19(2) 186-192 2021年  査読有り筆頭著者責任著者
  • Matthew P. Richardson, Hiroaki Kobayashi, Yuki Sakamoto, Yusuke Maru, Shinichiro Tokudome, Satoshi Nonaka, Shujiro Sawai, Akira Oyama, Daisaku Masaki, Satoshi Takada, Hiromitsu Kakudo, Toru Kaga, Kiyoshi Kinefuchi, Tetsuya Sato
    Accelerating Space Commerce, Exploration, and New Discovery conference, ASCEND 2021 2021年  
    The Japan Aerospace Exploration Agency, in partnership with academia and industry, are developing the Air Turbo Rocket for Innovative Unmanned Mission (ATRIUM) engine: an air turboramjet + rocket combine cycle propulsion system intended to replace conventional liquid rocket engines in Vertical Takeoff Vertical Landing applications, such as reusable sounding rockets. A subscale Flight Test Bed (FTB) vehicle is also being developed to demonstrate the ATRIUM engine in a flight environment. In this paper, the ATRIUM engine and FTB vehicle are introduced, and current progress in their development is summarized. Future test plans and practical applications are also discussed.
  • Shinichiro Tokudome, Ken Goto, Tsuyoshi Yagishita, Naohiro Suzuki, Takayuki Yamamoto
    AIAA Propulsion and Energy 2019 Forum 2019年8月19日  筆頭著者責任著者
  • YAMASHIRO Ryoma, TOKUDOME Shinichiro, SAITOH Yasuhiro, YAMAMOTO Takayuki, MOCHIHARA Yoshitaka, IKAIDA Hiroki
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 17(2) 160-164 2019年  査読有り
    <p>A new space transportation system with an expendable solid-fuel booster and a reusable liquid-fuel orbiter is under consideration as part of activities in JAXA to construct a fully reusable space transportation system in the future. This paper shows this new system's conceptual study results, the system specifications, the new technology to be applied, the requirements to the subsystems, and the prospects.</p>
  • 井出雄一郎, 高橋拓也, 岩井啓一郎, 野副克彦, 羽生宏人, 徳留真一郎
    宇宙航空研究開発機構研究開発報告 JAXA-RR-(Web) (17-008) 2018年  査読有り最終著者
  • 井出雄一郎, 高橋拓也, 岩井啓一郎, 野副克彦, 羽生宏人, 徳留真一郎
    宇宙航空研究開発機構研究開発報告 JAXA-RR- (15-004) 2016年  査読有り最終著者
  • Tetsuya Ono, Shinichiro Tokudome, Ryoma Yamashiro, Takayuki Yamamoto, Hiroshi Ikaida, Yasuhiro Saito
    Proceedings of the International Astronautical Congress, IAC 2016年  
    Copyright © 2016 by the International Astronautical Federation. All rights reserved. Although reusable launch vehicle's necessity and significance, being cost-effective, eco-friendly and reliable, have been recognized in a long time, practical system still has never been realized except the Space Shuttle. There are two main reasons in this. One reason is that reusable vehicle's recurring cost is high. The other reason is that reusable vehicle, especially that upper stage, have the problem of aerodynamic heating during re-entry. We are considering new upper stage reusable launch vehicle with solid rocket booster, which clear these problems concerning reusable launch vehicle. For the first problem on the recurring cost, the application of the auto inspection system which is cultivated in solid rocket motor's development and launch operation is being considered. That is expected to reduce the inspection cost drastically after the vehicle flight. For the second problem on the re-entry, challenging technologies are applied in the upper stage. Those are material and structure with heat tolerance and lightness, active-cooling system to share the hydrogen with the liquid propulsion system, advanced guidance and control system, and so on. On the other hand, to the lower stage or booster, application of solid rocket is considered. Since the challenging upper stage's size is expected to vary through the iteration of design cycles, the lower stage should be stable and flexible with the thrust level in development phase. Because solid motors of various sizes are developed in JAXA/ISAS since the first small solid motor started to be developed in 1954, those development method has been efficiently accumulated. Then this legacy's utilization for the new system is expected to be quite beneficial. On these technological backgrounds, this paper describes the system study for new upper-stage reusable launch vehicle with the solid rocket booster.
  • IDE Yuichiro, TAKAHASHI Takuya, IWAI Keiichiro, NOZOE Katsuhiko, HABU Hiroto, TOKUDOME Shinichiro
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 14(ists30) Pa_89-Pa_94 2016年  査読有り最終著者
    <p>As a replacement for hydrazine, ammonium-dinitramide-based ionic liquid propellant (ADN-based ILP) has been developed by JAXA and Carlit Holdings Co., Ltd. This propellant is made by mixing three solid powers: ADN, monomethylamine nitrate, and urea. The propellant's theoretical specific impulse is 1.2 times higher than that of hydrazine, and its density is 1.5 times higher at a certain composition. Although ionic liquids were believed to be non-flammable for a long time owing to their low-volatility, recently combustible ILs have been reported. The combustion mechanism of ILs is not yet understood. The objective of this paper is to understand the combustion wave structure of ADN-based ILP. The temperature distribution of the combustion wave in a strand burner test shows a region of constant temperature. This region would indicate boiling in a gas-liquid phase. Thus, the combustion wave structure consists of liquid, gas-liquid, and gas phases. The dependence of boiling point on pressure would identify chemical substances in the gas-liquid phase. The dependence of combustion and ignition characteristics on ADN content is also discussed. </p>
  • Tsutsumi Seiji, Ishii Tatsuya, Ui Kyouichi, Tokudome Shinichiro, Wada K
    Journal of Spacecraft and Rockets 52(2) 350-361 2015年3月  査読有り
    資料番号: PA1510016000
  • Yuichiro Ide, Takuya Takahashi, Keiichiro Iwai, Katsuhiko Nozoe, Hiroto Habu, Shinichiro Tokudome
    Procedia Engineering 99 332-337 2015年  査読有り最終著者
  • MORITA Yasuhiro, IMOTO Takayuki, TOKUDOME Shinichiro, OHTSUKA Hirohito
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 12(29) Tg_21-Tg_28 2014年  査読有り
    The development of the Epsilon launch vehicle, Japan's next generation solid rocket launcher, has just moved to the final stretch for its first launch scheduled in the summer of 2013 to carry the planetary telescope satellite SPRINT-A. The JAXA appreciates the advantages of combined benefits of the standardized small satellites and the Epsilon's highly efficient launch system in order to increase the level of space activities. The primary purpose of Epsilon is to provide small satellites with a responsive launch that means "Small, Low cost, Fast and Reliable". The attention should be directed toward the innovative design concept of Epsilon, which aims at developing the next generation technologies such as the highly intelligent autonomous checkout system and the mobile launch control. Now that the full-scale development is about to be finished, the most important is what the next step should be beyond the Epsilon. This paper deals with the significance of the Epsilon launch vehicle and how it contributes to the possible evolution of future space transportation systems.
  • 徳留 真一郎, 井元 隆行, 森田 泰弘
    溶接学会誌 83(3) 215-219 2014年  査読有り招待有り筆頭著者責任著者
  • Shinichiro Tokudome, Hiroto Habu, Kyoichi Ui, Fumio Shimizu, Yusaku Yachi, Naruhisa Sano
    48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012 2012年12月1日  筆頭著者責任著者
    A new small solid launcher named Epsilon is currently under development in JAXA. The Epsilon launch vehicle is normally three stage rocket system and can be added an optional liquid propulsion system to the third stage for the missions requiring precision orbit insertion. The SRB-A motor boosting the H-IIA vehicle and the H-IIB vehicle will be shared as the first stage motor. Upper-stage motors are inherited from the fifth M-V launch vehicle, from the viewpoints of development cost reduction, performance increase, and advanced technology succession. The solid motor side jet (SMSJ) system, which is used for the roll control during the first stage powered flight and the three-axis control after the SRB-A burnout, will be newly developed based on the technology of the SMSJ for the M-V vehicle. A maiden flight of the first Epsilon is scheduled in the summer of 2013. A successive concept of the advanced propulsion technologies for next-gen Epsilon are also described in the present paper. There are many technical challenges, such as new propellants and mass reduction of nozzle liner, to be tackled with for the next couple of year. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
  • 徳留 真一郎, 宇井 恭一, 清水 文男, 羽生 宏人, 谷内 雄作, 佐野 成寿
    日本航空宇宙学会誌 60(7) 272-276 2012年  査読有り招待有り筆頭著者責任著者
    イプシロンロケット二段階開発の最初のステップでは,本質的な低コスト化と即応性の向上を目指す革新的機体システム技術の開発に重きを置いている.推進系の開発においては,H-IIAやM-Vの開発で培われた技術を最大限活用することによって,期間,コスト,リスクを抑え,革新的機体システム技術の早期実証及び近い将来の小型衛星打上げの要求に応える.第1段モータには基幹ロケットのSRB-Aモータを共用し,第2段,第3段にはM-V-5号機の第3段モータ,キックモータをほぼそのまま流用してM-Vをしのぐ輸送効率を達成する.推進系の新しい開発課題は,多様なミッションへの対応能力を高めるPBSの小型液体推進系,そして第1段推力飛行中のロール制御と同コースティング中の3軸制御を担うSMSJ装置である.2013年度の初飛行を目指すイプシロンの推進系開発は,2011年度内に詳細設計を完了して初号機製造に進む見通しである.
