Details of the Researcher

PHOTO

Toshinori Kuwahara
Section
Green Goals Initiative
Job title
Professor
Degree
  • Dr.-Ing.(シュトゥットガルト大学)

  • 修士(工学)(九州大学)

Research History 5

  • 2025/01 - Present
    Research Center for Green X-Tech, Green Goals Initiative, Tohoku Universiry Space Infrastructure Engineering Laboratory, Innovative Infrastructure Research Division Professor

  • 2020/05 - Present
    Tohoku University Department of Aerospace Engineering

  • 2015/10 - 2024/12
    Tohoku University Department of Aerospace Engineering

  • 2010/08 - 2015/09
    Tohoku University Department of Aerospace Engineering Assistant Professor

  • 2009/04 - 2010/07
    University of Stuttgart Fuculty of Aerospace Engineering and Geodesy Academic Researcher

Education 3

  • University of Stuttgart Fuculty of Aerospace Engineering and Geodesy Institute of Space Systems

    2005/10 - 2009/03

  • Kyushu University

    2003/04 - 2005/03

  • Kyushu University School of Engineering Department of Mechanical and Aerospace Engineering

    2000/04 - 2003/03

Committee Memberships 5

  • 内閣府 ロケット開発等におけるスキル標準に関する調査検討会委員

    2024/06 - Present

  • 一般社団法人 クロスユー サポーター

    2023/05 - Present

  • 経済産業省 超小型衛星コンステレーションの試験方法に関する国際標準化プロジェクト委員会

    2022/08 - Present

  • 経済産業省 産業サイバーセキュリティ研究会ワーキンググループ1(制度・技術・標準化)宇宙産業サブワーキンググループ委員

    2021/01 - Present

  • 経済産業省 キューブサットインターフェースに関する国際標準化プロジェクト委員会

    2019/06 - 2022/02

Professional Memberships 6

  • International Academy of Astronautics, Corresponding Member

    2023/07 - Present

  • AIAA: American Institute of Aeronautics and Astronautics

    2020/09 - Present

  • JSME: The Japan Society of Mechanical Engineers

    2020/09 - Present

  • SICE: The Society of Instrument and Control Engineers

    2020/09 - Present

  • IEEE: Institute of Electrical and Electronics Engineers

    2020/08 - Present

  • JSASS: The Japan Society for Aeronautical and Space Sciences

    2003/05 - Present

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Research Interests 8

  • System Engineering

  • CubeSat

  • Micro/Nano-Satellite

  • Aerospace Engineering

  • Orbital Mechanics

  • Control Engineering

  • System Integration

  • Small Satellite

Research Areas 1

  • Manufacturing technology (mechanical, electrical/electronic, chemical engineering) / Control and systems engineering /

Awards 19

  1. Japan Venture Awards

    2023/12 独立行政法人中小企業基盤整備機構 地域貢献特別賞

  2. TOHOKU TECH PLANTER

    2023/11 株式会社リバネス みずほ銀行賞

  3. Deep Tech Venture of the Year in Japan

    2023/04 Leave a Nest

  4. EY Innovative Startup 2023

    2023/03

  5. 2023年防災・減災×サステナブル大賞 防災・減災×SDGs賞 アカデミー&ジュニアアカデミー部門 グローバル賞/優秀賞

    2023/02 一般社団法人減災サステナブル技術協会 台風の目の立体構造の観測技術の確立

  6. J-Startup TOHOKU

    2023/01

  7. Award for Academic Startups

    2022/09

  8. すごいベンチャー100 2022年

    2022/09 東洋経済

  9. Space Frontier Award

    2021/03 The Japan Society of Mechanical Engineers

  10. 2021 IEEE/SICE International Symposium on System Integration Best Student Paper Award

    2021/01 IEEE/SICE

  11. UNISEC挑戦賞

    2020/07 NPO法人大学宇宙工学コンソーシウムUNISEC 超小型衛星技術の発展と宇宙開発利用の裾野拡大への貢献

  12. 第34回独創性を拓く先端技術大賞, 社会人部門最優秀賞 経済産業大臣賞

    2020/06 フジサンケイビジネスアイ,経済産業省 人工衛星を用いた人工流れ星の生成技術

  13. ディスティングイッシュトリサーチャー称号付与

    2020/05 東北大学

  14. 令和2年度科学技術分野の文部科学大臣表彰 若手科学者賞

    2020/04 文部科学省 超小型宇宙システムによる宇宙開発利用の高度化に関する研究

  15. 第4回宇宙開発利用大賞 宇宙航空研究開発機構理事長賞

    2020/03 内閣府 アジア諸国への超小型衛星技術教育と実利用ネットワークの構築

  16. 第8回ものづくり日本大賞 優秀賞 製品・技術開発部門, 内閣総理大臣表彰

    2020/01 経済産業省 膜展開式軌道離脱装置「DOM」の開発と宇宙実証

  17. 12th IAA Symposium on Small Satellites for Earth Observation Best Paper Presentation Award – Second Prize

    2019/05 International Academy of Astronautics Lessons learned from Integrating the Dual-band Optical Transient Camera to Microsatellite RISESAT

  18. 2019 IEEE/SICE International Symposium on System Integration Best Paper Award

    2019/01 IEEE/SICE Attitude Maneuvering Sequence Design of High-Precision Ground Target Tracking Control for Multispectral Earth Observations

  19. 宇宙開発利用大賞

    2018/03 内閣府 宇宙航空研究開発機構理事長賞

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Papers 193

  1. Guidance strategies for controlled Earth reentry of small spacecraft in low Earth orbit

    Takumi Saito, Toshinori Kuwahara, Yuji Saito, Yuji Sato

    Acta Astronautica 2024/12

    DOI: 10.1016/j.actaastro.2024.12.054  

  2. Simplified Data-Reduction Method for Hybrid Propulsion

    Yuji Saito, Shota Kameyama, Toshinori Kuwahara

    Journal of Propulsion and Power 1-7 2024/02/29

    Publisher: American Institute of Aeronautics and Astronautics (AIAA)

    DOI: 10.2514/1.b39387  

    ISSN: 0748-4658

    eISSN: 1533-3876

  3. FEM dynamic simulation technique for membrane structure deployment and model evaluation

    Takumi Saito, Toshinori Kuwahara, Alperen Pala, Yasuyuki Miyazaki, Tetsuya Kaneko

    Acta Astronautica 2024/02

    DOI: 10.1016/j.actaastro.2024.01.043  

  4. Deployment Behavior Evaluation of Membrane Space Structure using Self-extending Booms under Microgravity Environment

    Takumi Saito, Toshinori Kuwahara, Yasuyuki Miyazaki, Tetsuya Kaneko

    AIAA SCITECH 2024 Forum 2024/01/04

    Publisher: American Institute of Aeronautics and Astronautics

    DOI: 10.2514/6.2024-2261  

  5. High Accuracy Pointing Control Using a MEMS Mirror for a Micro Space Telescope

    Hayate Nakaoka, Shinya Fujita, Ryo Ishimaru, Toshinori Kuwahara

    2024 IEEE/SICE International Symposium on System Integration, SII 2024 1554-1560 2024

    DOI: 10.1109/SII58957.2024.10417284  

  6. Safe Attitude and Orbit Control for ISS-Deployed CubeSat HOKUSHIN-1 with Cold-Gas Propulsion System

    Saki Komachi, Shinya Fujita, Kohei Takeda, Hayate Nakaoka, Toshinori Kuwahara, Kazuya Yoshida, Junichiro Kawaguchi

    2024 IEEE/SICE International Symposium on System Integration, SII 2024 1445-1451 2024

    DOI: 10.1109/SII58957.2024.10417713  

  7. On the low-cost asynchronous one-way range measurement method and the device for micro to nano deep space probes

    Junichiro Kawaguchi, Masahiro Fujita, Shinya Fujita, Yuji Sakamoto, Toshinori Kuwahara, Kazuya Yoshida, Shingo Nishimoto, Kohei Takeda, Saki Komachi, Kokubo Hayato

    Acta Astronautica 2024/01

    DOI: 10.1016/j.actaastro.2023.10.036  

  8. Study on Direct Transfer Strategies from Lunar Gateway to Different Types of Low Lunar Orbit

    Kohei Takeda, Saki Komachi, Toshinori Kuwahara, Shinya Fujita, Junichiro Kawaguchi

    2023 AAS/AIAA Astrodynamics Specialist Conference 2023/08

  9. De-Orbit Maneuver Demonstration Results of Micro-Satellite ALE-1 with a Separable Drag Sail

    Kohei Takeda, Toshinori Kuwahara, Takumi Saito, Shinya Fujita, Yoshihiko Shibuya, Hiromune Ishii, Lena Okajima, Tetsuya Kaneko

    Applied Sciences (Switzerland) 13 (13) 2023/07

    DOI: 10.3390/app13137737  

    eISSN: 2076-3417

  10. Lunar Orbit Mission using Spatial-resolved Fuel Regression Rate of Hybrid Thrusters

    Alejandro Taiki, Padilla Torres, Tomoya Takuma, Yuji Saito, Toshinori Kuwahara

    34th International Symposium on Space Technology and Science 2023/06

  11. Simulation Evaluation of Re-entry Control Technique for Small Satellite ELS-R100

    Takumi Saito, Toshinori Kuwahara, Mitsuki Takaoka, Yo Kawamata, Shinya Fujita, Yuji Saito, Nobuo Sugimura, Yuji Sato, Ryotaro Murakami

    34th International Symposium on Space Technology and Science 2023/06

  12. On-Orbit Operation Results of the AIS Receiving System Demonstration Satellite IHI-SAT

    Yuko Kawasoe, Takashi Ogai, Ryu Shinohara, Toshinori Kuwahara, Shinya Fujita, Takumi Saito

    2023/06

  13. Results and Lessons Learned from In-Orbit Thruster Control Demonstration of Microsatellite ALE-2 with a Small Propulsion System

    Takumi Saito, Shinya Fujita, Toshinori Kuwahara, Yoshihiko Shibuya, Hiromune Ishii, Lena Okajima, Junichiro Kawaguchi

    14th IAA Symposium on Small Satellites for Earth System Observation 2023/05

  14. Satellite Data Management System for Earth Observation Microsatellites Peer-reviewed

    Junichi KURIHARA, Yuji SAKAMOTO, Yuji SATO, Shinya FUJITA, Toshinori KUWAHARA, Kazuki KIBUNE, Naoya SHIRAISHI

    Journal of Evolving Space Activities 1 2023/03

    DOI: 10.57350/jesa.19  

  15. Development of Hybrid Thruster Ignition System with Low-Toxicity Fuel and Catalytic Reaction

    Yuji Saito, Alejandro Taiki Padilla Torres, Hirohide Ikeda, Taiichi Nagata, Yoshiki Matsuura, Shinji Igarashi, Hironori Chiba, Kosuke Kida, Toshinori Kuwahara

    Proceedings of the International Astronautical Congress, IAC 2023-October 2023

    ISSN: 0074-1795

  16. Magnetometer-Based Attitude Determination Extended Kalman Filter and Optimization Techniques

    Supakit Wattanarungsan, Toshinori Kuwahara, Shinya Fujita

    IEEE Transactions on Aerospace and Electronic Systems 2023

    DOI: 10.1109/TAES.2023.3299897  

  17. Constructing Earth-Moon Data Relay System: Trajectory Design of Ballistic Lunar Transfer for Nano Spacecraft

    Kodai Nakazawa, Kohei Takeda, Saki Komachi, Shinya Fujita, Toshinori Kuwahara

    2023 IEEE/SICE International Symposium on System Integration, SII 2023 2023

    DOI: 10.1109/SII55687.2023.10039237  

  18. Attitude and Orbit Control Strategy with 10N Thruster for ALE-3

    Kazuki Kibune, Shinya Fujita, Yoshihiko Shibuya, Toshinori Kuwhara, Hiromune Ishii, Pasith Tangdhanakanond

    2023 IEEE/SICE International Symposium on System Integration, SII 2023 2023

    DOI: 10.1109/SII55687.2023.10039171  

  19. Asynchronous One-Way Range Measurement Applied to Microspace Probes

    Junichiro Kawaguchi, Yuichiro Nada, Yuka Ishigooka, Toshinori Kuwahara, Kazuya Yoshida

    Journal of Spacecraft and Rockets 59 (5) 1602-1612 2022/09

    DOI: 10.2514/1.A35241  

    ISSN: 0022-4650

    eISSN: 1533-6794

  20. Motion Estimation of Orbital Objects Using SfM Method

    OKABAYASHI Hiroki, UNO Kentaro, KUWAHARA Toshinori, YOSHIDA Kazuya

    The Proceedings of JSME annual Conference on Robotics and Mechatronics (Robomec) 2022 1A1-K02 2022

    Publisher: The Japan Society of Mechanical Engineers

    DOI: 10.1299/jsmermd.2022.1a1-k02  

    eISSN: 2424-3124

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    Currently, there are an increasing number of space debris in the Earth’s orbit, such as parts from satellites and rockets that are no longer in operation but hold crucial risks of collision with other operational spacecraft. In order to safely approach and capture space debris with an unmanned orbital space robot, it is essential to understand its motion state before the active removal operation. In this paper, we experimentally verify the motion estimation method that uses the Structure from Motion (SfM) algorithm, which is a technique to reconstruct the three-dimensional shape of a target object and the pose of a camera by inputting a group of images with different viewpoints.