  • MORITA Yasuhiro, IMOTO Takayuki, TOKUDOME Shinichiro, OHTSUKA Hirohito
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 10(28) Tg_19-Tg_24 2012年  査読有り
    The Epsilon rocket, formerly called Advanced Solid Rocket (ASR) launcher, proceeded to the full development phase in August 2010 and its launch site was officially declared to be the Uchinoura Space Center (USC), the home of Japanese solid propellant rocket. The primary purpose of Epsilon is to provide small satellites with a responsive launch that means a low cost, user-friendly and ultimately efficient launch system. The slogan is "Small, Cheap, Fast and Reliable". This outcome is also a result of the excellent endeavors of those who devoted themselves to the next generation solid propellant rocket. However, this is not the final destination. Now that the development was approved, the most important is what the next step should be beyond Epsilon. This paper deals with the significance of the development of Epsilon launch vehicle and how it contributes to the possible evolution of future space transportation systems.
  • 森田 泰弘, 井元 隆行, 徳留 真一郎, 大塚 浩仁
    日本航空宇宙学会誌 59(695) 371-377 2011年  査読有り招待有り
    イプシロンロケットの目的は,小型衛星に対して即応性豊かな打ち上げシステム,すなわち自在性と機動性に富みユーザーフレンドリな輸送手段を構築,宇宙への敷居を下げて宇宙科学や宇宙利用の裾野を拡大することにある.一方,これを輸送系の視点でみると,打ち上げシステムの革新というひと言に尽きる.すなわち,今後のロケット開発にあたっては,射場設備と運用はもとより,製造プロセスから搭載系に至るまで,およそロケットの打ち上げに必要な設備や運用をとことんコンパクトで身軽なものにしていこう,それが未来への扉を開く鍵であるという理念である.イプシロンロケットでは,このような壮大なビジョンを実現する第一歩として,ロケットのインテリジェント化やモバイル管制などの超革新技術を開拓,これを世界に先駆けて実証するために,初号機を2013年度に打ち上げる計画である.
  • Shinichiro Tokudome, Yoshihiro Naruo, Hatsuo Mori, Tsuyoshi Yagishita, Takayuki Yamamoto
    46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &amp;amp; Exhibit 2010年7月25日  筆頭著者責任著者
  • Kazuhiro Yagi, Seiji Matsuda, Jun Yokote, Takayoshi Fuji, Kenji Sasaki, Mitsuteru Kaneoka, Shinichiro Tokudome, Yohsuke Nambu, Maasaaki Sugimoto
    23rd Annual AIAA/USU Conference on Small Satellite 2009年  
  • Akihito Itoh, Masashi Watanabe, Hiroto Habu, Shin-Ichiro Tokudome, Keiichi Hori, Hirobumi Saito, Kazuyuki Kondo, Shuji Tanaka, Masayoshi Esashi
    International Journal of Energetic Materials and Chemical Propulsion 8(4) 321-327 2009年  査読有り
    A micro solid propellant thruster for simple attitude control of a 10 kg class small spacecraft is currently under development. The prototype has 0.8 mm micro rocket elements, arrayed at a pitch of 1.2 mm on a 22 × 22 mm substance. Initially, solid propellants were used, obtaining only 20% ignition probability with a very long ignition delay (e.g. 1000 ms) as well as very high ignition energy. While observing the tested prototype sample, it became apparent that the main cause of these problems was a gap between the solid propellants and ignition heater. So, the thruster system was improved so that the propellants adhered to the heater. In addition, an ignition charge was used that starts to burn at 210°C, which was acetone having the form of slurry. As a result, a better ignition probability of over 80% in vacuum and half thrust of expectation were gained.
  • Shinichiro TOKUDOME, Yoshihiro NARUO, Tsuyoshi YAGISHITA, Satoshi NONAKA, Maki SHIDA, Hatsuo MORI, Takeshi NAKAMURA
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7(ists26) Ta_19-Ta_25 2009年  査読有り筆頭著者責任著者
  • 徳留 真一郎, 八木下 剛, 羽生 宏人, 鈴木 直洋, 大毛 康弘, 嶋田 徹
    宇宙航空研究開発機構研究開発報告 7 1-15 2008年2月  査読有り筆頭著者責任著者
    無毒で常温貯蔵可能な液体推進剤として亜酸化窒素(N_2O)/エタノールの組合せに着目し,それによる扱い易い液体推進系の実証研究を進めている.当面の目標として大気吸い込み式極超音速推進系の飛行試験に用いる加速用ロケットエンジンへの適用を目指しているが,その低温環境順応性を活かす衛星・探査機搭載推進系への応用も視野に入れている.これまでに,推力700N級の要素試験供試体を用いた燃焼試験を2シリーズ行って,エンジン噴射器設計のための有用なデータと運用特性を取得してきた.併せて,水冷式燃焼器による燃焼器壁面熱流束分布の測定や厚肉のシリカ繊維強化プラスチックSFRP製燃焼器を用いた燃焼試験によって燃焼器への耐熱複合材料適用の可能性も探っている.
  • Shinichiro Tokudome, Tsuyoshi Yagishita, Hiroto Habu, Toru Shimada, Yasuhiro Daimo
    Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference 5 4427-4440 2007年12月10日  筆頭著者責任著者
    Nitrous Oxide (N2O) / ethanol propulsion system is distinguished as the liquid propulsion with non-toxic, user-friendly, and storable bipropellant. The current target of the present study is to build a quick-response and maneuverable main engine of a sounding-rocket like flying test bed which will be applied to the hypersonic air-breathing propulsion researches in the near future. The application to the spacecraft propulsion is also considered due to its compatibility in low-temperature operation environment. Two series of static firing tests were performed with 700 N class gas generator models so far. Current test results showed that valuable design data were collected and operational procedure was verified. Potential of application of composite materials to the combustion chamber was also examined from the chamber wall heat flux data obtained and the result of firing test using a thick SFRP chamber.
  • Shinichiro Tokudome, Kiyokazu Kobayashi
    14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 2006年11月6日  筆頭著者責任著者
  • Hiroshi Hasegawa, Masahisa Hanzawa, Shin-Ichiro Tokudome, Masahiro Kohno
    Journal of Propulsion and Power 22(5) 975-983 2006年9月  査読有り
  • Kouichiro Tani, Takeshi Kanda, Shin-ichiro Tokudome
    44th AIAA Aerospace Sciences Meeting and Exhibit 2006年1月9日  
    Modified combined cycle engine models were tested in subsonic and transonic regions to improve the aerodynamic performance and overcome the problems which were found in the previous tests with the ejector jet prototype model. Three inlet geometries and two cowl options were tested and all models successfully reduced the inlet drag comparing to that of the prototype. In a high subsonic or transonic °ow, the current models showed the possibility of the thrust augmentation by the ejector-jet cycle. One dimensional aerodynamic estimations were also carried out and the results were compared with the data evaluated from the pitot pressure measurements. The mass °ow was in good agreement and, with a slight adjustment of the parameter, the total pressure prediction method showed reasonable match with the experimental data.
  • Yoshifumi Inatani, Yoshihiro Naruo, Nobuaki Ishii, Hiroyuki Ogawa, Satoshi Nonaka, Shinichiro Tokudome, Hiroshi Yamakawa
    Space Technology 25(3-4) 219-228 2005年  査読有り
    A fully reusable rocket vehicle is proposed to demonstrate good operability characteristics both on the ground and in flight. The proposed vehicle is to be used as a sounding rocket and has the capabilities of ballistic flight, returning to the launch site, and landing vertically making use of clustered liquid hydrogen rocket engines. Before initiating the development of this type of reusable rocket, a small test vehicle with a liquid hydrogen rocket engine was built and flight-tested. A demonstration of vertical landing and exercise of turnaround operation for repeated flights are the major objectives of the test vehicle. Three series of flight tests were performed in 1999, 2001 and 2003, and the flight test operation provided repeated flight environment and many valuable lessons were learned for designing the fully reusable rocket vehicle. © 2005 Published by Lister Science.