  21. Re-entry Control Technology for Small-satellite with High Thrust System

    Saito Takumi, Kuwahara Toshinori, Takaoka Mitsuki, Fujita Shinya

    Proceedings of the Japan Joint Automatic Control Conference 65 1190-1192 2022

    Publisher: The Japan Joint Automatic Control Conference

    DOI: 10.11511/jacc.65.0_1190  

  22. Space Demonstration of Boom Extension and De-orbit Sail Deployment of the Separable De-orbit Mechanism of Micro-satellite ALE-1

    PALA Alperen, KUWAHARA Toshinori, SAITOU Takumi, UTO Hiroki, SHIBUYA Yoshihiko

    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan (Web) 20 2022

    ISSN: 1884-0485

  23. On The Low-Cost Asynchronous One-Way Range Measurement Method and the Device for Micro to Nano Deep Space Probes

    Junichiro Kawaguchi, Masahiro Fujita, Shinya Fujita, Yuji Sakamoto, Toshinori Kuwahara, Kazuya Yoshida

    Proceedings of the International Astronautical Congress, IAC 2022-September 2022

    ISSN: 0074-1795

  24. Mission Assurance Handbook for University-based Lean Satellites

    Mengu Cho, Yoshihiro Tsuruda, Masahiro Furumoto, Kikuko Miyata, Yukihito Kitazawa, Toshinori Kuwahara

    Proceedings of the International Astronautical Congress, IAC 2022-September 2022

    ISSN: 0074-1795

  25. Orbital Demonstration of Gossamer Structure Shape Estimation using Time-of-Flight Camera System

    Toshinori Kuwahara, Alperen Pala, Adrien Potier, Yoshihiko Shibuya, Yuji Sato, Shinya Fujita, Daisuke Suzuki, Tetsuya Kaneko

    2022 IEEE/SICE International Symposium on System Integration, SII 2022 882-886 2022

    DOI: 10.1109/SII52469.2022.9708770  

  26. Development of Spin Stabilization Control System for the Cosmic Dust Observation CubeSat

    Shinya Fujita, Ryo Ishimaru, Yuji Sakamoto, Keisuke Maeda, Osamu Okudaira, Yuji Sato, Toshinori Kuwahara, Takafumi Matsui

    2022 IEEE/SICE International Symposium on System Integration, SII 2022 114-119 2022

    DOI: 10.1109/SII52469.2022.9708909  

  27. Attitude Control System Design of 3U CubeSat with Electrodynamic Tether for Post Mission Disposal Demonstration

    Naoya Shiraishi, Yuji Sato, Yoshihiko Shibuya, Shinya Fujita, Toshinori Kuwahara, Daisuke Suzuki

    2022 IEEE/SICE International Symposium on System Integration, SII 2022 132-137 2022

    DOI: 10.1109/SII52469.2022.9708853  

  28. Orbital Maneuver Evaluation of Micro-satellite ALE-1 with a Separable Drag Sail

    Alperen Pala, Toshinori Kuwahara, Kohei Takeda, Yoshihiko Shibuya, Yuji Sato, Shinya Fujita, Daisuke Suzuki, Tetsuya Kaneko

    2022 IEEE/SICE International Symposium on System Integration, SII 2022 877-881 2022

    DOI: 10.1109/SII52469.2022.9708783  

  29. On-orbit Calibration of a Telescope Alignment for Earth Observation using Stars and QUEST

    Shinya Fujita, Yuji Sato, Toshinori Kuwahara, Yuji Sakamoto, Junichi Kurihara

    2022 IEEE/SICE International Symposium on System Integration, SII 2022 120-125 2022

    DOI: 10.1109/SII52469.2022.9708740  

  30. Lessons Learned from On-orbit Gyroscope Malfunction and Recovery Operation of Microsatellite RISESAT

    Shinya Fujita, Toshinori Kuwahara, Kazuki Kibune, Naoya Shiraishi, Yuji Sato, Yuji Sakamoto, Junichi Kurihara

    2022 IEEE/SICE International Symposium on System Integration, SII 2022 126-131 2022

    DOI: 10.1109/SII52469.2022.9708894  

  31. Integration and Orbit Demonstration of Micro-satellite Payload System Based on a Plug-and-Play On-board Computer Peer-reviewed

    Morokot SAKAL, Toshinori KUWAHARA, Hannah TOMIO, Yu MURATA, Kosuke HANYU, Shinya FUJITA, Yuji SATO, Yuji SAKAMOTO, Shinichi KIMURA, Junichi KURIHARA

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19 (5) 784-793 2021/09

    Publisher: Japan Society for Aeronautical and Space Sciences

    DOI: 10.2322/tastj.19.784  

    eISSN: 1884-0485

  32. High Precision Orbit Determination Method Based on GPS Flight Data for ALE-1 Peer-reviewed

    Tomoyuki HONDA, Toshinori KUWAHARA, Shinya FUJITA, Alperen Ahmed PALA, Yoshihiko SHIBUYA, Yuji SATO, Koh KAMACHI

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19 (5) 744-752 2021/09

    Publisher: Japan Society for Aeronautical and Space Sciences

    DOI: 10.2322/tastj.19.744  

    eISSN: 1884-0485

  33. Time-of-Flight Monitoring Camera System of the De-orbiting Drag Sail for Microsatellite ALE-1 Peer-reviewed

    Adrien POTIER, Toshinori KUWAHARA, Alperen PALA, Shinya FUJITA, Yuji SATO, Yoshihiko SHIBUYA, Hannah TOMIO, Pasith TANGHANAKANOND, Tomoyuki HONDA, Tomomasa SHIBUYA, Kamachi KOH, Hiroki UTO

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19 (5) 774-783 2021/09

    Publisher: Japan Society for Aeronautical and Space Sciences

    DOI: 10.2322/tastj.19.774  

    eISSN: 1884-0485

  34. On-Board Computers for Micro-Satellites Peer-reviewed

    Toshinori KUWAHARA, Shinya FUJITA, Yuji SATO, Yoshihiko SIBUYA, Alperen PALA, Hannah TOMIO, Yu MURATA, Yuji SAKAMOTO

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19 (4) 485-492 2021/07

    ISSN: 1884-0485

  35. Development and Evaluation of a CCSDS-Based Communication System on Microsatellite ALE-1 Peer-reviewed

    Hannah TOMIO, Yoshihiko SHIBUYA, Toshinori KUWAHARA, Shinya FUJITA, Yuji SATO, Koh KAMACHI

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19 (3) 368-376 2021/05

    ISSN: 1884-0485

  36. System Design, Development and Ground Verification of a Separable De-Orbit Mechanism for the Orbital Manoeuvre of Micro-Satellite ALE-1 Peer-reviewed

    Alperen PALA, Toshinori KUWAHARA, Tomoyuki HONDA, Hiroki UTO, Tetsuya KANEKO, Adrien POTIER, Pasith TANGDHANAKANOND, Shinya FUJITA, Yoshihiko SHIBUYA, Yuji SATO, Tomomasa SHIBUYA, Koh KAMACHI

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19 (3) 360-367 2021/05

    ISSN: 1884-0485

  37. Radiometric calibration for a multispectral sensor onboard risesat microsatellite based on lunar observations

    Masataka Imai, Junichi Kurihara, Toru Kouyama, Toshinori Kuwahara, Shinya Fujita, Yuji Sakamoto, Yuji Sato, Sei Ichi Saitoh, Takafumi Hirata, Hirokazu Yamamoto, Yukihiro Takahashi

    Sensors 21 (7) 2021/04

    DOI: 10.3390/s21072429  

    ISSN: 1424-8220

  38. In-Flight Target Pointing Calibration of the Diwata-2 Earth Observation Microsatellite

    Edgar Paolo Violan, Shinya Fujita, Yuji Sato, Yuji Sakamoto, Julie Ann Banatao, Toshinori Kuwahara, Kazuya Yoshida

    IEEE Aerospace Conference Proceedings 2021-March 2021/03/06

    DOI: 10.1109/AERO50100.2021.9438197  

    ISSN: 1095-323X

  39. Design, Implementation and In-orbit Demonstration of Attitude and Orbit Control System for Micro-satellite ALE-2

    Yuji Sato, Shinya Fujita, Toshinori Kuwahara, Yoshihiko Shibuya, Koh Kamachi

    2021 IEEE/SICE International Symposium on System Integration, SII 2021 662-668 2021/01/11

    DOI: 10.1109/IEEECONF49454.2021.9382731  

  40. Development and Demonstration of the Mission Control System for Artificial Meteor Generating Micro-satellites

    Yoshihiko Shibuya, Yuji Sato, Hannah Tomio, Toshinori Kuwahara, Shinya Fujita, Koh Kamachi, Hayato Watanabe

    2021 IEEE/SICE International Symposium on System Integration, SII 2021 531-536 2021/01/11

    DOI: 10.1109/IEEECONF49454.2021.9382604  

  41. Automated Mission Planning System for Ocean Observation of Micro-satellite RISESAT

    Naoya Shiraishi, Kazuki Kibune, Shinya Fujita, Yoshihiko Shibuya, Yuji Sato, Toshinori Kuwahara, Junichi Kurihara

    2021 IEEE/SICE International Symposium on System Integration, SII 2021 656-661 2021/01/11

    DOI: 10.1109/IEEECONF49454.2021.9382717  

  42. Accuracy of satellite orbit prediction and optical design of optical ground station beacons for satellite-to-ground optical communication

    H. Takenaka, H. Kunimori, S. Fujita, T. Kuwahara, T. Kubooka, T. Fuse, M. Toyoshima

    Proceedings of SPIE - The International Society for Optical Engineering 11852 2021

    Publisher: SPIE

    DOI: 10.1117/12.2599372  

    ISSN: 1996-756X 0277-786X

  43. Orbit Design and Analysis of Artificial Meteors Generating Micro-satellites

    Yoshihiko Shibuya, Toshinori Kuwahara, Yuji Sato, Shinya Fujita, Hayato Watanabe, Yui Mitsuhashi

    Proceedings of the International Astronautical Congress, IAC B4 2021

    ISSN: 0074-1795

  44. Lunar Calibration and its Validation for a Multispectral Sensor Onboard Risesat Microsatellite.

    Masataka Imai, Junichi Kurihara, Toru Kouyama, Toshinori Kuwahara, Shinya Fujita 0002, Yuji Sakamoto, Sei-Ichi Saitoh, Takafumi Hirata, Hirokazu Yamamoto, Yuji Sato, Yukihiro Takahashi

    IEEE International Geoscience and Remote Sensing Symposium(IGARSS) 7775-7778 2021

    Publisher: IEEE

    DOI: 10.1109/IGARSS47720.2021.9555066  

  45. Structural Design and Verification of Aeronomy Study Satellite ALE-1 Peer-reviewed

    Pasith TANGDHANAKANOND, Toshinori KUWAHARA, Yoshihiko SHIBUYA, Tomoyuki HONDA, Alperen Ahmed PALA, Shinya FUJITA, Yuji SATO, Tomomasa SHIBUYA, Koh KAMACHI

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19 (1) 42-51 2021/01

    ISSN: 1884-0485

  46. Double Fail-Safe Attitude Control System for Artificial Meteor Microsatellite ALE-1 Peer-reviewed

    Shinya FUJITA, Yuji SATO, Toshinori KUWAHARA, Yuji SAKAMOTO, Yoshihiko SHIBUYA, Koh KAMACHI

    AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19 (1) 9-16 2021/01

    ISSN: 1884-0485

  47. Inflight Radiometric Calibration for a Multi-Band Sensor Onboard Risesat with the Moon

    Masataka Imai, Toru Kouyama, Junichi Kurihara, Toshinori Kuwahara, Shinya Fujita, Yuji Sakamoto, Sei Ichi Saitoh, Takafumi Hirata, Yukihiro Takahashi

    International Geoscience and Remote Sensing Symposium (IGARSS) 6222-6225 2020/09/26

    DOI: 10.1109/IGARSS39084.2020.9323468  

  48. A High Spatial Resolution Multispectral Sensor on the RISESAT Microsatellite Peer-reviewed

    Junichi KURIHARA, Toshinori KUWAHARA, Shinya FUJITA, Yuji SATO, Kosuke HANYU, Morokot SAKAL, Yu MURATA, Hannah TOMIO, Yukihiro TAKAHASHI, Wing-Huen IP

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 18 (5) 186-191 2020/09

    Publisher: Japan Society for Aeronautical and Space Sciences

    DOI: 10.2322/tastj.18.186  

    eISSN: 1884-0485

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    <p>Nano/microsatellites play a significant role in Earth observation with the emerging constellation of high spatial resolution satellites. However, there are technological limitations in their spectral resolution. In this paper, we present an overview of a high spatial resolution multispectral sensor, the High-Precision Telescope (HPT), which was developed originally for the RISING-2 microsatellite and subsequently improved for the Rapid International Scientific Experiment Satellite (RISESAT) microsatellite. The HPTs were also installed on the DIWATA-1 and DIWATA-2 microsatellites, but they are different from those in the RISING-2 and RISESAT microsatellites in terms of number of spectral bands. The HPT on the RISESAT has the largest number of spectral bands in a series of the high spatial resolution multispectral sensors. The RISESAT was successfully launched by the Epsilon-4 launch vehicle on 18 January 2019. The preliminary results obtained in the commissioning phase of the operation demonstrate the expected performance of the HPT.</p>

  49. Establishment of the Ground Evaluation and Operational Training System of Artificial Meteor Micro-satellite ALE-1 Peer-reviewed

    Yuji SATO, Shinya FUJITA, Toshinori KUWAHARA, Tomoyuki HONDA, Yuji SAKAMOTO, Yoshihiko SHIBUYA, Koh KAMACHI

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 18 (3) 84-92 2020/05

    Publisher: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    DOI: 10.2322/tastj.18.84  

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    <p>The Space Robotics Laboratory (SRL) of Tohoku University and ALE Co., Ltd. have developed a 60-kg-class microsatellite ALE-1, which generates artificial meteors by releasing meteor source pellets towards the Earth. The purpose of this research is to establish a system for ground evaluation and operation training of ALE-1. This satellite requires an accurate orbit and attitude determination technique for operation safety and mission success. A triple redundant system with multiple independent sensors is adopted for ensuring safe operation. A generic ground evaluation system “MEVIμS” is applied to evaluate such a complicated satellite bus system. MEVIμS has a high reliability and flexibility based on the results of its application to past micro-satellite projects. This system contains a satellite simulator with a space dynamics calculator with a high accuracy as well as mathematical models of the space environment and satellite components. A hardware-in-the-loop simulation can be carried out to evaluate the satellite hardware with on-board software by connecting to the simulator virtually. The performance evaluation of the attitude control system and comprehensive mission operational tests were carried out by MEVIμS. The simulation result demonstrated that ALE-1 reached a sufficient level of attitude control accuracy to realize the mission. The result also confirmed that the mission sequence was performed successfully as the mission feasibility and the operation safety were validated. ALE-1 was launched by the fourth Epsilon rocket on January 18, 2019 and initial operation is in progress. Further improvement of the ALE-1 system can be executed by repeated operation training under various conditions to enhance the chance of mission success.</p>

  50. Commercial Uncooled Microbolometer Camera Applied to 50-kg Class Satellite Peer-reviewed

    Tetsuya Fukuhara, Yuji Sakamoto, Toshinori Kuwahara, Nobuo Sugimura, Kazuya Yoshida, Yukihiro Takahashi

    IEEE GEOSCIENCE AND REMOTE SENSING LETTERS 17 (2) 332-336 2020/02

    DOI: 10.1109/LGRS.2019.2918197  

    ISSN: 1545-598X

    eISSN: 1558-0571

  51. Ground Evaluation of the Attitude Control System of 3U-CubeSat IHI-SAT Peer-reviewed

    Yu Murata, Yuji Sato, Morokot Sakal, Toshinori Kuwahara, Shinya Fujita, Yuko Kawasoe, Ryu Shinohara, Taku Izumiyama

    2020 IEEE/SICE INTERNATIONAL SYMPOSIUM ON SYSTEM INTEGRATION (SII) 771-776 2020

    ISSN: 2474-2317

  52. Design and Evaluation of Thruster Control Approach for Micro-satellite ALE-2 Peer-reviewed

    Yuji Sato, Shinya Fujita, Toshinori Kuwahara, Yoshihiko Shibuya, Koh Kamachi, Junichiro Kawaguchi, Yuki Kubo, Yuichiro Nada, Kaoru Ohashi

    2020 IEEE/SICE INTERNATIONAL SYMPOSIUM ON SYSTEM INTEGRATION (SII) 477-482 2020

    ISSN: 2474-2317

  53. Preliminary Results of Very Small Optical Transmitter (VSOTA) on Microsatellite RISESAT Peer-reviewed

    Hiroo Kunimori, H. Takenaka, T. Kubo-oka, T. Fuse, M. Toyoshima, H. Tomio, S. Fujita, T. Kuwahara

    IEEE International Conference on Space Optical Systems and Applications 2019 1-5 2019/10

  54. RISEPix—A Timepix-based radiation monitor telescope onboard the RISESAT satellite

    Robert Filgas, Milan Malich, Toshinori Kuwahara, Jan Broulím, Michael Holík, Morokot Sakal, Yu Murata, Hannah Tomio, Stefan Gohl, Johan M. Pineda T.

    Astronomische Nachrichten 340 (7) 674-680 2019/08/01

    DOI: 10.1002/asna.201913674  

    ISSN: 0004-6337

    eISSN: 1521-3994

  55. Orbit Verification Result of De-orbit Mechanism Demonstration CubeSat FREEDOM Peer-reviewed

    Hiroki Uto, Toshiyuki Mogi, Toshinori Kuwahara

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 17 (3) 295-300 2019/05

  56. Optical communication experiment using a 1kg class optical communication transmitter onboard microsatellite RISESAT

    桒原 聡文, 藤田 伸哉, 佐藤 悠司, Tomio Hannah, Sakal Morokot, 國森 裕生, 竹中 秀樹

    Optronics : 光技術コーディネートジャーナル 38 (2) 83-87 2019/02

    Publisher: オプトロニクス社

    ISSN: 0286-9659

  57. Development and Ground Evaluation of Ground-Target Tracking Control of Microsatellite RISESAT

    Shinya FUJITA, Yuji SATO, Toshinori KUWAHARA, Yuji SAKAMOTO, Kazuya YOSHIDA

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 17 (2) 120-126 2019

    Publisher: Japan Society for Aeronautical and Space Sciences

    DOI: 10.2322/tastj.17.120  

    eISSN: 1884-0485

  58. Optical communication experiment with microsatellite body-pointing using VSOTA on RISESAT

    Hideki Takenaka, Hiroo Kunimori, Toshinori Kuwahara, Yuji Sakamoto, Shinya Fujita, Homio Tomio, Morokot Sakal, Junichi Kurihara, Toshihiro Kubo-Oka, Tetsu Fuse, Morio Toyoshima

    IET Conference Publications 2019 (CP774) 2019

    DOI: 10.1049/cp.2019.1247  

  59. Attitude Maneuvering Sequence Design of High-Precision Ground Target Tracking Control for Multispectral Earth Observations Peer-reviewed

    Shinya Fujita, Yuji Sato, Toshinori Kuwahara, Yuji Sakamoto, Kazuya Yoshida

    2019 IEEE/SICE INTERNATIONAL SYMPOSIUM ON SYSTEM INTEGRATION (SII) 153-158 2019

    DOI: 10.1109/SII.2019.8700434  

    ISSN: 2474-2317

  60. Development and Ground Evaluation of Fast Tracking Algorithm for Star Trackers Peer-reviewed

    Sato Yuji, KUWAHARA Toshinori, Fujita Shinya, Sakamoto Yuji, Yoshida Kazuya

    Trans. JSASS Aerospace Tech. Japan 16 (3) 202-209 2018/04

    ISSN: 1884-0485

  61. Design of a MEMS-Mirror-based Laser Pointing Control System of Optical Transponder for Micro-satellites Peer-reviewed

    KUWAHARA Toshinori, Fujita Shinya, Sato Yuji, Suzuki Shota, Okajima Lena

    Trans. JSASS Aerospace Tech. Japan 16 (3) 285-290 2018/04

    Publisher: Japan Society for Aeronautical and Space Sciences

    DOI: 10.2322/tastj.16.285  

    ISSN: 1884-0485

    eISSN: 1884-0485

  62. HPT: A High Spatial Resolution Multispectral Sensor for Microsatellite Remote Sensing Peer-reviewed

    Junichi Kurihara, Yukihiro Takahashi, Yuji Sakamoto, Toshinori Kuwahara, Kazuya Yoshida

    SENSORS 18 (2) 619 2018/02

    DOI: 10.3390/s18020619  

    ISSN: 1424-8220

    eISSN: 1424-8220

  63. HPT: A High Spatial Resolution Multispectral Sensor for Microsatellite Remote Sensing Peer-reviewed

    Kurihara Junichi, Takahashi Yukihiro, Sakamoto Yuji, KUWAHARA Toshinori, Kazuya Yoshida

    Sensors 619 (18) 1-11 2018/02

  64. Evaluation of thermal analysis of orbital environment of microsatellite ALE-1

    Mina Konaka, Shinya Fujita, Yuji Sato, Tomomasa Shibuya, Tohsinori Kuwahara, Koh Kamachi

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

    ISSN: 0074-1795

  65. Assembly and integration of optical downlink terminal vsota on microsatellite risesat

    Hannah Tomio, Toshinori Kuwahara, Shinya Fujita, Yuji Sato, Morokot Sakal, Hiroo Kunimori, Toshihiro Kubooka, Hideki Takenaka, Yoshihiko Saito, Morio Toyoshima

    Proceedings of SPIE - The International Society for Optical Engineering 11180 2018

    DOI: 10.1117/12.2536134  

    ISSN: 0277-786X

    eISSN: 1996-756X

  66. Improvement and Verification of Satellite Dynamics Simulator Based on Flight Data Analysis Peer-reviewed

    Sato Yuji, Fujita Shinya, KUWAHARA Toshinori, Katagiri Hiroto, Sakamoto Yuji, Yoshida Kazuya

    2017 IEEE/SICE International Symposium on System Integration (SII) 686-691 2017/12

    DOI: 10.1109/SII.2017.8279301  

    ISSN: 2474-2317

  67. Development and Ground Evaluation of Optical Ground Station Tracking Control System of Microsatellite RISESAT Peer-reviewed

    Fujita Shinya, Sato Yuji, KUWAHARA Toshinori

    Proceedings of the 2017 IEEE/SICE International Symposium on System Integration 2018-January 201-207 2017/12

    DOI: 10.1109/SII.2017.8279212  

  68. On-Ground Verification of Attitude Control System for 50-kg-class Microsatellite Using a Hardware-in-the-Loop-Simulator

    Fujita Shinya, Yuji Sato, Toshinori Kuwahara, Yuji Sakamoto, Kazuya Yoshida

    68th International Astronautical Congress 9 6141-6150 2017/09/25

    ISSN: 0074-1795

  69. Microsatellite bus system technologies of Tohoku University

    Toshinori Kuwahara, Yuji Sakamoto, Shinya Fujita, Yuji Sato, Ryo Taba, Hiroto Katagiri, Masafumi Endo, Pasith Tangdhanakanond, Tomoyuki Honda, Kazuya Yoshida

    1st IAA North East Asia Symposium on Small Satellites 2017/08/21

  70. Safety Assessment and Verification Results for Micro and Nano Satellites with Deployable Mechanism

    Yuji Sakamoto, Shinya Fujita, Toshinori Kuwahara, Kazuya Yoshida

    1st IAA North East Asia Symposium on Small Satellites 2017/08/21

  71. Software Demodulation Technique for the Stora and Forward System of Vietnam's first Micro-Satellite MicroDragon

    Toshinori Kuwahara, James Harpur, Ngo Thanh Cong, Ta Phuong Linh, Tran Van Ninh, Nguyen Minh Thao, Yuji Sakamoto, Kasuya Yoshida, Kaname Kojima, Takahiro Shinke, Tomoya Mochizuki

    31st International Symposium on Space Technology and Science 2017/06/21

  72. Tracking Control System Design and Evaluation of a Small Mobile Optical Ground Station for Satellite-to-Ground Optical Communication

    Masafumi Hiraoka, Toshinori Kuwahara, Yuji Sato, Shinya Fujita, Shunsuke Kawasaki, Daichi Morita, Toshiyuki Mogi, Shouta Suzuki, Lena Okajima

    31st International Symposium on Space Technology and Science 2017/06/21

  73. Design of a MEMS-Mirror-based Laser Pointing Control System of Optical Transponder for Micro-satellites

    Shunsuke Kawasaki, Toshinori Kuwahara, Masafumi Hiraoka, Toshiyuki Mogi, Daichi Morita, Shota Suzuki, Kazufumi Fukuda, Shinya Fujita, Yuji Sato, Lena Okajima

    31st International Symposium on Space Technology and Science 16 (3) 285-290 2017/06/21

    Publisher: Japan Society for Aeronautical and Space Sciences

    DOI: 10.2322/tastj.16.285  

    eISSN: 1884-0485

  74. Static Closed Loop Simulation for Ground-Target Tracking Control of Microsatellite RISESAT

    Shinya Fujita, Yuji Sato, Toshinori Kuwahara, Yuji Sakamoto, Kazuya Yoshida

    31st International Symposium on Space Technology and Science 2017/06/21

  75. Scalable Nano-Satellite Platform for Low-Cost Space Education

    Toshinori Kuwahara, James Harpur, Shinya Fujita, Yuji Sato, Ta Phuong Linh, Ngo Thanh Cong, Tran Van Ninh, Nguyen Minh Thao, Pasith Tangdhanakanond

    31st International Symposium on Space Technology and Science 2017/06/05

  76. Development and Flight Operations of Microsatellite Bus System for DIWATA-1

    Yuji Sakamoto, Ariston Gonzalez, John Leur Labrador, Gerwin Policarpio Guba, Harold Bryan, Solano Paler, Toshinori Kuwahara, Kazuya Yoshida, Tetsuro Ishida, Junichi Kurihara, Yukihiro Takahashi

    31st International Symposium on Space Technology and Science 2017/06/05

  77. Development and Ground Evaluation of Fast Tracking Algorithm for Star Trackers

    Yuji Sato, Toshinori Kuwahara, Shinya Fujita, Yuji Sakamoto, Kazuya Yoshida

    31st International Symposium on Space Technology and Science 16 (3) 2017/06/05

    ISSN: 1884-0485

  78. Development of an Improved Micro-satellite Simulator Environment for Attitude Determination and Control System Verification through DIWATA-1 Flight Data Analysis

    John Leur Labrador, Ariston Gonzalez, Yuji Sakamoto, Toshinori Kuwahara, Kazuya Yoshida

    31st International Symposium on Space Technology and Science 2017/06/05

  79. Design and Implementation of an Attitude Determination Module with Real-Time Sensor Calibration for Small-Satellite Systems including performance Verification using DIWATA-1 Flight Data

    Ariston Gonzalez, John Leur Labrador, Yuji Sakamoto, Toshinori Kuwahara, Kazuya Yoshida

    31st International Symposium on Space Technology and Science 2017/06/05

  80. Design and Implementation of a Thermopile-Based Earth Sensor Peer-reviewed

    Toshinori KUWAHARA, Kazufumi FUKUDA, Nobuo SUGIMURA, Yuji SAKAMOTO, Kazuya YOSHIDA, Ariana DORSA, Pietro PAGANI, Franco Z. BERNELLI

    Transactions of Japan Society for Aeronautical and Space Science (JSASS) Aerospace Technology Japan 14 (ists30) Pf_77-Pf_81 2016/10/01