  • Kazuyuki Kondo, Shuji Tanaka, Hiroto Habu, Shin-ichiro Tokudome, Keiichi Hori, Hirobumi Saito, Akihito Itoh, Masashi Watanabe, Masayoshi Esashi
    IEICE Electron. Express 1(8) 222-227 2004年  
  • 徳留 真一郎, 田中 秀治
    日本航空宇宙学会誌 52(610) 283-285 2004年  査読有り招待有り筆頭著者責任著者
  • 長谷川 宏, 徳留 真一郎, 判澤 正久, 高野 雅弘
    日本航空宇宙学会論文集 51(594) 364-370 2003年7月5日  査読有り
  • Hiroshi Hasegawa, Shin-ichiro Tokudome, Masahisa Hanzawa, Masahiro Kohno
    39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2003年6月26日  
  • Tanaka Shuji, Hosokawa Ryuichiro, Tokudome Shin-ichiro, HORI Keiichi, SAITO Hirobumi, WATANABE Masashi, ESASHI Masayoshi
    Transactions of the Japan Society for Aeronautical and Space Sciences 46(151) 47-51 2003年5月4日  査読有り
    The prototype of a solid propellant rocket array thruster for simple attitude control of a 10 kg class micro-spacecraft was completed and tested. The prototype has 10×10 φ0.8 mm solid propellant micro-rockets arrayed at a pitch of 1.2 mm on a 20×22 mm substrate. To realize such a dense array of micro-rockets, each ignition heater is powered from the backside of the thruster through an electrical feedthrough which passes along a propellant cylinder wall. Boron/potassium nitrate propellant (NAB) is used with/without lead rhodanide/potassium chlorate/nitrocellulose ignition aid (RK). Impulse thrust was measured by a pendulum method in air. Ignition required electric power of at least 3–4 W with RK and 4–6 W without RK. Measured impulse thrusts were from 2×10−5 Ns to 3×10−4 Ns after the calculation of compensation for air dumping.
  • Shin-ichiro Tokudome, Hiroshi Hasegawa, Masahisa Hanzawa, Masahiro Kohno
    38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2002年7月7日  筆頭著者責任著者
  • 長谷川 宏, 徳留 真一郎, 判澤 正久
    東海大学紀要 工学部 41(2) 147-152 2001年  査読有り
  • Tokudome, S, Tanno, H, Nakano, N, Kato, K, Komai, I, Kohno, M
    Proceedings of the 22nd International Symposium on Space Technology and Science (The 22nd ISTS was held from May 28 through June 4, 2000, at Hotel Metropolitan Morioka New Wing in Morioka City, Iwate Prefecture.) 174-179 2000年  査読有り筆頭著者責任著者
    Restricting partially and temporally the initial propellant burning surfaces with thin HTPB inhibitors realized a new method of controlling the chamber pressure rise rate at ignition. The merits of the method are to be manufactured easily, to hardly affect the whole motor thrust pattern, and low in cost. The ground firing tests with sub-scale motors have verified the method to be reliable and flexible. The principal concept of a "staged ignition system" is to replace the ignitor main charge by an "ignition cavity" perforated at the fwd.-end of the motor propellant grain. This 'ignition cavity' generates the combustion gas required for igniting the remaining portion of the grain. It has been employed in the designs of two ISAS' solid motors now under development and has contributed to simplification of the ignition systems.
  • Masahiro Kohno, Angelo Volpi, Shin-Ichiro Tokudome
    International Journal of Energetic Materials and Chemical Propulsion 918-926 1997年  査読有り
    Combustion products flowing in the free port of a solid-rocket motor are responsible for the erosive burning effect. To improve the knowledge of the mechanism governing erosive burning, a nonintrusive X-ray diagnostic system is utilized with the objective of acquiring burning rate data with high temporal and spatial resolutions. The motor has a rectangular cross section, and it is loaded with two solid-propellant slabs parallel to each other. The X-ray source is placed above the motor. The X-ray beam passes through the aluminum windows, which are inserted in the top side of the motor case, and the component transmitted through the slabs is collected by three sensors inserted in the case on the opposite side of the windows. By means of an experimentally determined calibration curve of the attenuation of the X-ray beam through various thicknesses of an unburned propellant, the local time history of the propellant thickness can be deduced and the erosive burning can be evaluated. Results demonstrate a diagnostic reliability and provide data for improving model development and validation of the erosive burning characteristics of the tested solid propellant.
  • 徳留真一郎
    1995年  査読有り筆頭著者責任著者
    地上静止状態から音速程度までの低速飛翔環境で作動可能なエジェクタ式空気吸い込みロケットにおいては、混合ダクト出口で超音速混合流を形成することが推力増強効果の点でより有利とされている。しかし、未だその作動特性に関する一般性のある理論や経験則は確立されていない。本研究では、低亜音速までの飛翔環境も勘案した上で、超音速混合流を形成するエジェクタ式空気吸い込みロケットの地上静止状態における作動特性を明らかにすることを主目的として、固体ロケットと円筒ダクトを組み合わせて作動特性実験を行うとともに、内部流評価ために新しい解析法を導入して実験結果を詳細に検討している。そして、広い条件にわたる作動性能の予測法を提案し、基本的設計指針を示している。 第1章は序論で、空気吸い込み式ロケットに関する従来の研究動向と問題点を総括し、本研究の目的と意義を述べている。 第2章では、実験装置と方法を説明している。本研究のために試作された小型固体ロケットモータのノズル出口部を円筒型混合ダクト入口に挿入し、混合ダクト出口背圧が、吸い込まれる二次流側総圧(Pts)以下の地上静止状態で実験を行っている。実験供試体としては、ノズルスロート面積(Atp)を一定として開口比の異なる三種類のロケットノズル、および断面積(Ad)の異なる二種類の円筒型混合ダクトを長さを変えて用いている。また一回の実験で広い主流側総圧範囲の計測データを取得するため、ロケットモータ燃焼室圧力(主流側総圧:Ptp)を連続的に降下させている。取得される測定データは、ロケット燃焼室圧力、大気圧、ダクト壁圧およびダクト壁面近傍におけるガス温度である。 第3章では、安定した超音速混合流を形成する条件において、「二次流閉塞モード」と「亜音速混合モード」の二つの作動形態があることを確認している。二次流閉塞モードは従来から知られている作動形態である。一方亜音速混合モードは、二次流が亜音速のまま混合して、ある程度混合が進行した位置で流れが閉塞するもので、従来報告例のない、著者が見い出した作動形態である。本研究では、広い条件にわたって亜音速混合モードとなったことを指摘している。 第4章では、総圧比(Ptp/Pts)、混合ダクト断面積比(Ad/Atp)およびロケットノズル開口比(Aep/Atp)が作動性能に及ぼす影響を系統的に把握するために、内部流の一次元解析法を提案している。この解析法では、混合ダクト出口位置において一様な混合流が形成されていると仮定している。また新たに、主流と二次流が未混合のまま静圧の等しい流れ(Compound-compressible flow以下CCFと略す)を形成すると仮定した、静圧平衡位置が想定されている。CCFの振舞いについては、Compound-flow indicator を導入して判別できることを指摘している。 第5章では、超音速混合流の形成条件に関する解析結果より求めた超音速混合流維持に必要な最小総圧比が、実験値と一致することを示している。また、圧力測定データを用い、対応する混合ダクト出口位置状態と静圧平衡位置状態を推算している。混合ダクト出口位置静圧P2の解析結果は壁圧測定値に良く一致し、また静圧平衡位置の解析結果は、実験で確認された現象をある程度捉えている。特に、静圧平衡位置における二次流側マッハ数M1sの解析結果から、各作動形態に対応する次のような特徴を得ている。すなわち、二次流閉塞モードではPtp/Ptsの値に依らずM1s=1.1であり、亜音速混合モードではPtp/Pts、Ad/AtpおよびAep/Atpの値に依らずM1s0.52である。二次流閉塞モードについては、本研究の解析法でM1s=1を仮定することにより,作動性能を予測できることを示している。亜音速混合モードについても、経験的に得られるM1sの値を仮定することにより作動性能予測が可能なこと、またM1sを一定とみなすと、流量率比で代表される作動性能は、Ptp/PtsとAd/Atpの比をCとするとき、ほぼ一義的にCのみに依存することを指摘している。また、Cが一定の条件下では、混合ダクト内部に形成される流れ場は、大まかに混合ダクト直径Dを基準とした寸法で発達すると推察し、実験結果によってこれを実証している。さらに、推力増強効果に関する考察結果に基づいて、より大推力・高比推力を達成する超音速混合流形成型エジェクタ式空気吸い込みロケットの基本的な設計指針を示している。 第6章は結論で、本研究の成果が要約されている。補遺には本文で使用される数式等の詳細が記されている。 以上要するに本論文は、超音速混合流を形成するエジェクタ式空気吸い込みロケットの地上静止状態における作動特性実験ならびに混合ダクト内部流の一次元解析を行い、同型ロケットに関して作動特性の新しい予測法と基本的設計指針を与えるものであり、航空宇宙工学上寄与するところが大きい。よって本論文は博士(工学)の学位請求論文として合格と認められる。
  • Ikeda, Hirohide, Tanno, Haruhito, Tokudome, Shinichiro, Kohno, Masahiro
    Proceedings of the 17th International Symposium on Space Technology and Science 1 249-254 1990年  査読有り
    The SAS’ nozzle two-phase flow computer program has recently been revised to achieve a higher .accuracy in calculating thrust characteristic and behavior of particle streamlines. Alumina particles had been gathered in lots of motor firings over a wide range in scale. The particle size distribution characteristics were obtained and the resulted particle sizing equation in terms of the mass averaged particle diameter D43 is quite close to that employed in the improved SPP, i.e., D43 is a unique function of motor throat diameter. Subscale motors containing highly aluminized propellant were fired, whose nozzles were designed to have significant amount of particle impingement and then severe erosion at the exit lip. The nozzle eroded locations were used to verify the computational accuracy of impingement location prediction. It has been shown that the improved two-phase flow program can well predict the particle impingement location by assuming an appropriate particle diameter DpIMP, which is proportional to D43. The proportional coefficient is rather universal.