    Publisher: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    DOI: 10.2322/tastj.14.Pf_77  

    More details Close

    <p>In recent years, microsatellites have attracted great attention for their low cost, rapid development, and utilization capability. Demand for more requirements is increasing, and reliable attitude control is indispensable for secure operation. An Earth sensor is typically used to detect the direction of Earth's center relative to the spacecraft's attitude. Unlike Sun sensors, an Earth sensor can be functional even in the eclipse region in orbit, which enables a spacecraft to determine its attitude regardless of orbital position. The thermopile-based Earth sensor developed in this research is designed to have full sky coverage, i.e., it is operational independent of satellite attitude. Therefore, it can be used in safe-hold-mode operation. As a result of this research, an Earth sensor is realized by utilizing multiple thermopile sensors. The geocentric vector can be determined from the output voltages of thermopiles that are mounted on the entire satellite in a distributed manner and pointed in different directions. In order to establish a data processing algorithm, the output voltage and angle characteristics of the sensors were investigated analytically and experimentally. A numerical model of the sensor was developed, and its performance in orbit was evaluated in a software-based simulation and verification environment.</p>

  81. Improvement of Star Sensor in Generic Test Environment Peer-reviewed

    Nobuo SUGIMURA, Tatsuaki HASHIMOTO, Toshinori KUWAHARA, Yuji SAKAMOTO, Kazuya YOSHIDA, Yuji SATO, Tomohiro TAKANO

    Transactions of Japan Society for Aeronautical and Space Science (JSASS) Aerospace Technology Japan 14 (ists30) Pf_97-Pf_103 2016/10/01

  82. Development and Flight Results of Microsatellite Bus System for RISING-2 Peer-reviewed

    Yuji SAKAMOTO, Nobuo SUGIMURA, Kazufumi FUKUDA, Toshinori KUWAHARA, Kazuya YOSHIDA, Junichi KURIHARA, Tetsuya FUKUHARA, Yukihiro TAKAHASHI

    Transactions of Japan Society for Aeronautical and Space Science (JSASS) Aerospace Technology Japan 14 (ists30) Pf_89-Pf_96 2016/10/01

  83. Structural Design of De-orbit Mechanism Demonstration CubeSat FREEDOM Peer-reviewed

    Toshiyuki Mogi, Toshinori Kuwahara, Hiroki Uto

    Transactions of Japan Society for Aeronautical and Space Science (JSASS) Aerospace Technology Japan 14 (ists30) 61-68 2016/10/01

    Publisher: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    DOI: 10.2322/tastj.14.Pf_61  

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    <p>With increasing number of microsatellite launches, the mitigation of space debris is becoming a pressing problem. An easy-handling de-orbit device is required to deal with this issue. However, existing devices face some problems when being installed in a microsatellite. These problems include the volume, direction in which the booms are extended, and battery consumption. Since 2010, Tohoku University and Nakashimada Engineering Works, Ltd., have been developing a De-Orbit Mechanism (DOM) that deploys a thin film to drag microsatellites down to reenter the atmosphere. A DOM deployment procedure was devised to achieve light weight and low power consumption. For an early orbit demonstration of the DOM technology, Tohoku University and Nakashimada Engineering Works, Ltd., are developing a single-unit-size CubeSat named "FREEDOM," which aims to demonstrate a DOM. The DOM for FREEDOM is capable of deploying a thin square film with edge lengths of 1500 mm out of a total satellite mass of less than 1.33 kg. The film size vs. satellite weight ratio of the FREEDOM will be the highest in Japan and is one of the highest in the world. FREEDOM is planned to be delivered to the International Space Station by the Japan Aerospace Exploration Agency and will be deployed into Low Earth Orbit (LEO) in 2016. This paper describes the structural design and verification results of FREEDOM.</p>

  84. Low-Cost Simulation and Verification Environment for Micro-Satellites Peer-reviewed

    Toshinori Kuwahara, Kasufumi Fukuda, Nobuo Sugimura, Tatsuaki Hashimoto, Yuji Sakamoto, Kazuya Yoshida

    Transactions of Japan Society for Aeronautical and Space Science (JSASS) Aerospace Technology Japan 14 (ists30) Pf_83-Pf_88 2016/10/01

    Publisher: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    DOI: 10.2322/tastj.14.Pf_83  

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    <p>The Space Robotics Laboratory (SRL) of Tohoku University has been developing micro-satellites for years and has gained experience in their development, verification, integration, and operation. The SRL has recently started the development of model-based simulation, verification, and integration environment to realize rapid and cost-effective development of reliable micro-satellites. The conceptual design and its functionality have been verified through the real-life 50-kg-class micro-satellite projects RISING-2 and RISESAT. The developed environment can be utilized in different configurations such as full-software simulation, hardware-in-the-loop simulation, and even flight operation, depending on demands in each satellite development phase. This environment is designed to be modular and flexible. The minimum hardware configuration can be a single personal computer, which enables low-cost introduction of a satellite system simulator for a wide range of projects in a variety of project phases. It can be utilized for general micro-satellite missions and possibly even much smaller space systems in the future. Micro-satellite RISING-2 is the first satellite tested by means of this environment. Functionality of the developed simulation and verification environment was evaluated by comparing the ground simulation results and flight data obtained by RISING-2.</p>

  85. Development of fast tracking algorithm using nearest neighbor star search approach Peer-reviewed

    Yuji Sato, Nobuo Sugimura, Toshinori Kuwahara, Kazuya Yoshida

    IEEE Aerospace Conference Proceedings 2016- 1-8 2016/06/27

    Publisher: IEEE Computer Society

    DOI: 10.1109/AERO.2016.7500673  

    ISSN: 1095-323X

  86. Development of Fast Tracking Algorithm Using Nearest Neighbor Star Search Approach Peer-reviewed

    Yuji Sato, Nobuo Sugimura, Toshinori Kuwahara, Kazuya Yoshida

    2016 IEEE AEROSPACE CONFERENCE 2016

    ISSN: 1095-323X

  87. Attitude Determination and Control System for Nadir Pointing Using Magnetorquer and Magnetometer Peer-reviewed

    Nobuo Sugimura, Toshinori Kuwahara, Kazuya Yoshida

    2016 IEEE AEROSPACE CONFERENCE 1-12 2016

    DOI: 10.1109/AERO.2016.7500665  

    ISSN: 1095-323X

  88. Improvement of Star Sensor in Generic Test Environment

    Nobuo SUGIMURA, Tatsuaki HASHIMOTO, Toshinori KUWAHARA, Yuji SAKAMOTO, Kazuya YOSHIDA, Yuuki SATO, Tomohiro TAKANO

    30th International Symposium on Space Technology and Science 2015/07/10

  89. Structural Design of De-orbit Mechanism Demonstration CubeSat FREEDOM

    Toshiyuki MOGI, Toshinori KUWAHARA, Hiroki UTO

    30th International Symposium on Space Technology and Science 14 (30) Pf_61-Pf_68 2015/07/10

    Publisher: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    DOI: 10.2322/tastj.14.Pf_61  

    More details Close

    <p>With increasing number of microsatellite launches, the mitigation of space debris is becoming a pressing problem. An easy-handling de-orbit device is required to deal with this issue. However, existing devices face some problems when being installed in a microsatellite. These problems include the volume, direction in which the booms are extended, and battery consumption. Since 2010, Tohoku University and Nakashimada Engineering Works, Ltd., have been developing a De-Orbit Mechanism (DOM) that deploys a thin film to drag microsatellites down to reenter the atmosphere. A DOM deployment procedure was devised to achieve light weight and low power consumption. For an early orbit demonstration of the DOM technology, Tohoku University and Nakashimada Engineering Works, Ltd., are developing a single-unit-size CubeSat named "FREEDOM," which aims to demonstrate a DOM. The DOM for FREEDOM is capable of deploying a thin square film with edge lengths of 1500 mm out of a total satellite mass of less than 1.33 kg. The film size vs. satellite weight ratio of the FREEDOM will be the highest in Japan and is one of the highest in the world. FREEDOM is planned to be delivered to the International Space Station by the Japan Aerospace Exploration Agency and will be deployed into Low Earth Orbit (LEO) in 2016. This paper describes the structural design and verification results of FREEDOM.</p>

  90. Design and Implementation of a Thermopile-based Earth Sensor

    Toshinori KUWAHARA, Kazufumi FUKUDA, Nobuo SUGIMURA, Yuji SAKAMOTO, Kazuya YOSHIDA, Arianna DORSA, Pietro PAGANI, Franco Z. BERNELLI

    30th International Symposium on Space Technology and Science 14 (30) Pf_77-Pf_81 2015/07/10

    Publisher: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    DOI: 10.2322/tastj.14.Pf_77  

    More details Close

    <p>In recent years, microsatellites have attracted great attention for their low cost, rapid development, and utilization capability. Demand for more requirements is increasing, and reliable attitude control is indispensable for secure operation. An Earth sensor is typically used to detect the direction of Earth's center relative to the spacecraft's attitude. Unlike Sun sensors, an Earth sensor can be functional even in the eclipse region in orbit, which enables a spacecraft to determine its attitude regardless of orbital position. The thermopile-based Earth sensor developed in this research is designed to have full sky coverage, i.e., it is operational independent of satellite attitude. Therefore, it can be used in safe-hold-mode operation. As a result of this research, an Earth sensor is realized by utilizing multiple thermopile sensors. The geocentric vector can be determined from the output voltages of thermopiles that are mounted on the entire satellite in a distributed manner and pointed in different directions. In order to establish a data processing algorithm, the output voltage and angle characteristics of the sensors were investigated analytically and experimentally. A numerical model of the sensor was developed, and its performance in orbit was evaluated in a software-based simulation and verification environment.</p>

  91. Flight Verification of Attitude Determination Methods for Microsatellite RISING-2 Using Magnetometers, Sun Sensors, Gyro Sensors, and Observation Images Peer-reviewed

    Yuji Sakamoto, Nobuo Sugimura, Kazufumi Fukuda, Toshinori Kuwahara, Kazuya Yoshida

    the 30th International Symposium on Space Technology and Science (30th ISTS), Kobe, Japan, July 4 - 10, 2015. 2015/06

  92. Development of Attitude Control System and Testing Simulator for Microsatellite MicroDragon Peer-reviewed

    Trinh Hoang Quan, Nguyen Son Duong, Nguyen Van Thuc, Le The Soat, Cao Xuan Hiep, Toshinori Kuwahara, Yuji Sakamoto, Kazuya Yoshida, Pham Anh Tuan

    the 30th International Symposium on Space Technology and Science (30th ISTS), Kobe, Japan, July 4 - 10, 2015. 2015/06

  93. Optical payloads on microsatellites hodoyoshi and UNIFORM

    Maeda, K., Iwasaki, A., Nakasuka, S., Kuwahara, T., Akiyama, H.

    Optical Payloads for Space Missions 2015

    DOI: 10.1002/9781118945179.ch42  

  94. Verification of RISING-2 Attitude Control System in Generic Hardware-in-the-Loop Simulation Environment

    Nobuo Sugimura, Yoshihiro Tomioka, Toshinori Kuwahara, Yuji Sakamoto, Kazufumi Fukuda, Kazuya Yoshida

    65th International Astronautical Congress 2014/10/03

  95. TRITEL-JMS: A Three-Dimensional Silicon Detector Telescope Dedicated for Operation on Board Microsatellite RISESAT Peer-reviewed

    Toshinori Kuwahara, Attila Hirn, Istvan Apathy, Laszlo Bodnar, Antal Csoke, Sandor Deme, Tamas Pazmandi, Peter Szanto, Gabor Troznai, Balazs Zabori

    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan 12 (ists29) p. Tr_13-p. Tr_17 2014/08/27

    DOI: 10.2322/tastj.12.Tr_13  

  96. Timepix-Based Miniaturized Radiation Micro-Tracker for the Micro-Satellite RISESAT Peer-reviewed

    Carlos Granja, Michal Platkevic, Daniel Turecek, Vaclav Kraus, Stanislav Pospisil, Jan Jakubek, Michael Holik, Zdenek Vykydal, Ondrej Valach, Ivan Caicedo, Toshinori Kuwahara

    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan 12 (ists12) p.Pf_21-p.Pf_26 2014/08/23

    DOI: 10.2322/tastj.12.Tr_7  

  97. Low-Cost Development and Operation of Tohoku University Scientific Microsatellites,

    Yuji Sakamoto, Toshinori Kuwahara, Kazuya Yoshida

    11th Annual Meeting, Asia Oceania Geosciences Society (AOGS 2014) 2014/07

  98. Establishment of the Ground Testing Environment for Verification and Integration of Micro-satellite Peer-reviewed

    Yoshihiro Tomioka, Kazufumi Fukuda, Nobuo Sugimura, Yuji Sakamoto, Toshinori Kuwahara, Kazuya Yoshida

    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan 12 (ists29) p. Tf_33-p. Tf_38 2014/06/12

    DOI: 10.2322/tastj.12.Tf_33  

  99. Development and Evaluation of Small Size Whole Sky Observation Camera System for Micro-Satellite Peer-reviewed

    Kento Ohya, Shinichi Kimura, Toshinori Kuwahara

    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan 12 (ists29) p.Tf_27-p.Tf_31 2014/05/09

    DOI: 10.2322/tastj.12.Tf_27  

  100. Attitude Control for Earth Observation Microsatellite RISING-2 Peer-reviewed

    Nobuo Sugimura, Kazufumi Fukuda, Masato Fukuyama, Yoshihiro Tomioka, Toshinori Kuwahara, Yuji Sakamoto, Kazuya Yoshida, Yukihiro Takahashi

    Small Satellite Missions for Earth Observation: Missions & Technologies, Operational Responsive Space, Commercial Constellations 1 (4) 262-269 2014

  101. Development of Small Optical Transmitter for Microsatellites Peer-reviewed

    Kazufumi Fukuda, Tatsuaki Hashimoto, Toshinori Kuwahara, Hiroo Kunimori, Kazuya Yoshida

    2014 IEEE/SICE INTERNATIONAL SYMPOSIUM ON SYSTEM INTEGRATION (SII) 370-375 2014

    DOI: 10.1109/SII.2014.7028066  

  102. Model-Based Environment for Verification and Integration of Micro-Satellites Peer-reviewed

    Toshinori Kuwahara, Yoshihiro Tomioka, Kazufumi Fukuda, Nobuo Sugimura, Yuji Sakamoto, Kazuya Yoshida

    19th IFAC Symposium on Automatic Control in Aerospac 2013/09/03

  103. Impacts of Space Plug-And-Play Technology on Micro and Nano-Satellites Peer-reviewed

    Toshinori Kuwahara, Yoshihiro Tomioka, Kazufumi Fukuda, Kazuya Yoshida, Johan Baeckstroem, Fredrik Bruhn

    19th IFAC Symposium on Automatic Control in Aerospace 2013/09/03

  104. Generic Thermal Design Strategy for 50kg-class Micro-Satellites

    Yoshihiro Tomioka, Toshinori Kuwahara, Yuji Sakamoto, Kazufumi Fukuda, Nobuo Sugimura, Kazuya Yoshida

    64th International Astronautical Congress 2013/09

  105. DYNAMIC CLOSED LOOP ATTITUDE CONTROL SIMULATION AND VERIFICATION ENVIRONMENT FOR MICRO-SATELLITES

    Kazufumi Fukuda, Toshinori Kuwahara, Yoshihiro Tomioka, Yuji Sakamoto, Kazuya Yoshida

    64th International Astronautical Congress 2013/09

  106. A SERIES OF DE-ORBIT MECHANISM FOR ACTIVE PREVENTION AND REDUCTION OF SPACE DEBRIS

    Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto, Yoshihiro Tomioka, Kazufumi Fukuda, Nobuo Sugimura

    64th International Astronautical Congress 2013/09

  107. MODEL-BASED SIMULATION AND VERIFICATION ENVIRONMENT FOR SPACE PLUG-AND-PLAY AVIONICS Peer-reviewed

    Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto, Yoshihiro Tomioka, Kazufumi FUkuda, Nobuo Sugimura

    64th International Astronautical Congress 2013/09

  108. Constellation of Earth Observation Micro-satellites with Multi-spectral High-resolution Telescopes Peer-reviewed

    Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto, Yoshihiro Tomioka, Kazufumi Fukuda, Nobuo Sugimura, Junichi Kurihara, Tetsuya Fukuhara, Yukihiro Takahashi

    Small Satellite Conference 2013 2013/08/13

  109. Laser Data Downlink System of Micro-satellite RISESAT Peer-reviewed

    Toshinori Kuwahara, Kazuya Yoshida, Yoshihiro Tomioka, Kazufumi Fukuda, Hiroo Kunimori, Morio Toyoshima, Tetsuharu Fuse, Toshihiro Kubooka

    Small Satellite Conference 2013 2013/08/12

  110. Application of Thin-Film Deployment Mechanism as De-orbit Device from Low Earth Orbit Peer-reviewed

    KUWAHARA Toshinori, TOMIOKA Yoshihiro, HASHIMOTO Tatsuaki

    Technical report of IEICE. SANE 113 (88) 75-79 2013/06/20

    Publisher: The Institute of Electronics, Information and Communication Engineers

    ISSN: 0913-5685

    More details Close

    Tohoku University has been very active in small satellite development for years and has already successfully developed, tested, and launched its first microsatellite SPRITE-SAT (renamed as RISING-1 after the launch) in 2009, and is completing the second and third microsatellites RISING-2 and RISESAT, and has also launched a CubeSat RAIKO which was deployed from the International Space Station (ISS) into low Earth orbit in 2012. Tohoku University has initiated a development activity of thin film deployment mechanisms in order to de-orbit used microsatellites mainly by means of the residual atmospheric drags. Three different sizes of models have been so far developed, and verified on ground. The smallest (500mm square) is flown on the RAIKO and will be deployed in 2013, the second (1500mm square) will fly on the RISING-2 to be launched in 2013, and the third (2500mm square) on the RISESAT. The important characteristic of this mechanism is that the size of the sail can be modified very easily depending on the requirements of the spacecraft. By preparing deferent size of sails, this kind of de-orbit mechanisms can become the standard prevention and reduction measures of space debris. This mechanism has also potentials to be applied to return capsule deceleration from the ISS, to elements of space solar power systems, to active orbit maneuver device, and more.

  111. TriTel-JMS: A Three-dimensional Silicon Detector Telescope Dedicated for Operation on Board Microsatellite RISESAT Peer-reviewed

    Toshinori Kuwahara, Attila Hirn, Istvan Apathy, Laszlo Bodnar, Antal Csoke, Sandor Deme, Tamas Pazmandi, Peter Szanto, Gabor Troznai, Balazs Zabori

    29th International Symposium on SpaceTechnology and Science 2013/06/05

    DOI: 10.2322/tastj.12.Tr_13  

  112. Development and Evaluation of Small Size Whole Sky Observation Camera System for Micro-Satellite Peer-reviewed

    Kento Ohya, Shinichi Kimura, Toshinori Kuwahara

    29th International Symposium on SpaceTechnology and Science 2013/06/05

    DOI: 10.2322/tastj.12.Tf_27  

  113. Qualification and Characterization of Very Small Optical Transponder Component (VSOTA) Flight Model for a Micro Satellite RISESAT Peer-reviewed

    Hiroo Kunimori, Toshihiro Kubo-oka, Hideki Takenaka, Tetsuharu Fuse, Morio Toyoshima, Toshinori Kuwahara, Yoshihiro Tomioka, Kazufumi Fukuda, Masato Fukuyama, Kazuya Yoshida

    29th International Symposium on SpaceTechnology and Science 2013/06/05

  114. Dynamic Test Table with Spherical Air Bearing for Microsatellite Peer-reviewed

    Kazufumi Fukuda, Toshinori Kuwahara, Yoshihiro Tomioka, Nobuo Sugimura, Kazuya Yoshida

    29th International Symposium on SpaceTechnology and Science 2013/06/05

  115. Establishment of the Ground Testing Environment for Verification and Integration of Micro-satellite Peer-reviewed

    Yoshihiro Tomioka, Kazuya Yoshida, Yuji Sakamoto, Toshinori Kuwahara, Kazufumi Fukuda, Nobuo Sugimura

    29th International Symposium on SpaceTechnology and Science 2013/06/05

    DOI: 10.2322/tastj.12.Tf_33  

  116. Attitude Control System of International Scientific Micro-satellite RISESAT Peer-reviewed

    Toshinori KUWAHARA, Kazufumi FUKUDA, Yoshihiro TOMIOKA, Masato FUKUYAMA, Yuji SAKAMOTO, Kazuya YOSHIDA

    29th International Symposium on SpaceTechnology and Science 2013/06/03

  117. A Coordination Method of Gondola Attitude Control and Telescope Pointing Control on a Balloon-Borne Telescope Peer-reviewed

    Toshihiko Nakano, Yasuhiro Shoji, Yuji Sakamoto, Toshinori Kuwahara, Makoto Watanabe, Yukihiro Takahashi, Makato Taguchi, Kazuya Yoshida

    29th International Symposium on SpaceTechnology and Science 2013/06/03

  118. Performance evaluation for pointing control system of the balloon-borne telescope

    T. Nakano, R. Fujimura, Y. Sakamoto, K. Yoshida, T. Kuwahara, Y. Shoji, M. Taguchi, M. Yamamoto, Y. Takahashi

    Advances in the Astronautical Sciences 146 381-391 2013/04/24

    ISSN: 0065-3438

  119. Space Plug and Play Compatible Earth Observation Payload Instruments Peer-reviewed

    Toshinori Kuwahara, Yoshihiro Tomioka, Kazufumi Fukuda, Yuji Sakamoto, Kazuya Yoshida

    9th IAA Symposium on Small Satellites for Earth Observation 2013/04/10

  120. Attitude Control for Earth Observation Microsatellite RISING-2 Peer-reviewed

    Nobuo Sugimura, Kazufumi Fukuda, Masato Fukuyama, Yoshihiro Tomioka, Toshinori Kuwahara, Yuji Sakamoto, Kazuya Yoshida, Yukihiro Takahashi

    9th IAA Symposium on Small Satellites for Earth Observation 2013/04/09

  121. Down link optical communication experiment using micro satellite body pointing and collaboration with co-located science instrument

    Hiroo Kunimori, Toshihiro Kubooka, Tetsuharu Fuse, Hideki Takenaka, Morio Toyoshima, Toshinori Kuwahara, Kazuya Yoshida, Yoshihiro Tomioka, Kazufumi Fukuda, Junichi Kurihara, Yukihiro Takahashi

    Proceedings of the International Astronautical Congress, IAC 4 3132-3136 2013

    ISSN: 0074-1795

  122. PERFORMANCE EVALUATION FOR POINTING CONTROL SYSTEM OF THE BALLOON-BORNE TELESCOPE Peer-reviewed

    T. Nakano, R. Fujimura, Y. Sakamoto, K. Yoshida, T. Kuwahara, Y. Shoji, M. Taguchi, M. Yamamoto, Y. Takahashi

    SPACE FOR OUR FUTURE 146 381-391 2013

    ISSN: 1081-6003

  123. Model-based environment for verification and integration of micro-satellites

    T. Kuwahara, Y. Tomioka, K. Fukuda, N. Sugimura, Y. Sakamoto, K. Yoshida

    IFAC Proceedings Volumes (IFAC-PapersOnline) 19 230-235 2013/01/01

    ISSN: 1474-6670

  124. Impacts of space plug-and-play technology on micro- and nano-satellites Peer-reviewed

    T. Kuwahara, Y. Tomioka, K. Fukuda, Y. Sakamoto, K. Yoshida, J. Baeckstroem, F. Bruhn

    IFAC Proceedings Volumes (IFAC-PapersOnline) 19 289-294 2013/01

    ISSN: 1474-6670

  125. Development and Operation of Tohoku University Micro Satellite Series for Earth Observation Science

    Yuji Sakamoto, Toshinori Kuwahara, Kazuya Yoshida

    Asian Conference on Remote Sensing (ACRS 2013) 2013

  126. Requirement of Optical communication downlink experiment using body pointing and evaluation method of satellite attitude Peer-reviewed

    Hiroo Kunimori, Tetsuharu Fuse, Hideki Takenaka, Toshihiro Kubooka, Morio Toyoshima, Toshinori Kuwahara, Kazufumi Fukuda, Yoshihiro Tomioka

    The 56th Space Sciences and Technology Conference 2012/11/22

  127. Missions and Development Status of the Hodoyoshi-Program's Second Micro-satellite RISESAT Peer-reviewed

    Toshinori Kuwahara, Yuji Sakamoto, Kazuya Yoshida, Junichi Kurihara, Yukihiro Takahashi, Atsushi Takada, Hiroshi Yamakawa

    The 56th Space Sciences and Technology Conference 2012/11/21

  128. Deployment Analysis of Convex Tapes as Extension Booms of Membrane Structure Peer-reviewed

    Keiji Ainoura, Shingo Shimazaki, Yasuyuki Miyazaki, Toshinori Kuwahara

    The 56th Space Sciences and Technology Conference 2012/11/21

  129. System Description and Results of Ground Test for Cubesat "RAIKO" Peer-reviewed

    Hitoshi Yagisawa, Yuji Sakamoto, Yuta Tanabe, Nobuo Sugimura, Toshinori Kuwahara, Kazuya Yoshida

    UN/Japan Nano-satellite Symposium 2012/10/10

  130. Establishment of the Enviroment to Support Cost-effective and Rapid Development of Micro-satellites Peer-reviewed

    Yohihiro Tomioka, Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto

    63rd International Astronautical COngress 2012/10/05

  131. Space Plug and Play Avionics for Small Satellites

    Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto

    63rd International Astronautical COngress 2012/10/03

  132. Qualification Results of a Sail Deployment Mechanism for Active Prevention and Reduction of Space Debris

    Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto

    63rd International Astronautical COngress 2012/10/03

  133. THE LAIKABOARD { PROPOSAL FOR A GENERIC, MODULAR AND DISTRIBUTED OPEN SOURCE SATELLITE ON-BOARD DATA HANDLING SYSTEM Peer-reviewed

    Claas Ziemke, Toshinori Kuwahara

    63rd IAC – International Astronautical Congress 2012/10/03

  134. Evaluation of Power Control System for Micro and Nano Satellites by Hardware-in-the-Loop Simulator Peer-reviewed

    Yuji Sakamoto, Toshinori Kuwahara, Kazuya Yoshida

    Small Satellite Conference 2012 2012/08/13

  135. International Scientific Micro-satelite RISESAT based on Space Plug and Play Avionics Peer-reviewed

    Toshinori Kuwahara, Yuji Sakamoto, Kazuya Yoshida

    Small Satellite Conference 2012 2012/08/13

  136. 超小型地球観測衛星「RISING-2」の開発報告 - 多波長望遠鏡による積乱雲及びスプライト現象の観測 - Peer-reviewed

    冨岡義弘, 坂本祐二, 桒原聡文

    The Institute of Electronics, Information and Communication Engineers (IEICE), The Committee on Space, Aeronautical and Navigational Electronics Technical Report 112 (107) 83-88 2012/06

    Publisher: The Institute of Electronics, Information and Communication Engineers

    ISSN: 0913-5685

    More details Close

    The development of 50kg-class micro-satellite RISING-2 was started in 2009 by Tohoku University. At the time of Jun, 2012, the development of flight model of hardware was completed, and the adjustment of software and others is continued aimed its launch in 2013. The satellite has a telescope with 10cm diameter and lm focal length, and it takes images with 5m resolution. It can observe multi-spectrum images using liquid crystal tunable filter as well as RGB color photos. The primary mission is the observation of cumulonimbus clouds in visible near infrared. Also, transient luminous events in upper atmosphere such as sprite are observed using CMOS sensors. This paper shows the latest specifications of FM, and the result of test was carried out so far and task-schedule of future.