MISC

 89
  • 坂本, 勇樹, 小林, 弘明, 丸, 祐介, 徳留, 真一郎, 大山, 聖, 竹内, 伸介, 三浦, 政司, 正木, 大作, 高田, 仁志, 角銅, 洋実, 加賀, 亨, 山城, 龍馬, 杵淵, 紀世志, 真子, 弘泰, 内海, 政春, 中田, 大将, 江口, 光, 湊, 亮二郎, 吹場, 活佳, 川崎, 央, 前田, 慎市, 武田, 洋一, 佐藤, 哲也
    観測ロケットシンポジウム2023 講演集 2024年2月  
    レポート番号: Ⅱ-2
  • 徳留真一郎, 餅原義孝, 三浦政司, 坂本勇樹, 森下直樹, 山本高行, 荒川聡, 竹内伸介, 竹前俊昭, 豊田裕之, 奥平俊暁, 太刀川純孝, 寺島啓太, 紙田徹, 今村裕志, 高島健
    第67回宇宙科学技術連合講演会講演集 2023年10月  筆頭著者責任著者
  • 徳留真一郎, 佐伯孝尚, 津田雄一, 秋月祐樹, 澤田健一郎, 森下直樹, 北川幸樹, 松井康平, 坂本勇樹, 松永哲也, 堀恵一, 荒川聡, 松浦芳樹
    第67回宇宙科学技術連合講演会講演集 2023年10月  筆頭著者責任著者
  • 徳留 真一郎, 佐藤 哲也, 丸 祐介
    日本航空宇宙学会第54期年会講演会講演集 2023年4月  筆頭著者責任著者
  • 津田雄一, 佐伯孝尚, 森治, 黒川宏之, 嶌生有理, 高尾勇輝, 丸祐介, 坂東信尚, 徳留真一郎, 森下直樹
    宇宙科学技術連合講演会講演集(CD-ROM) 67th 2023年  
  • 丸祐介, 武井悠人, 佐伯孝尚, 森治, 津田雄一, 徳留真一郎, 野中聡, 古川克己, 長田泰一, 中塚潤一
    宇宙科学技術連合講演会講演集(CD-ROM) 67th 2023年  
  • 伊藤千珠, 宍戸拓, 真子弘泰, 徳留真一郎, 丸祐介
    宇宙科学技術連合講演会講演集(CD-ROM) 67th 2023年  
  • 宍戸, 拓, 伊藤, 千珠, 真子, 弘泰, 小林, 弘明, 丸, 祐介, 徳留, 真一郎, SHISHIDO, Taku, ITO, Senju, MANAKO, Hiroyasu, KOBAYASHI, Hiroaki, MARU, Yusuke, TOKUDOME, Shinichiro
    令和4年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2022 2023年1月  
    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: SA6000184015 STCP-2022-015
  • M. Kinoshita, K. Ui, K. Sato, K. Nitta, H. Ikeda, N. Morishita, S. Tokudome, K. Hori, Y. Matsuura
    10th Space Debris Workshop 2022年11月28日  
  • 森下直樹, 荒川聡, 餅原義孝, 松浦芳樹, 武田真一, 井川寛隆, 久田深作, 境野正法, 佐藤峻介, 坂本勇樹, 竹前俊明, 三浦政司, 徳留真一郎, 高島健
    宇宙科学技術連合講演会講演集(CD-ROM) 66th 2022年  
  • 坂本勇樹, 小林弘明, 丸祐介, 徳留真一郎, 野中聡, 澤井秀次郎, 大山聖, 三浦政司, 正木大作, 高田仁志, 角銅洋実, 加賀亨, 山城龍馬, 杵淵紀世志, 真子弘泰, 内海政春, 中田大将, 江口光, RICHARDSON Matthew, 佐藤哲也
    宇宙科学技術連合講演会講演集(CD-ROM) 66th 2022年  
  • 近藤, 奨一郎, 福﨑, 俊哉, 坂野, 友哉, 杵淵, 紀世志, 藤浦, 彰友, 奈女良, 実央, 中田, 大将, 真子, 弘泰, 徳留, 真一郎, 小林, 弘明, 坂本, 勇樹, 丸, 祐介, KONDO, Shoichiro, FUKUZAKI, Toshiya, BANNO, Yuya, KINEFUCHI, Kiyoshi, FUJIURA, Akitomo, NAMERA, Mio, NAKATA, Daisuke, MANAKO, Hiroyasu, TOKUDOME, Shinichiro, KOBAYASHI, Hiroaki, SAKAMOTO, Yuki, MARU, Yusuke
    令和3年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2021 2022年1月  
    令和3年度宇宙輸送シンポジウム(2022年1月13日-14日. オンライン開催) Space Transportation Symposium FY2021 (January 13-14, 2022. Online Meeting) 著者人数: 12名 資料番号: SA6000173016 STCP-2021-016
  • 藤浦, 彰友, 奈女良, 実央, 住吉, 政哉, 中田, 大将, 内海, 政春, 江口, 光, 近藤, 奨一郎, 坂野, 友哉, 福崎, 俊哉, 杵淵, 紀世志, 真子, 弘泰, 坂本, 勇樹, 丸, 祐介, 小林, 弘明, 徳留, 真一郎, 八木下, 剛, FUJIURA, Akitomo, NAMERA, Mio, SUMIYOSHI, Masaya, NAKATA, Daisuke, UCHIUMI, Masaharu, EGUCHI, Hikaru, KONDO, Shoichiro, BANNO, Yuya, FUKUZAKI, Toshiya, KINEFUCHI, Kiyoshi, MANAKO, Hiroyasu, SAKAMOTO, Yuki, MARU, Yusuke, KOBAYASHI, Hiroaki, TOKUDOME, Shinichiro, YAGISHITA, Tsuyoshi
    令和3年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2021 2022年1月  
    令和3年度宇宙輸送シンポジウム(2022年1月13日-14日. オンライン開催) Space Transportation Symposium FY2021 (January 13-14, 2022. Online Meeting) 著者人数: 16名 資料番号: SA6000173015 STCP-2021-015
  • 後藤 健, 丸 祐介, 山田 和彦, 志田 真樹, 福島 洋介, 山本 高行, 徳留 真一郎, 野中 聡, 峯杉 賢治, 竹内 伸介, 佐藤 泰貴, 澤井 秀次郎, 羽生 宏人, 阿部 琢美
    2021年3月  
    第3回観測ロケットシンポジウム(2021年3月24-25日. オンライン開催)著者人数: 14名資料番号: SA6000162017レポート番号: Ⅴ-3
  • 小林弘明, 坂本勇樹, 丸祐介, 徳留真一郎, 澤井秀次郎, 野中聡, 後藤健, 加賀亨, 佐藤英一, 山城龍馬, 八木下剛, 高田仁志, 角銅洋実
    宇宙科学技術連合講演会講演集(CD-ROM) 64th 2020年  
  • 丸祐介, 小林弘明, 坂本勇樹, 徳留真一郎, 澤井秀次郎, 野中聡
    宇宙科学技術連合講演会講演集(CD-ROM) 64th 2020年  
  • RAMON Roger Gutierrez, TSUDA Yuichi, SAIKI Takanao, TAKEI Yuto, MIMASU Yuya, MARU Yusuke, NONAKA Satoshi, TOKUDOME Shinichiro
    宇宙科学技術連合講演会講演集(CD-ROM) 64th 2020年  
  • 徳留 真一郎, 野中 聡, 丸 祐介, TOKUDOME Shinichiro, NONAKA Satoshi, MARU Yusuke
    令和元年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2019 2020年1月  筆頭著者責任著者
    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: SA6000147015レポート番号: STCP-2019-015
  • 丸 祐介, 佐藤 哲也, 小林 弘明, 徳留 真一郎, 野中 聡, 澤井 秀次郎, Maru Yusuke, Sato Tetsuya, Kobayashi Hiroaki, Tokudome Shinichiro, Nonaka Satoshi, Sawai Shujiro
    観測ロケットシンポジウム2019 講演集 = Proceedings of Sounding Rocket Symposium 2019 2019年8月  
    第2回観測ロケットシンポジウム(2019年8月5日-6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: SA6000142004レポート番号: Ⅰ-4
  • 笠原 次郎, 松岡 健, 川崎 央, 松山 行一, 後藤 啓介, 松尾 亜紀子, 船木 一幸, 丸 祐介, 羽生 宏人, 竹内 伸介, 山田 和彦, 北川 幸樹, 戸部 裕史, 山田 和彦, 荒川 聡, 岩崎 祥大, 和田 明哲, 中田 大将, 内海 政春, 遠藤 琢磨, 石井 一洋, 徳留 真一郎, 野中 聡, 小島 孝之, 川島 秀人, 庄司 烈, Kasahara Jiro, Matsuoka Ken, Kawasaki Akira, Matsuyama Koichi, Goto Keisuke, Matsuo Akiko, Funaki Ikkoh, Maru Yusuke, Habu Hiroto, Takeuchi Shinsuke, Yamada Kazuhiko, Kitagawa Koki, Tobe Hirobumi, Yamada Kazuhiko, Arakawa Satoshi, Iwasaki Akihiro, Wada Asato, Nakata Daisuke, Uchiumi Masaharu, Endo Takuma, Ishii Kazuhiro, Tokudome Shinichiro, Nonaka Satoshi, Kojima Takayuki, Kawashima Hideto, Shouji Takeshi