  137. VSOTA: ほどよし2号機の光通信ミッションについて Peer-reviewed

    國森裕生, 桒原聡文, 吉田和哉

    The Institute of Electronics, Information and Communication Engineers (IEICE), The Committee on Space, Aeronautical and Navigational Electronics Technical Report 2012/06

  138. Design of a satellite ground station within a global network Peer-reviewed

    Jochum, A, Beyermann, U, Laufer, R, Kuwahara, T, Hyde, T

    9th IAA Symposium on Small Satellites for Earth Observation 2012/04/09

  139. Ka-band High-speed Communication Systems on Small Satellites for Future Advanced Communication Networks and Earth Observations Peer-reviewed

    Toshinori Kuwahara, Michael Lengowski, Urlich Beyermann, Alexander Uryu, Hans-Peter Roeser

    Transactions of the Japan Society for Aeronautical and Space Science, Aerospace Technology JAPAN 8 (27) Tj_11-Tj_16 2012/02/18

    Publisher: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    DOI: 10.2322/tastj.8.Tj_11  

    ISSN: 1884-0485

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    The goal of this paper is to describe the capabilities and application methods of Ka-band communication systems for small satellites indicating contributions to future advanced communication networks and Earth observations. This study is based on the actual experience on the design of the Ka-band high-speed communication system of the small satellite Flying Laptop, which is developed at the Institute of Space Systems of the Universität Stuttgart. The objectives of the Ka-band communication system is to demonstrate high-speed communications with a data rate of up to 500 Mbit/s as well as to conduct scientific Earth observations. Flying Laptop satellite is also equipped with a Ku-band signal transmitter. The attenuation of the two transmission signals in Ka-/Ku-bands are measured with ground stations to estimate the local precipitation rate. The mathematical background and operational scenario of this measurement is summarized. The received Ka-band transmission signal is measured in different meteorological conditions to identify attenuation characteristics of the Ka-band signal due to rain, clouds, trace gases and so forth, which is of great interest for utilization of Ka-band frequencies for future broadband communications.

  140. Micro-Satellites for International Scientific Missions

    YOSHIDA Kazuya, SAKAMOTO Yuji, KUWAHARA Toshinori, TAKAHASHI Yukihiro

    Journal of The Society of Instrument and Control Engineers 51 (5) 438-444 2012

    Publisher: The Society of Instrument and Control Engineers

    DOI: 10.11499/sicejl.51.438  

    ISSN: 0453-4662

  141. Ground Test of Attitude Control System for Micro Satellite RISING-2 Peer-reviewed

    Nobuo Sugimura, Kazufumi Fukuda, Yoshihiro Tomioka, Masato Fukuyama, Yuji Sakamoto, Toshinori Kuwahara, Tetuya Fukuhara, Kazuya Yoshida, Yukihiro Takahashi

    2012 IEEE/SICE INTERNATIONAL SYMPOSIUM ON SYSTEM INTEGRATION (SII) 301-306 2012

    DOI: 10.1109/SII.2010.5708354  

  142. Development and Verification Environment for the Attitude Determination and Control System of the Micro-satellite RISESAT Peer-reviewed

    Toshinori Kuwahara, Yuji Sakamoto, Kazuya Yoshida, Yoshihiro Tomioka, Kazushi Fukuda, Nobuo Sugimura, Masato Fukuyama, Yoshihiko Shibuya

    第20回スペース・エンジニアリング・コンファレンス【SEC’11】 10 (28) Td_11-Td_16 2012/01

    Publisher: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    DOI: 10.2322/tastj.10.Td_11  

    ISSN: 1884-0485

    More details Close

    The 50-kg class micro satellite RISING-2 is now under development by Tohoku University and Hokkaido University. The development is at Flight Model phase and some components are tested to evaluate its specifications. In this paper, the endurance tests using vacuum chamber and thermal test chamber in Tohoku University are described. There was no problem in those tests. In addition, the attitude control accuracy of the RISING-2 was analyzed in the simulation. This simulation based on component specifications and also included noise data. The results show the pointing error angle was less than required error angle.

  143. Development Method of Command and Data Handling System Peer-reviewed

    Yuji Sakamoto, Toshinori Kuwahara, Steve Battazzo, Kazufumi Fukuda, Hitoshi Yagisawa, Kazuya Yoshida

    第20回スペース・エンジニアリング・コンファレンス【SEC’11】 2012/01

  144. Lessons Learned on Structural Design of 50kg Micro-satellites based on Three Real-life Micro-satellite Projects Peer-reviewed

    Yoshihiro Tomioka, Kazuya Yoshida, Yuji Sakamoto, Toshinori Kuwahara, Kazufumi Fukuda, Nobuo Sugimura

    2012 IEEE/SICE INTERNATIONAL SYMPOSIUM ON SYSTEM INTEGRATION (SII) 319-324 2012

  145. The Pointing Control Method of Balloon-Borne Telescope Compensating the Motion of Flexible Base Peer-reviewed

    Toshihiko Nakano, Yasuhiro Shoji, Mutsumi Yamamoto, Ko Hamamoto, Jumpei Nakamoto, Masataka Imai, Yuji Sakamoto, Toshinori Kuwahara, Makoto Watanabe, Yukihiro Takahashi, Kazuya Yoshida, Makoto Taguchi

    2012 IEEE/SICE INTERNATIONAL SYMPOSIUM ON SYSTEM INTEGRATION (SII) 313-318 2012

    DOI: 10.1109/SII.2012.6427318  

  146. Lessons Learned on Structural Design of 50kg Micro-satellites based on Three Real-life Micro-satellite Projects Peer-reviewed

    Yoshihiro Tomioka, Kazuya Yoshida, Yuji Sakamoto, Toshinori Kuwahara, Kazufumi Fukuda, Nobuo Sugimura

    2012 IEEE/SICE INTERNATIONAL SYMPOSIUM ON SYSTEM INTEGRATION (SII) 319-324 2012

    DOI: 10.1109/SII.2012.6427314  

  147. Radiation Effect Mitigation Methods for Electronic Systems Peer-reviewed

    Toshinori Kuwahara, Yoshihiro Tomioka, Kazufumi Fukuda, Nobuo Sugimura, Yuji Sakamoto

    2012 IEEE/SICE INTERNATIONAL SYMPOSIUM ON SYSTEM INTEGRATION (SII) 307-312 2012

    DOI: 10.1109/SII.2012.6427324  

  148. Satellite-to-Ground Optical Communication System on Low Earth Orbit Micro-satellite RISESAT Peer-reviewed

    Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto, Yoshihiro Tomioka, Kazufumi Fukuda, Masato Fukuyama, Nobuo Sugimura, Hiroo Kunimori, Hideki Takenaka, Morio Toyoshima, Tetsuharu Fuse, Toshihiro Kubooka

    2012 IEEE/SICE INTERNATIONAL SYMPOSIUM ON SYSTEM INTEGRATION (SII) 939-944 2012

    DOI: 10.1109/SII.2012.6427336  

  149. Ground Test of Attitude Control System for Micro Satellite RISING-2 Peer-reviewed

    Nobuo Sugimura, Kazufumi Fukuda, Yoshihiro Tomioka, Masato Fukuyama, Yuji Sakamoto, Toshinori Kuwahara, Tetuya Fukuhara, Kazuya Yoshida, Yukihiro Takahashi

    2012 IEEE/SICE INTERNATIONAL SYMPOSIUM ON SYSTEM INTEGRATION (SII) 301-306 2012

    DOI: 10.1109/SII.2012.6427322  

  150. System Integration of a Star Sensor for the Small Earth Observation Satellite RISING-2 Peer-reviewed

    Toshinori Kuwahara, Steve Battazzo, Yoshihiro Tomioka, Kazufumi Fukuda, Yuji Sakamoto, Kazuya Yoshida

    Transactions of the Japan Society for Aeronautical and Space Science, Aerospace Technology JAPAN 2012

    DOI: 10.2322/tastj.10.Td_1  

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  151. Development Status of Micro-satellite De-orbit Mechanisms for Active Prevention and Reduction of Space Debris Peer-reviewed

    Toshinori Kuwahara, Kazuya Tomioka, Yuji Sakamoto

    3rd Nano-satellite Symposium 2011/12/12

  152. Micro-satellite structure system for cost-effective and rapid development Peer-reviewed

    Yoshihiro Tomioka, Toshinori Kuwahara, Yuji Sakamoto

    3rd Nano-satellite Symposium 2011/12/12

  153. Development Method of Command and Data Handling System for Micro and Nano Satellites Peer-reviewed

    Yuji Sakamoto, Toshinori Kuwahara, Kazuya Yoshida

    3rd Nano-satellite Symposium 2011/12/12

  154. ほどよし2号機の開発状況 Peer-reviewed

    桒原聡文, 坂本祐二, 吉田和哉

    第55回宇宙科学技術連合講演会 2011/11/30

  155. 次世代型超小型衛星の低コスト短期開発手法及びその支援環境の構築

    冨岡義弘, 桒原聡文, 坂本祐二, 吉田和哉

    第55回宇宙科学技術連合講演会 2011/11/30

  156. 50kg級超小型衛星の効率的な熱設計および評価手法 Peer-reviewed

    坂本祐二, 桒原聡文, 吉田和哉

    第55回宇宙科学技術連合講演会 2011/11/30

  157. A Sail Deployment Mechanism for Active Prevention and Reduction of Space Debris Peer-reviewed

    Toshinori Kuwahara, Yoshida Kazuya, Yuji Sakamoto

    62nd International Astronautical Congress 2011/10/03

  158. An integrated development framework for rapid development of platform-independent and reusable satellite on-board software Peer-reviewed

    Claas Ziemke, Toshinori Kuwahara, Ivan Kossev

    ACTA ASTRONAUTICA 69 (7-8) 583-594 2011/09

    DOI: 10.1016/j.actaastro.2011.04.011  

    ISSN: 0094-5765

  159. Development Status and Performance Verification of Balloon-Borne Telescope for Optical Observation of Planets

    Toshihiko Nakano, Yuji Sakamoto, Kazuya Yohida, Toshinori Kuwahara, Steve Battazzo, Ryosuke Fujimura, Yasuhiro Shoji, Makoto Taguchi, Mutumi Yamamoto, Yukihiro Takahashi

    The 28th International Symposium on Space Technology and Science (ISTS), Naha, Japan, June 2011, No.2011-k-27. 2011/06

  160. The Evaluation Tests of the Attitude Control System of the 50-kg Micro Satellite RISING-2 Peer-reviewed

    Kazufumi Fukuda, Nobuo Sugimura, Yuji Sakamoto, Toshinori Kuwahara, Kazuya Yoshida, Yukihiro Takahashi

    Proceedings of the 28th International Symposium on Space Technology and Science 10 (28) Td_11-Td_16 2011/06

    Publisher: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    DOI: 10.2322/tastj.10.Td_11  

    ISSN: 1884-0485

    More details Close

    The 50-kg class micro satellite RISING-2 is now under development by Tohoku University and Hokkaido University. The development is at Flight Model phase and some components are tested to evaluate its specifications. In this paper, the endurance tests using vacuum chamber and thermal test chamber in Tohoku University are described. There was no problem in those tests. In addition, the attitude control accuracy of the RISING-2 was analyzed in the simulation. This simulation based on component specifications and also included noise data. The results show the pointing error angle was less than required error angle.

  161. System Integration of a Star Sensor for the Small Earth Observation Satellite RISING-2 Peer-reviewed

    Toshinori Kuwahara, Steve Battazzo, Yoshihiro Tomioka, Yuji Sakamoto, Kazuya Yoshida

    Proceedings of the 28th International Symposium on Space Technology and Science 2011/06

    DOI: 10.2322/tastj.10.Td_1  

  162. Development Status and Operation Plan of 50-kg Microsatellite RISING-2 for Earth Observations by Multi-Spectrum Instruments Peer-reviewed

    Yuji Sakamoto, Toshinori Kuwahara, Kazufumi Fukuda, Kazuya Yoshida, Tetsuya Fukuhara, Junichi Kurihara, Yukihiro Takahashi

    Proceedings of the 28th International Symposium on Space Technology and Science 2011/06

  163. A Low-cost Mass Memory Unit for Small Satellites Peer-reviewed

    Marek Dittmar, Mahdi Najmabadi, Toshinori Kuwahara, Hans-Peter Roeser

    Proceedings of the 28th International Symposium on Space Technology and Science 2011/06

  164. A Series of 50kg-Class Micro-Satellites for Advanced Science Missions Peer-reviewed

    Kazuya Yoshida, Yuji Sakamoto, Toshinori Kuwahara

    8th IAA Symposium on Small Satellites for Earth Observation 2011/04

  165. Mission and System of the Earth Observation Microsatellite RISING-2 Peer-reviewed

    Toshinori Kuwahara, Yuji Sakamoto, Kazuya Yoshida, Yukihiro Takahashi, Tetsuya Fukuhara, Junichi Kurihara

    8th IAA Symposium on Small Satellites for Earth Observation 2011/04

  166. International Scientific Missions on a Japan-led Micro-satellite Peer-reviewed

    Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto, Yukihiro Takahashi, Junichi Kurihara, Hiroshi Yamakawa, Atsushi Takada

    2nd Nano-Satellite Symposium 2011/03

  167. One satellite per country - How emerging space-faring nations can benefit from technology transfer through free open-source projects

    Claas Ziemke, Toshinori Kuwahara

    62nd International Astronautical Congress 2011, IAC 2011 5 3604-3612 2011

  168. A Japanese microsatellite bus system for international scientific missions Peer-reviewed

    Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto, Yukihiro Takahashi, Junichi Kurihara, Hiroshi Yamakawa, Atsushi Takada

    62nd International Astronautical Congress 2011, IAC 2011 5 3699-3706 2011

  169. Static closed loop test system for attitude control system of micro satellite RISING-2 Peer-reviewed

    Kazufumi Fukuda, Yuji Sakamoto, Toshinori Kuwahara, Kazuya Yoshida, Yukihiro Takahashi

    2011 IEEE/SICE International Symposium on System Integration, SII 2011 890-895 2011

    DOI: 10.1109/SII.2011.6147567  

  170. Satellite system integration based on space plug and play avionics Peer-reviewed

    Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto, Yoshihiro Tomioka, Kazufumi Fukuda

    2011 IEEE/SICE International Symposium on System Integration, SII 2011 896-901 2011

    DOI: 10.1109/SII.2011.6147568  

  171. An Integrated Development Framework for Rapid Development of Platform-Independent and Reusable Satellite On-board Software Peer-reviewed

    Claas Ziemke, Toshinori Kuwahara, Ivan Kossev

    61th International Astronautical Congress 2010/09

  172. A commercial procedure execution engine completing the command chain of a university satellite simulation infrastructure Peer-reviewed

    Michael Fritz, Albert Falke, Toshinori Kuwahara, Hans-Peter Roeser, Steve Pearson, Andrew Witts, Jens Eickhoff

    ACTA ASTRONAUTICA 66 (5-6) 950-953 2010/03

    DOI: 10.1016/j.actaastro.2009.06.004  

    ISSN: 0094-5765

  173. Attitude control system of micro satellite RISING-2 Peer-reviewed

    Kazufumi Fukuda, Toshihiko Nakano, Yuji Sakamoto, Toshinori Kuwahara, Kazuya Yoshida, Yukihiro Takahashi

    2010 IEEE/SICE International Symposium on System Integration: SI International 2010 - The 3rd Symposium on System Integration, SII 2010, Proceedings 373-378 2010

    DOI: 10.1109/SII.2010.5708354  

  174. The balloon-borne telescope system for optical observation of planets Peer-reviewed

    Toshihiko Nakano, Yuji Sakamoto, Kazuya Yoshida, Toshinori Kuwahara, Yasuhiro Shoji, Makoto Taguchi, Mutumi Yamamoto, Yukihiro Takahashi

    2010 IEEE/SICE International Symposium on System Integration: SI International 2010 - The 3rd Symposium on System Integration, SII 2010, Proceedings 236-241 2010

    DOI: 10.1109/SII.2010.5708331  

  175. Asynchronous Parallel Reactive System for Intelligent Small Satellite on-Board Computing Systems Peer-reviewed

    Toshinori Kuwahara, Claas Ziemke, Michael Fritz, Jens Eickhoff, Hans-Peter Roeser

    SMALL SATELLITE MISSIONS FOR EARTH OBSERVATION 279-+ 2010

    DOI: 10.1007/978-3-642-03501-2_26  

  176. FPGA-based operational concept and payload data processing for the Flying Laptop satellite Peer-reviewed

    Toshinori Kuwahara, Felix Boehringer, Albert Falke, Jens Eickhoff, Felix Huber, Hans-Peter Roeser

    ACTA ASTRONAUTICA 65 (11-12) 1616-1627 2009/12

    DOI: 10.1016/j.actaastro.2009.04.011  

    ISSN: 0094-5765

  177. FPGA-based On-board Computers for Reconfigurable Computing on Space Systems Peer-reviewed

    Toshinori Kuwahara, Marek Dittmar, Claas Ziemke, Hans-Peter Roeser

    60thInternational Astronautical Congress 2009/10

  178. Simulation-Based Testing of Embedded Attitude Control Algorithms of a FPGA based Micro Satellite Peer-reviewed

    Yasir Muhammad, Toshinori Kuwahara, Claas Ziemke, Michael Fritz, Hans-Peter Roeser

    23rd Annual AIAA/USU Conference on Small Satellites 2009/08

  179. Ka-band High-speed Communication Systems on Small Satellites for Future Advanced Communication Networks and Earth Observations Peer-reviewed

    Toshinori Kuwahara, Michael Lengowski, Ulrich Beyermann, Alexander Uryu, Hans-Peter Roeser

    27th International Symposium on Space Technology and Science 8 (27) Tj_11-Tj_16 2009/06

    Publisher: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    DOI: 10.2322/tastj.8.Tj_11  

    ISSN: 1884-0485

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    The goal of this paper is to describe the capabilities and application methods of Ka-band communication systems for small satellites indicating contributions to future advanced communication networks and Earth observations. This study is based on the actual experience on the design of the Ka-band high-speed communication system of the small satellite Flying Laptop, which is developed at the Institute of Space Systems of the Universität Stuttgart. The objectives of the Ka-band communication system is to demonstrate high-speed communications with a data rate of up to 500 Mbit/s as well as to conduct scientific Earth observations. Flying Laptop satellite is also equipped with a Ku-band signal transmitter. The attenuation of the two transmission signals in Ka-/Ku-bands are measured with ground stations to estimate the local precipitation rate. The mathematical background and operational scenario of this measurement is summarized. The received Ka-band transmission signal is measured in different meteorological conditions to identify attenuation characteristics of the Ka-band signal due to rain, clouds, trace gases and so forth, which is of great interest for utilization of Ka-band frequencies for future broadband communications.

  180. Programmability of FPGAs with the High-level Hardware Description Language Handel-C for Space Applications Peer-reviewed

    Toshinori Kuwahara, Claas Ziemke, Michael Fritz, Mario Kobald, Marek Dittmar, Hans-Peter Roeser

    27th International Symposium on Space Technology and Science 2009/06

  181. Effective Project Management of Small Satellite Projects from the System Engineer’s Point of View, An Example of the Small Satellite Flying Laptop Project Peer-reviewed

    Toshinori Kuwahara, Albert Falke, Hans-Peter Roeser

    Transactions of Japan Society for Aeronautical and Space Science (JSASS) Space Technology Japan 7 (ists26) Pt_1-Pt_8 2009

    Publisher: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    DOI: 10.2322/tstj.7.Pt_1  

    ISSN: 1347-3840

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    The number of the small satellite projects is recently dramatically increasing and there are great demands for effective project management methods for them. The goal of this paper is to propose effective project management methods for small satellite projects, which are obtained through the real-life experience of the small satellite Flying Laptop project. The project management methods implemented in this project maximize the advantages of rapid and cost-effective small satellite approaches. The management of the project is based on project breakdown structures, which are derived from a combination of several existing standards and empirical methods. These management methods use a product tree as the backbone of the management architecture. The project management activities, such as the establishment of a work breakdown structure, drawing and documentation management structures, time scheduling, and cost management is described with real-life examples. Applications of project management tools, including open source software, which play important roles in cost-effective small satellite approaches, are also summarized and examples of them are illustrated. Finally, further possibilities of effective project management with up-coming new management tools are discussed.

  182. Development of a Hardware-in-the-Loop Simulation Environment on an MDVE for FPGA-based On-board Computing Systems Peer-reviewed

    Toshinori Kuwahara, Albert Falke, Claas Ziemke, Jens Eickhoff, Hans-Peter Roeser, Yasir Muhammad

    Transactions of Japan Society for Aeronautical and Space Science (JSASS) Space Technology Japan 7 (ists26) Pf_1-Pf_9 2009

    Publisher: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    DOI: 10.2322/tstj.7.Pf_1  

    ISSN: 1347-3840

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    The goal of this paper is to describe the development of a hardware-in-the-loop simulation and verification environment for Field Programmable Gate Array (FPGA) based on-board computing systems. The underlying simulation environment is the Model-based Development and Verification Environment (MDVE). MDVE is an infrastructure for model-based engineering developed by EADS Astrium. A simulation environment based on MDVE was developed at the Universität Stuttgart. Recently, the demand on applying new high density FPGA technologies for innovative spacecraft on-board computing systems is rising. The small satellite "Flying Laptop" which is built by the Universität Stuttgart is the demonstrator of a FPGA-based on-board computer. In order to develop and verify the hardware and control algorithm of the computer, an extended simulation interface between MDVE and FPGA-based computing systems is established. This environment is capable of software verification and real-time simulation/verification configuration, and enables not only on-board software development but also functional real-time hardware evaluation of all the satellite components under precise space environment models. This paper describes the detailed implementation of this simulation interface and illustrates the obtained simulation results on attitude control algorithm verification and power budget calculation as well as communication timing analysis, which ensure the validity of the implementation.

  183. Operational Design and On-board Payload Data Processing of the small satellite Flying Laptop with an FPGA-based On-board Computer System Peer-reviewed

    Toshinori Kuwahara, Felix Boehringer, Albert Falke, Jens Eickhoff, Felix Huber, Hans-Peter Roeser

    59th International Astronautical Congress 2008/09

  184. Improved Land Surface Temperature Retrieval Method for the Small Satellite Flying Laptop Peer-reviewed

    Ursula Kirchgaessner, Toshinori Kuwahara, Maria von Schoenermark

    59th International Astronautical Congress 2008/09

  185. QSAT Mission Analysis and Operation Plan Design Peer-reviewed

    Alexander Uryu, Josef van, der Ha, Hans-Peter Roeser, Toshinori Kuwahara

    59th International Astronautical Congress 2008/09

  186. Development of On-Orbit Servicing concepts, technology options, and roadmap (Part II): Technical design

    Steve Ulrich, Julia Schwartz, Viqar Abbasi, Duncan Cree, Marianne Daae, David Grover, Jason Hay, Weiliang He, Xiaohu Huang, Shane Jacobs, Zhou Jun, Stephen Kearney, Toshinori Kuwahara, Fiorenzo Lenzi, Halit Mirahmetoglu, Scott Morley, Masato Otani, Massimiliano Pastena, Martina Pinni, Karin Shala, Jian-Feng Shi, Jasvinder Singh Khoral, Manfred Steinkellner, David Treat, Peter Verheyden, Xiao Yong Wang, Charity Weeden

    JBIS-JOURNAL OF THE BRITISH INTERPLANETARY SOCIETY 61 (6) 213-223 2008/06

    ISSN: 0007-084X

  187. Development of On-Orbit Servicing concepts, technology options and roadmap (Part III): Policy considerations

    Charity Weeden, Massimilliano Pastena, Scott Morley, Viqar Abbasi, Duncan Cree, Marianne Daae, David Grover, Jason Hay, Weiliang He, Xiaohu Huang, Shane Jacobs, Zhou Jun, Stephen Kearney, Toshinori Kuwahara, Fiorenzo Lenzi, Halit Mirahmetoglu, Masato Otani, Martina Pinni, Julia Schwartz, Karin Shala, Jian-Feng Shi, Jasvinder Singh Khoral, Manfred Steinkellner, David Treat, Steve Ulrich, Peter Verheyden, Xiao Yong Wang

    JBIS-JOURNAL OF THE BRITISH INTERPLANETARY SOCIETY 61 (6) 224-228 2008/06

    ISSN: 0007-084X

  188. Development of On-Oribit Servicing concepts, technology options and roadmap (Part I): Commercial aspects

    David Grover, Shane Jacobs, Viqar Abbasi, Duncan Cree, Marianne Daae, Jason Hay, Weiliang He, Xiaohu Huang, Zhou Jun, Stephen Kearney, Toshinori Kuwahara, Fiorenzo Lenzi, Halit Mirahmetoglu, Scott Morley, Masato Otani, Massimiliano Pastena, Martina Pinni, Julia Schwartz, Kartn Shala, Jian-Feng Shi, Jasvinder Singh Khoral, Manfred Steinkellner, David Treat, Steve Ulrich, Peter Verheyden, Xiao Yong Wang, Charity Weeden

    JBIS-JOURNAL OF THE BRITISH INTERPLANETARY SOCIETY 61 (6) 203-212 2008/06

    ISSN: 0007-084X

  189. System Design of the Small Satellite Flying Laptop, as the Technology Demonstrator of the FPGA-based On-board Computer System Peer-reviewed

    Toshinori Kuwahara, Felix Huber, Albert Falke, Michael Lengowski, Sebastian Walz, Georg Grillmayer, Hans-Peter Roeser

    58th International Astronautical Congress 2007/09

  190. Earth Remote Sensing with the Stuttgart's Small Satellites Peer-reviewed

    Maria von Schoenermark, Hans-Peter Roeser, Felix Huber, Sebastian Walz, Georg Grillmayer, Michael Lengowski, Albert Falke, Toshinori Kuwahara

    Meteorologentagung 2007 2007/09

  191. Challenges of Small Satellites: New Technology Demonstration of Field Programmable Gate Array On-board Computing System Peer-reviewed

    Toshinori Kuwahara, Albert Falke, Georg Grillmayer, Hans-Peter Roeser

    International Space University Annual Conference 2007 2007/08

  192. Use of Advanced Ion-engine Vehicles to Reduce the Cost of On-orbit Servicing Peer-reviewed

    Toshinori Kuwahara

    International Space University Annual Conference 2007 2007/08

  193. Kyushu University Micro-Satellite QTEX Project Peer-reviewed

    Toshinori Kuwahara, Tetsuo Yasaka, Toshiya Hanada, Hiroshi Hirayama, Yuji Sakamoto, Takamasa Itahashi

    55th International Astronautical Congress 2004/10

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Misc. 4

  1. ISS曝露部搭載型生物培養器(BioCube Unit)開発の進捗状況2022—Development of Plant-Biosatellite Cube-Unit (Plant-BioCube Unit) Mounted on Exposure Area at ISS Platform for Investigation of Plant Life Support Mechanisms in Space Environment 2022