    観測ロケットシンポジウム2019 講演集 = Proceedings of Sounding Rocket Symposium 2019 2019年8月  
    第2回観測ロケットシンポジウム(2019年8月5日-6日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県著者人数: 26名資料番号: SA6000142023レポート番号: Ⅶ-2
  • 丸祐介, 小林弘明, 大山聖, 斉藤巧真, 徳留真一郎, 佐藤哲也
    宇宙科学技術連合講演会講演集(CD-ROM) 63rd 2019年  
  • 小林弘明, 徳留真一郎, 澤井秀次郎, 丸祐介, 坂本勇樹, 佐藤哲也
    宇宙科学技術連合講演会講演集(CD-ROM) 63rd 2019年  
  • Ken GOTO, Shinichiro TOKUDOME, Tsuyoshi YAGISHITA
    SiC/SIC COMPOSITE THRUSTER FOR A NON-TOXIC LIQUID PROPELLANT ROCKET ENGINE 2017年11月  
  • 山城 龍馬, 徳留 真一郎, 齊藤 靖博, 伊海田 皓史, 山本 高行, 小野 哲也
    宇宙科学技術連合講演会講演集 60 6p 2016年9月6日  
  • 徳留 真一郎
    日本航空宇宙学会誌 64(7) 227-230 2016年  査読有り招待有り筆頭著者責任著者
  • 竹内 伸介, 徳留 真一郎, 峯杉 賢治
    宇宙科学技術連合講演会講演集 59 3p 2015年10月7日  
  • 北川 幸樹, 徳留 真一郎, 和田 英一
    宇宙科学技術連合講演会講演集 59 4p 2015年10月7日  
  • 井出雄一郎, 高橋拓也, 岩井啓一郎, 野副克彦, 羽生宏人, 徳留真一郎
    火薬学会年会講演要旨集 2015 2015年  
  • 後藤健, 金谷寿浩, 金谷寿浩, 戸島英貴, 戸島英貴, 大谷章夫, 徳留真一郎, 羽生宏人, 鈴木直洋, 八木下剛, 富沢利夫, 有川秀一, 米山聡, 黒川一哉
    宇宙科学技術連合講演会講演集(CD-ROM) 59th 2015年  
  • 井出雄一郎, 高橋拓也, 岩井啓一郎, 野副克彦, 羽生宏人, 徳留真一郎
    火薬学会秋季研究発表講演会講演要旨集 2015 2015年  
  • 森田 泰弘, 井元 隆行, 山城 龍馬, 徳留 真一郎, 岸 光一, 大塚 浩仁
    日本航空宇宙学会誌 63(8) 265-272 2015年  査読有り
    イプシロンの目指している世界は何か? 来るべき本格的宇宙利用の時代を視野に入れると,出発点はコストと性能である.しかし,これだけで未来永劫世界と勝負できるわけではない.大事なのは付加価値を含めた高い次元の総合力,いわゆるユニバーサルデザインであろう.それは,ユーザの視点では乗り心地や使い勝手に代表される利便性,輸送性の観点としては打ち上げシステムの革新である.言うなれば,F1レーシングカーのように特殊な宇宙ロケットという乗り物を高級乗用車並みに身近な乗り物に転換していこうということである.宇宙もこれからは「おもてなし」の時代なのである.
  • 井出 雄一郎, 高橋 拓也, 岩井 啓一郎, 野副 克彦, 羽生 宏人, 徳留 真一郎, Ide Yuichiro, Takahashi Takuya, Iwai Keiichiro, Nozoe Katsuhiko, Habu Hiroto, Tokudome Shinichiro
    平成26年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2014 2015年  
    平成26年度宇宙輸送シンポジウム(2015年1月15日-16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: SA6000036007レポート番号: STCP-2014-007
  • 北川 幸樹, 徳留 真一郎, 和田 英一
    宇宙科学技術連合講演会講演集 58 5p 2014年11月12日  
  • 徳留 真一郎, 齊藤 靖博, 山本 高行
    宇宙科学技術連合講演会講演集 58 1-4 2014年11月12日  筆頭著者責任著者
  • 徳留 真一郎, 齊藤 靖博, 山本 高行, 中谷 幸司, 岩田 直子, 岡田 修平, 羽生 宏人, 森田 泰弘, 沖田 耕一, Tokudome Shinichiro, Saitoh Yasuhiro, Yamamoto Takayuki, Nakaya Koji, Iwata Naoko, Okada Shyuhei, Habu Hiroto, Morita Yasuhiro, Okita Koichi
    第47回月・惑星シンポジウム = Proceedings of the 47th ISAS Lunar and Planetary Symposium 2014年8月  筆頭著者責任著者
    第47回月・惑星シンポジウム (2014年8月4日-6日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県形態: カラー図版あり資料番号: SA6000033030
  • 羽生宏人, 津田雄一, 徳留真一郎, 三宅淳巳, 堀恵一, 森田泰弘
    火薬学会年会講演要旨集 2014 2014年  
  • 高橋拓也, 秦啓晃, 岩井啓一郎, 野副克彦, 井出雄一郎, 羽生宏人, 徳留真一郎
    火薬学会年会講演要旨集 2014 2014年  
  • 井出雄一郎, 高橋拓也, 岩井啓一郎, 野副克彦, 羽生宏人, 徳留真一郎
    火薬学会年会講演要旨集 2014 2014年  最終著者
  • 高橋拓也, 秦啓晃, 岩井啓一郎, 野副克彦, 山口容史, 井出雄一郎, 羽生宏人, 徳留真一郎
    安全工学シンポジウム講演予稿集 2014 2014年  
  • 徳留 真一郎, 宮澤 哲裕, 彦坂 篤志
    宙舞 : 中部支部報 (74) 7-11,図巻頭1p 2014年  
  • 森田 泰弘, 井元 隆行, 徳留 真一郎, 堀 恵一, 大塚 浩仁, 宮川 清, 秋葉 鐐二郎, 次世代固体ロケット研究会, イプシロンロケットプロジェクトチーム, Morita Yasuhiro, Imoto Takayuki, Tokudome Shinichiro, Hori Keiichi, Otsuka Hirohito, Miyagawa Kiyoshi, Akiba Ryojiro, Epsilon Launch Vehicle Project Team
    平成25年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2013 2014年  
    平成25年度宇宙輸送シンポジウム(2014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: SA6000016009レポート番号: STCP-2013-009
  • 徳留 真一郎, 清水 文男, 和田 英一, 羽生 宏人, 堀 恵一, 反野 晴仁, 中野 信之, 佐野 成寿, Tokudome Shinichiro, Shimizu Fumio, Wada Eiichi, Habu Hiroto, Hori Keiichi, Tanno Haruhito, Nakano Nobuyuki, Sano Naruhisa
    平成25年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2013 2014年  筆頭著者責任著者
    平成25年度宇宙輸送シンポジウム(2014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: SA6000016010レポート番号: STCP-2013-010
  • 羽生 宏人, 加藤 勝美, 藤里 公司, 永山 清一郎, 田中 邦翁, 小駒 益弘, 徳留 真一郎, 堀 恵一
    宇宙航空研究開発機構研究開発報告 12 41-44 2013年3月  
    The cost reduction is currently important for the development of space launch systems. The solid motor side jet system is loaded the low temperature gas generator propellant (GGP) which includes a special purpose material. The combustion gas temperature of GGP should be controlled up to 1400 K because of the system requirement. The objective of this research is to find the substitution of the composition for GGP to reduce the cost. That is why ammonium nitrate (AN) is selected as an oxidizer for GGP. The composition and combustion characteristics of AN based GGP for the launch vehicle side jet system were investigated. The burning rate was measured by the strand burner.
  • 羽生宏人, 徳留真一郎, 井元隆行, 三宅淳巳, 堀恵一, 森田泰弘
    火薬学会年会講演要旨集 2013 2013年  
  • 羽生宏人, 徳留真一郎, 井元隆行, 三宅淳巳, 堀恵一, 森田泰弘
    安全工学シンポジウム講演予稿集 2013 2013年  
  • 森田 泰弘, 井元 隆行, 徳留 真一郎, 堀 恵一, 大塚 浩仁, 宮川 清, 秋葉 鐐二郎, 次世代固体ロケット研究会, 宇宙航空研究開発機構宇宙輸送ミッション本部イプシロンロケットプロジェクトチーム(JAXA), Morita Yasuhiro, Imoto Takayuki, Tokudome Shinichiro, Hori Keiichi, Otsuka Hirohito, Miyagawa Kiyoshi, Akiba Ryojiro, Epsilon Rocket Project Team Space Transportation Mission Directorate Japan Aerospace Exploration Agency (JAXA)
    平成24年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium: FY2012 2013年1月  
    平成24年度宇宙輸送シンポジウム (2013年1月17日-1月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, 神奈川県今夏の初飛行に向けて開発も大詰めを迎えているイプシロンロケットでは、点検機能のインテリジェント化やロケット管制のモバイル化など、固体ロケットばかりでなく将来の輸送系を牽引する次世代革新技術を世界に先駆けて実現しようとしている。しかし、これは我々が目指す壮大なビジョンのほんの序章に過ぎない。宇宙輸送システムの発展のためには、イプシロンの先を見据えたより大きな改革が必要であり、製造プロセスを含めた打ち上げシステム全体の革新こそが今後の進むべき方向である。これはまた、将来の再使用スタイルの輸送系に必須の取り組みでもある。イプシロンが未来に向けた第一歩たる所以である。本報告では、イプシロンロケットが目指すところを起点として、今後のロケット開発の発展の方向性を示す。形態: カラー図版あり形態: PDF資料番号: AA0061856007レポート番号: STCP-2012-007
  • 淺賀 健太郎, 反野 晴仁, 中野 信之, 大塚 浩仁, 佐野 成寿, 浅野 俊介, 徳留 真一郎, 安田 誠一, 清水 文男, Asaka Kentaro, Tanno Haruhito, Nakano Nobuyuki, Otsuka Hirohito, Sano Naruhisa, Asano Shunsuke, Tokudome Shinichiro, Yasuda Seiichi, Shimizu Fumio
    平成24年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium: FY2012 1-5 2013年1月  
    平成24年度宇宙輸送シンポジウム (2013年1月17日-1月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, 神奈川県形態: カラー図版あり形態: PDF資料番号: AA0061856012レポート番号: STCP-2012-012
  • 徳留 真一郎, 宇井 恭一, 清水 文男, 和田 英一, 羽生 宏人, 堀 恵一, 反野 晴仁, 中野 信之, 佐野 成寿, Tokudome Shinichiro, Ui Kyoichi, Shimizu Fumio, Wada Eiichi, Habu Hiroto, Hori Keiichi, Tanno Haruhito, Nakano Nobuyuki, Sano Naruhisa
    平成24年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium: FY2012 54th 1-19 2013年1月  筆頭著者責任著者
    平成24年度宇宙輸送シンポジウム (2013年1月17日-1月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, 神奈川県形態: カラー図版あり形態: PDF資料番号: AA0061856010レポート番号: STCP-2012-010
  • 永山清一郎, 加藤勝美, 東英子, 中野勝之, 藤里公司, 羽生宏人, 徳留真一郎, 堀恵一
    火薬学会年会講演要旨集 2012 2012年  
  • 井出雄一郎, 藤里公司, 堤明正, 勝身俊之, 羽生宏人, 曽根理嗣, 徳留真一郎, 茶圓茂広, 川口淳一郎
    宇宙エネルギーシンポジウム(Web) 31st 2012年  

主要な講演・口頭発表等

 52
  • Yuki Sakamoto, Tetsuya Sato, Matthew Richardson, Hiromitsu Kakudo, Ryoma Yamashiro, Masashi Miura, Akira Oyama, Shujiro Sawai, Shinichiro Tokudome, Yusuke Maru, Hikaru Eguchi, Daisuke Nakata, Hiroaki Kobayashi
    AJCPP 2023 2023年3月16日 日本航空宇宙学会
  • 小林弘明, 徳留真一郎, 丸祐介, 坂本勇樹, 佐藤哲也
    AJCPP 2023 2023年3月16日 日本航空宇宙学会
  • 徳留 真一郎
    第5回観測ロケットシンポジウム 2023年3月1日 宇宙航空研究開発機構 宇宙科学研究所  招待有り
    宇宙科学研究所(ISAS)の宇宙輸送系専門委員会において策定されている宇宙科学・探査分野における宇宙輸送系の中長期ミッションシナリオでは,2040年頃の達成を目指すミッションを「多様な宇宙科学の世界をカバーする軌道間輸送ネットワークを構築する」ことと設定している. ミッション達成に向けて,地上から地球周回軌道へ高頻度に大量の物資や人員を輸送する宇宙往還機を実現するためには,往還飛行において「極超音速飛行」を避けることはできない.本稿では,主に宇宙往還機の実現と競争力向上に資する極超音速エンジンの技術実証を中心に,極超音速飛行に係る技術課題に実証的に取り組むための飛行実験機の目的と検討例について紹介する.
  • 徳留 真一郎, 野中 聡, 丸 祐介, 小林 弘明, 佐藤 哲也, 三浦 政司, 坂本 勇樹
    令和4年(2022年)度宇宙輸送シンポジウム 2023年1月13日
  • 丸祐介, 徳留真一郎, 佐藤哲也
    令和4年(2022年)度宇宙輸送シンポジウム 2023年1月13日
  • 関二千翔, 渡辺俊作, 吉村拓, 吉田圭一郎, 和田豊, 加藤信治, 徳留真一郎
    令和4年(2022)度宇宙輸送シンポジウム 2023年1月12日
  • 宍戸拓, 伊藤千珠, 真子弘泰, 小林弘明, 丸祐介, 徳留真一郎
    令和4年(2022年)度宇宙輸送シンポジウム 2023年1月
  • 松浦 芳樹, 北川 幸樹, 松井 康平, 徳留 真一郎
    第66回宇宙科学技術連合講演会 2022年11月4日
  • 三浦 政司, 餅原 義孝, 徳留 真一郎, 荒川 聡, 竹前 俊昭, 森下 直樹, 山本 高行, 太刀川 純孝, 竹内 伸介, 豊田 裕之, 奥平 俊暁, 坂本 勇樹, 寺島 啓太, 紙田 徹, 高島 健, 今村 裕志
    第66回宇宙科学技術連合講演会 2022年11月4日
  • 宍戸 拓, 真子 弘泰, 徳留 真一郎, 丸 祐介
    第66回宇宙科学技術連合講演会 2022年11月1日
  • 坂本 勇樹, 小林 弘明, 丸 祐介, 徳留 真一郎, 野中 聡, 澤井 秀次郎, 大山 聖, 三浦 政司, 正木 大作, 髙田 仁志, 角銅 洋実, 加賀 亨, 山城 龍馬, 杵淵 紀世志, 真子 弘泰, 内海 政春, 中田 大将, 江口 光, Richardson Matthew, 佐藤 哲也
    第66回宇宙科学技術連合講演会 2022年11月1日
  • Shinichiro Tokudome, Yusuke Maru, Satoshi Nonaka
    73rd International Astronautical Congress (IAC), Paris, France, 18-22 September 2022. 2022年9月20日 The International Astronautical Federation
    The Space Transportation System Committee of the Institute of Space and Astronautical Science (ISAS) of the Japan Aerospace Exploration Agency (JAXA) has been continuously drafting medium- to long-term strategies in the research field of space transportation system under the Inter-University Research Institute System of ISAS since FY2018. This committee is also considering the role of ISAS in cooperation with the organization-wide activities of JAXA to formulate strategies in the space transportation system field. Among its previous achievements, the committee assembled a strategic target and scenario for the space transportation system research field at the end of the last fiscal year and is continuously revising it. Based on a formulated mission scenario, the committee identified three priority areas related to system technologies that must be tackled. They are a “reusable orbit transportation system” that aims for a highly frequent mass transportation from Earth to low Earth orbit, “deep space interorbital transportation system” that aims for a marked improvement in space science and exploration missions in terms of frequency and flexibility, and “small flying test bed system” for flight demonstrations, which is indispensable in the research and development of space transportation systems. In this paper, the authors summarize the medium- to long term strategies and their concrete implementation measures over the next two decades.
  • 徳留 真一郎
    第22回宇宙科学シンポジウム(FY2021) 2022年1月6日
  • 徳留真一郎
    航空原動機・宇宙推進講演会講演論文集(CD-ROM) 2022年
  • Masahiro Kinoshita, Kyoichi Ui, Kenichi Satoh, Kumi Nitta, Hirohide Ikeda, Naoki Morishita, Shinichiro Tokudome, Keiichi Hori, Yoshiki Matsuura
    11th IAASS Conference - "MANAGING RISK IN SPACE" - (IAASS/JAXA) 2021年10月21日
  • Masanori Sakaino, Shinichiro Tokudome, Toshiaki Takemae, Yoshitaka Mochihara, Satoshi Arakawa, Naoki Morishita, Yoshiki Matsuura
    The 11th IAASS Conference - “Managing Risk in Space”- (IAASS/JAXA) 2021年10月20日
  • 徳留 真一郎
    第21回宇宙科学シンポジウム(FY2020) 2021年1月6日  招待有り
  • Matthew P. Richardson, Hiroaki Kobayashi, Yuki Sakamoto, Yusuke Maru, Shinichiro Tokudome, Satoshi Nonaka, Shujiro Sawai, Akira Oyama, Daisaku Masaki, Satoshi Takada, Hiromitsu Kakudo, Toru Kaga, Kiyoshi Kinefuchi, Tetsuya Sato
    Accelerating Space Commerce, Exploration, and New Discovery conference, ASCEND 2021 2021年
    The Japan Aerospace Exploration Agency, in partnership with academia and industry, are developing the Air Turbo Rocket for Innovative Unmanned Mission (ATRIUM) engine: an air turboramjet + rocket combine cycle propulsion system intended to replace conventional liquid rocket engines in Vertical Takeoff Vertical Landing applications, such as reusable sounding rockets. A subscale Flight Test Bed (FTB) vehicle is also being developed to demonstrate the ATRIUM engine in a flight environment. In this paper, the ATRIUM engine and FTB vehicle are introduced, and current progress in their development is summarized. Future test plans and practical applications are also discussed.
  • Shinichiro TOKUDOME, Tsuyoshi YAGISHITA, Ken GOTO, Naohiro SUZUKI, Takayuki YAMAMOTO, Yasuhiro DAIMOH
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 2021年 Japan Society for Aeronautical and Space Sciences
  • Shinichiro Tokudome, Ken Goto, Tsuyoshi Yagishita, Naohiro Suzuki, Takayuki Yamamoto
    AIAA Propulsion and Energy 2019 Forum 2019年8月19日 American Institute of Aeronautics and Astronautics
  • KITAGAWA Koki, TOKUDOME Shinichiro, HORI Keiichi, TANNO Haruhito, NAKANO Nobuyuki
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 2019年 一般社団法人 日本航空宇宙学会
    <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>
  • IDE Yuichiro, TAKAHASHI Takuya, IWAI Keiichiro, NOZOE Katsuhiko, HABU Hiroto, TOKUDOME Shinichiro
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 2016年 一般社団法人 日本航空宇宙学会
    <p>As a replacement for hydrazine, ammonium-dinitramide-based ionic liquid propellant (ADN-based ILP) has been developed by JAXA and Carlit Holdings Co., Ltd. This propellant is made by mixing three solid powers: ADN, monomethylamine nitrate, and urea. The propellant's theoretical specific impulse is 1.2 times higher than that of hydrazine, and its density is 1.5 times higher at a certain composition. Although ionic liquids were believed to be non-flammable for a long time owing to their low-volatility, recently combustible ILs have been reported. The combustion mechanism of ILs is not yet understood. The objective of this paper is to understand the combustion wave structure of ADN-based ILP. The temperature distribution of the combustion wave in a strand burner test shows a region of constant temperature. This region would indicate boiling in a gas-liquid phase. Thus, the combustion wave structure consists of liquid, gas-liquid, and gas phases. The dependence of boiling point on pressure would identify chemical substances in the gas-liquid phase. The dependence of combustion and ignition characteristics on ADN content is also discussed. </p>
  • Tetsuya Ono, Shinichiro Tokudome, Ryoma Yamashiro, Takayuki Yamamoto, Hiroshi Ikaida, Yasuhiro Saito
    Proceedings of the International Astronautical Congress, IAC 2016年
    Copyright © 2016 by the International Astronautical Federation. All rights reserved. Although reusable launch vehicle's necessity and significance, being cost-effective, eco-friendly and reliable, have been recognized in a long time, practical system still has never been realized except the Space Shuttle. There are two main reasons in this. One reason is that reusable vehicle's recurring cost is high. The other reason is that reusable vehicle, especially that upper stage, have the problem of aerodynamic heating during re-entry. We are considering new upper stage reusable launch vehicle with solid rocket booster, which clear these problems concerning reusable launch vehicle. For the first problem on the recurring cost, the application of the auto inspection system which is cultivated in solid rocket motor's development and launch operation is being considered. That is expected to reduce the inspection cost drastically after the vehicle flight. For the second problem on the re-entry, challenging technologies are applied in the upper stage. Those are material and structure with heat tolerance and lightness, active-cooling system to share the hydrogen with the liquid propulsion system, advanced guidance and control system, and so on. On the other hand, to the lower stage or booster, application of solid rocket is considered. Since the challenging upper stage's size is expected to vary through the iteration of design cycles, the lower stage should be stable and flexible with the thrust level in development phase. Because solid motors of various sizes are developed in JAXA/ISAS since the first small solid motor started to be developed in 1954, those development method has been efficiently accumulated. Then this legacy's utilization for the new system is expected to be quite beneficial. On these technological backgrounds, this paper describes the system study for new upper-stage reusable launch vehicle with the solid rocket booster.
  • 徳留真一郎
    「宇宙科学・探査ロードマップと各分野の将来計画」シンポジウム 2014年5月8日  招待有り
  • 徳留 真一郎
    日本機械学会 宇宙工学部門 2013年度部門賞・一般表彰 記念講演会 2014年3月28日  招待有り
  • MORITA Yasuhiro, IMOTO Takayuki, TOKUDOME Shinichiro, OHTSUKA Hirohito
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 2014年 一般社団法人 日本航空宇宙学会
    The development of the Epsilon launch vehicle, Japan's next generation solid rocket launcher, has just moved to the final stretch for its first launch scheduled in the summer of 2013 to carry the planetary telescope satellite SPRINT-A. The JAXA appreciates the advantages of combined benefits of the standardized small satellites and the Epsilon's highly efficient launch system in order to increase the level of space activities. The primary purpose of Epsilon is to provide small satellites with a responsive launch that means "Small, Low cost, Fast and Reliable". The attention should be directed toward the innovative design concept of Epsilon, which aims at developing the next generation technologies such as the highly intelligent autonomous checkout system and the mobile launch control. Now that the full-scale development is about to be finished, the most important is what the next step should be beyond the Epsilon. This paper deals with the significance of the Epsilon launch vehicle and how it contributes to the possible evolution of future space transportation systems.
  • Shinichiro Tokudome, Hiroto Habu, Kyoichi Ui, Fumio Shimizu, Yusaku Yachi, Naruhisa Sano
    48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012 2012年12月1日
    A new small solid launcher named Epsilon is currently under development in JAXA. The Epsilon launch vehicle is normally three stage rocket system and can be added an optional liquid propulsion system to the third stage for the missions requiring precision orbit insertion. The SRB-A motor boosting the H-IIA vehicle and the H-IIB vehicle will be shared as the first stage motor. Upper-stage motors are inherited from the fifth M-V launch vehicle, from the viewpoints of development cost reduction, performance increase, and advanced technology succession. The solid motor side jet (SMSJ) system, which is used for the roll control during the first stage powered flight and the three-axis control after the SRB-A burnout, will be newly developed based on the technology of the SMSJ for the M-V vehicle. A maiden flight of the first Epsilon is scheduled in the summer of 2013. A successive concept of the advanced propulsion technologies for next-gen Epsilon are also described in the present paper. There are many technical challenges, such as new propellants and mass reduction of nozzle liner, to be tackled with for the next couple of year. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
  • 徳留 真一郎, 宇井 恭一, 清水 文男, 羽生 宏人, 谷内 雄作, 佐野 成寿
    日本航空宇宙学会誌 2012年 一般社団法人 日本航空宇宙学会
    イプシロンロケット二段階開発の最初のステップでは,本質的な低コスト化と即応性の向上を目指す革新的機体システム技術の開発に重きを置いている.推進系の開発においては,H-IIAやM-Vの開発で培われた技術を最大限活用することによって,期間,コスト,リスクを抑え,革新的機体システム技術の早期実証及び近い将来の小型衛星打上げの要求に応える.第1段モータには基幹ロケットのSRB-Aモータを共用し,第2段,第3段にはM-V-5号機の第3段モータ,キックモータをほぼそのまま流用してM-Vをしのぐ輸送効率を達成する.推進系の新しい開発課題は,多様なミッションへの対応能力を高めるPBSの小型液体推進系,そして第1段推力飛行中のロール制御と同コースティング中の3軸制御を担うSMSJ装置である.2013年度の初飛行を目指すイプシロンの推進系開発は,2011年度内に詳細設計を完了して初号機製造に進む見通しである.
  • 徳留真一郎, 宇井恭一, 清水文男, 和田英一, 羽生宏人, 堀恵一, 反野晴仁, 中野信之, 佐野成寿
    宇宙科学技術連合講演会講演集(CD-ROM) 2012年
  • MORITA Yasuhiro, IMOTO Takayuki, TOKUDOME Shinichiro, OHTSUKA Hirohito
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 2012年 一般社団法人 日本航空宇宙学会
    The Epsilon rocket, formerly called Advanced Solid Rocket (ASR) launcher, proceeded to the full development phase in August 2010 and its launch site was officially declared to be the Uchinoura Space Center (USC), the home of Japanese solid propellant rocket. The primary purpose of Epsilon is to provide small satellites with a responsive launch that means a low cost, user-friendly and ultimately efficient launch system. The slogan is "Small, Cheap, Fast and Reliable". This outcome is also a result of the excellent endeavors of those who devoted themselves to the next generation solid propellant rocket. However, this is not the final destination. Now that the development was approved, the most important is what the next step should be beyond Epsilon. This paper deals with the significance of the development of Epsilon launch vehicle and how it contributes to the possible evolution of future space transportation systems.
  • 徳留真一郎, 宇井恭一, 清水文男, 羽生宏人, 堀恵一, 谷内雄作, 中野信之, 矢代顕慎, 佐野成寿
    宇宙科学技術連合講演会講演集(CD-ROM) 2011年
  • 徳留真一郎, 羽生宏人, 和田英一
    火薬学会年会講演要旨集 2011年
  • Shinichiro Tokudome, Yoshihiro Naruo, Hatsuo Mori, Tsuyoshi Yagishita, Takayuki Yamamoto
    46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &amp;amp; Exhibit 2010年7月25日 American Institute of Aeronautics and Astronautics
  • 徳留真一郎, 成尾芳博, 志田真樹, 小川博之, 福吉芙由子, 八木下剛, 野中聡, 岩田直子
    宇宙科学技術連合講演会講演集(CD-ROM) 2009年
  • Shinichiro TOKUDOME, Yoshihiro NARUO, Tsuyoshi YAGISHITA, Satoshi NONAKA, Maki SHIDA, Hatsuo MORI, Takeshi NAKAMURA
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 2009年 Japan Society for Aeronautical and Space Sciences
  • 2007年7月 アメリカ航空宇宙学会
  • 徳留 真一郎, 羽生 宏人
    宇宙科学シンポジウム 2003年1月9日 宇宙科学研究所
  • 徳留真一郎, 羽生宏人, 山本高行, 里吉貴史, 西中村健一, 川口淳一郎
    宇宙輸送シンポジウム 平成14年度 2003年
  • 徳留 真一郎, 細川 隆一郎, 田中 秀治, 堀 恵一, 齋藤 宏文, 渡辺 将史, 江刺 正喜
    年次大会講演論文集 2002年 一般社団法人 日本機械学会
    The authors have developed the practical prototype of a micro-solid propellant rocket array thruster for attitude control of a 10kg class micro-spacecraft. a target of this activity is to build the array thruster with 10000 of solid propellant micro-rockets arrayed on a 100×100mm substrate. The prototype with the Φ0.8 micro-rockets arrayed at a pitch of 1.2mm on a 20×30mm substrate has built and tested so far. Boron/potassium nitrate (NAB) propellant is used with/without initiator of lead rhodanide/potassium chlorate/nitrocellulose (RK). Impulse thrust was measured by means of a pendulum method. The experimental results show that the prototype has proper ignition characteristics and further experimental studies are needed to evaluate and to control the impulse thrust with accuracy. We are planning to conduct the thrust measurement test under vacuum condition.

担当経験のある科目(授業)

 4

所属学協会

 2

主要な共同研究・競争的資金等の研究課題

 9
  • JAXA宇宙科学研究所 工学委員会戦略的開発研究経費 2021年4月 - 2035年3月
    徳留真一郎, 津田雄一, 佐伯孝尚, 坂本勇樹, 森下直樹, 澤田健一郎, 秋月祐樹, 北川幸樹, 松井康平, 堀恵一, 松浦芳樹, 松永哲也
  • JAXA宇宙科学研究所 工学委員会戦略的開発研究費 2018年 - 2025年3月
    佐藤哲也, 小林弘明, 丸祐介, 坂本勇樹, 徳留真一郎, 澤井秀次郎, 後藤健, 大山聖, 佐藤英一, 戸部裕史, 高田仁志, 角銅洋実, 山城龍馬, 八木下剛, 野中聡, 三浦政司, 正木大作, 真子弘泰, 加賀亨, 船﨑健一, 吉原信人, 武田洋一, 大志田宜明, 内海政春, 中田大将, 江口光, 室蘭工, 湊亮二郎, 杵淵紀世志, 吹場活佳, 内藤均, 雨宮和久, 天沼光博, 竹内伸介, 小路谷剛, 鎮守裕太, 平松宏健
  • 国立研究開発法人 宇宙航空研究開発機構 JAXAプロジェクト 2019年 - 2024年
    DESTINY PLUSプロジェクトメンバー
  • JAXA宇宙科学研究所と外部機関との共同研究制度 2021年6月 - 2022年3月
    徳留真一郎, 竹前俊昭, 荒川聡, 森下直樹, 餅原義孝, 増田和久, 境野正法, 須藤翔, 松浦芳樹, 五十嵐真二
  • JAXA宇宙科学研究所と外部機関との共同研究制度 2020年2月 - 2022年3月
    徳留真一郎, 竹前俊昭, 鈴木直洋, 入門朋子, 志田真樹, 八木下剛, 森下直樹, 関野展弘, 瀬川泰伸, 森崎浩武, 長沼哲史, 野原勝, 知念克典
  • JAXA宇宙科学研究所と他機関との共同研究制度 2020年10月 - 2021年3月
    徳留真一郎, 竹前俊昭, 荒川聡, 森下直樹, 餅原義孝, 松浦芳樹, 五十嵐真二
  • JAXA宇宙科学研究所 工学委員会戦略的開発研究費(工学) 2010年4月 - 2019年3月
    徳留真一郎, 羽生宏人, 八木下剛, 鈴木直洋, 後藤健, 佐藤英一, 竹内伸介, 山本高行, 佐伯孝尚, 植田修一, 齋藤俊仁, 竹腰正雄, 高田仁志, 姫野武洋, 井上智博
  • JAXA宇宙科学研究所 工学委員会戦略的開発研究費(工学) 2003年4月 - 2009年3月
    徳留真一郎, 羽生宏人, 八木下剛, 鈴木直洋, 後藤健, 佐藤英一, 竹内伸介, 山本高行, 佐伯孝尚, 植田修一, 齋藤俊仁, 竹腰正雄, 高田仁志, 姫野武洋, 井上智博

主要な学術貢献活動

 1

主要な社会貢献活動

 15