    日出間, 純, 愿山(岡本), 郁, 笠羽, 康正, 桒原, 聡文, 久米, 篤, 永井, 大樹, 橋本, 博文, HIDEMA, Jun, YOSHIYAMA(OKAMOTO), Kaoru, KASABA, Yoshimasa, KUWAHARA, Toshinori, KUME, Atsushi, NAGAI, Hiroki, HASHIMOTO, Hirofumi

    宇宙環境利用シンポジウム 第37回: 令和四年度 = Space Utilization Research, Vol. 37 2022: Proceedings of The Thirty-seventh Space Utilization Symposium 2023/01

    Publisher: 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)

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    第37回宇宙環境利用シンポジウム (2023年1月17日-18日. オンライン開催) Space Utilization Research (January 17-18, 2023. Online Meeting) 資料番号: SA6000180003 F-2

  2. 植物の微小重力下における太陽光影響評価に向けたISS曝露部搭載型植物培養器(Plant-BioCube Unit)エンジニアリングモデルの開発に関する進捗状況—Development of Plant-Biosatellite Cube-Unit (Plant-BioCube Unit) Mounted on Exposure Area at ISS Platform for Investigation of Plant Life Support Mechanisms in Space Environment 2021

    日出間, 純, 愿山(岡本), 郁, 笠羽, 康正, 桒原, 聡文, 久米, 篤, 永井, 大樹, 橋本, 博文, 稲富, 裕光, HIDEMA, Jun, YOSHIYAMA, (OKAMOTOA) Kaoru, KASABA, Yasumasa, KUWAHARA, Yoshinori, KUME, Atsushi, NAGAI, Hiroki, HASHIMOTO, Hirofumi, INATOMI, Yuko

    宇宙環境利用シンポジウム 第36回: 令和三年度 = Space Utilization Research, Vol. 36 2021: Proceedings of The Thirty-sixth Space Utilization Symposium 2022/01

    Publisher: 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)

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    第36回宇宙環境利用シンポジウム (2022年1月18日-19日. オンライン開催) Space Utilization Research (January 18-19, 2022. Online Meeting) 資料番号: SA6000168015 F-03

  3. 植物の微小重力下における太陽光影響評価に向けたISS曝露部搭載型植物培養器(Plant-BioCube Unit)の開発に関する進捗状況—Development of Plant-Bioatellite Cube-Unit (Plant-BioCube Unit) Mounted on Exposure Area at ISS Platform for Investigation of Plant Life Support Mechanisms in Space Environment

    日出間, 純, 愿山(岡本), 郁, 笠羽, 康正, 桒原, 聡文, 久米, 篤, 永井, 大樹, 橋本, 博文, 稲富, 裕光, HIDEMA, Jun, YOSHIYAMA, Kaoru, KASABA, Yasumasa, KUWAHARA, Yoshinori, KUME, Atsushi, NAGAI, Hiroki, HASHIMOTO, Hirofumi, INATOMI, Yuko

    宇宙環境利用シンポジウム 第35回: 令和二年度 = Space Utilization Research, Vol. 35 2020: Proceedings of The Thirty-fifth Space Utilization Symposium 35 2021/01

    Publisher: 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)

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    第35回宇宙環境利用シンポジウム(2021年1月19日-20日. オンライン開催) Space Utilization Research (January 19-20, 2021. Online Meeting) 資料番号: SA6000156006 レポート番号: F-05

  4. Improvement of Model based Power Balance Simulation for Micro-Satellite

    KATAGIRI Hiroto, KUWAHARA Toshinori, FUJITA Shinya, SATO Yuji, TABA Ryo, SAKAMOTO Yuji, OKAJIMA Lena

    The Proceedings of the Space Engineering Conference 2017 (0) 1A7 2017

    Publisher: The Japan Society of Mechanical Engineers

    DOI: 10.1299/jsmesec.2017.26.1A7  

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    Space Robotics Laboratory (SRL) of Tohoku University established a ground test environment system called: MEVIμS (Model-based Environment for Verification and Integration of Micro-Satellites). The core of this system is the software simulator called: SSES (Satellite and Space Environment Simulator). SSES can perform simulations such as attitude control simulation, orbit determination simulation and power balance simulation. This paper aims to improve the results of power balance simulation by adding certain functionalities to the power supply system, which allows SSES to perform the detailed power balance simulation.

Books and Other Publications 11

  1. UNISEC CanSatの20年 -缶サットの奥深さと電子工作の面白さ-

    鶴田佳宏, 佐原宏典, 中西洋喜, 桒原聡文

    電子情報通信学会誌,106, 4, 2023年4月,310-313. 2023

  2. Lessons & Learned for Mission Success of Microsatellites

    2022

    DOI: 10.20637/00048260  

  3. 小型衛星RISESATの光センサー技術と1 kg級光送信器による光通信実験 (特集 光技術×宇宙通信)

    桒原聡文, 藤田伸哉, 佐藤悠司, Tomio Hannah, Sakal Moroko, 國森裕生, 竹中秀樹

    Optronics : 光技術コーディネートジャーナル,38, 2, 2019年2月,83-87. 2019

  4. Optical Payloads for Space Missions

    Korehiro Maeda, Akira Iwasaki, Shinichi Nakasuka, Toshinori Kuwahara, Hiroaki Akiyama

    2015/11

  5. Small Satellite Missions for Earth Observation: Missions & Technologies, Operational Responsive Space, Commercial Constellations

    Nobuo Sugimura, Kazufumi Fukuda, Masato Fukuyama, Yoshihiro Tomioka, Toshinori Kuwahara, Yuji Sakamoto, Kazuya Yoshida, Yukihiro Takahashi

    2013

  6. Micro-Satellites for International Scientific Missions

    YOSHIDA Kazuya, SAKAMOTO Yuji, KUWAHARA Toshinori, TAKAHASHI Yukihiro

    The Society of Instrument and Control Engineers 2012

    DOI: 10.11499/sicejl.51.438  

  7. Small Satellite Missions for Earth Observation: New Mission Concepts and Technology Challenges

    Kazuya Yoshida, Yuji Sakamoto, Toshinori Kuwahara, Yukihiro Takahashi

    2011

  8. Small Satellite Missions for Earth Observation: New Mission Concepts and Technology Challenges

    Toshinori Kuwahara, Yuji Sakamoto, Kazuya Yoshida, Yukihiro Takahashi, Tetsuya Fukuhara, Junichi Kurihara

    2011

  9. Small Satellite Missions for Earth Observation: New Developments and Trends

    Toshinori Kuwahara, Claas Ziemke, Michael Fritz, Jens Eickhoff, Hans-Peter Röser

    Springer 2010/02

  10. ―小型宇宙システム共同開発を支える企業・組織― 大学・企業による小型宇宙システムの共同開発事例 株式会社中島田鉄工所

    川島徳夫, 桒原聡文

    日本航空宇宙学会誌, 第57巻, 第671号, 2009年9月, 363-365. 2009

  11. Developing On-Orbit Servicing Concepts Technology Options and Roadmap

    Toshinori Kuwahara, Team Doctor

    International Space University 2007/08

Show all Show first 5

Presentations 87

  1. UNISEC20年の歴史と今後の展望

    川島レイ, 桒原聡文, 坂本啓, 永田晴紀, 船瀬龍, 宮崎康行, 山﨑政彦, 中須賀真一

    第67回宇宙科学技術連合講演会 2023/10

  2. AIS受信システム実証衛星IHI-SATの運用結果

    川添悠子, 大貝高士, 篠原流, 桒原聡文, 藤田伸哉, 齊藤拓実

    第67回宇宙科学技術連合講演会 2023/10

  3. 国内超小型人工衛星の成功率向上に向けたロードマップ案の提案

    宮田喜久子, 趙孟佑, 鶴田佳宏, 北澤幸人, 桒原聡文

    第67回宇宙科学技術連合講演会 2023/10

  4. 超小型衛星ミッションアシュアランスハンドブックの改訂について

    趙孟佑, 鶴田佳宏, 宮田喜久子, 増田和三, 北澤幸人, 桒原聡文

    第67回宇宙科学技術連合講演会 2023/10

  5. UNISEC超小型衛星ミッションアシュアランス情報共有Webサイトの開発・運用から得られた知見

    鶴田佳宏, 青木位織, 金子颯汰, 宮田喜久子, 増田和三, 趙孟佑, 桒原聡文, 北澤幸人

    第67回宇宙科学技術連合講演会 2023/10

  6. 革新的衛星技術実証プログラムから得られたUNISEC衛星のLessons Learnedとミッションアシュアランス活動

    鶴田佳宏, 河村政昭, 宮田喜久子, 趙孟佑, 中須賀真一, 桒原聡文

    第67回宇宙科学技術連合講演会 2023/10

  7. 再突入技術実証衛星ELS-R100のためのコールドガスRCSを用いた姿勢制御シミュレーション評価

    石原裕大, 桒原聡文, 齊藤拓実, 佐藤悠司

    第67回宇宙科学技術連合講演会 2023/10

  8. コールドガス推進系を有するISS放出キューブサットの軌道上での安全な姿勢軌道制御

    小町咲葵, 藤田伸哉, 武田浩平, 中岡颯, 桒原聡文, 吉田和哉, 川口淳一郎

    第67回宇宙科学技術連合講演会 2023/10

  9. 超小型宇宙望遠鏡衛星のためのMEMSミラーを用いた高精度指向制御手法

    中岡颯, 藤田伸哉, 桒原聡文

    第67回宇宙科学技術連合講演会 2023/10

  10. 高頻度低軌道実験・回収システム実証機 ELS-R100 の開発

    藤田和央, 新玉重貴, 杉村伸雄, 桒原聡文, 小林稜平

    第67回宇宙科学技術連合講演会 2023/10

  11. ISS曝露部搭載型生物培養器(BioCube Unit)開発の進捗状況2022—Development of Plant-Biosatellite Cube-Unit (Plant-BioCube Unit) Mounted on Exposure Area at ISS Platform for Investigation of Plant Life Support Mechanisms in Space Environment 2022

    日出間, 純, 愿山(岡本), 郁, 笠羽, 康正, 桒原, 聡文, 久米, 篤, 永井, 大樹, 橋本, 博文, HIDEMA, Jun, YOSHIYAMA(OKAMOTO), Kaoru, KASABA, Yoshimasa, KUWAHARA, Toshinori, KUME, Atsushi, NAGAI, Hiroki, HASHIMOTO, Hirofumi

    宇宙環境利用シンポジウム 第37回: 令和四年度 = Space Utilization Research, Vol. 37 2022: Proceedings of The Thirty-seventh Space Utilization Symposium 2023/01

    More details Close

    第37回宇宙環境利用シンポジウム (2023年1月17日-18日. オンライン開催) Space Utilization Research (January 17-18, 2023. Online Meeting) 資料番号: SA6000180003 F-2

  12. Accuracy of satellite orbit prediction and optical design of optical ground station beacons for satellite-to-ground optical communication Invited

    H. Takenaka, H. Kunimori, S. Fujita, Toshinori Kuwahara, T. Kubooka, T. Fuse, M. Toyoshima

    ICSO2020 2021/03/31

  13. 植物の微小重力下における太陽光影響評価に向けたISS曝露部搭載型植物培養器(Plant-BioCube Unit)の開発に関する進捗状況—Development of Plant-Bioatellite Cube-Unit (Plant-BioCube Unit) Mounted on Exposure Area at ISS Platform for Investigation of Plant Life Support Mechanisms in Space Environment

    日出間, 純, 愿山(岡本), 郁, 笠羽, 康正, 桒原, 聡文, 久米, 篤, 永井, 大樹, 橋本, 博文, 稲富, 裕光, HIDEMA, Jun, YOSHIYAMA, Kaoru, KASABA, Yasumasa, KUWAHARA, Yoshinori, KUME, Atsushi, NAGAI, Hiroki, HASHIMOTO, Hirofumi, INATOMI, Yuko

    宇宙環境利用シンポジウム 第35回: 令和二年度 = Space Utilization Research, Vol. 35 2020: Proceedings of The Thirty-fifth Space Utilization Symposium 2021/01

    More details Close

    第35回宇宙環境利用シンポジウム(2021年1月19日-20日. オンライン開催) Space Utilization Research (January 19-20, 2021. Online Meeting) 資料番号: SA6000156006 レポート番号: F-05

  14. Preliminary design and case study of Satellite Operation Management System for constellations and ground station network

    坂本祐二, 藤田伸哉, 白石尚也, 桑原聡文, 栗原純一

    日本地球惑星科学連合大会予稿集(Web) 2021

  15. Tools and Methods of Satellite Operation Management System for Constellation of Micro Satellites and Ground Stations

    坂本祐二, 栗原純一, 佐藤悠司, 藤田伸哉, 桑原聡文

    宇宙科学技術連合講演会講演集(CD-ROM) 2021

  16. Ground demonstrations of the High-performance Star Tracker for microsatellites

    中村倫敦, 谷津陽一, 渡邉奎, 松永三郎, 河合誠之, 佐藤悠司, 藤田伸哉, 桑原聡文, 栗原純一, 坂本祐二, 白籏麻衣, 江野口章人, 武山芸英, 上村文彦, 正木哲, 稲葉和男, 丸茂孝一, 吉田政和, 蓮見俊吾, 福田達也

    宇宙科学技術連合講演会講演集(CD-ROM) 2021

  17. Development of Plant-Bioatellite Cube-Unit (Plant-BioCube Unit) Mounted on Exposure Area at ISS Platform for Investigation of Plant Life Support Mechanisms in Space Environment

    HIDEMA Jun, YOSHIYAMA Kaoru, KASABA Yasumasa, KUWAHARA Yoshinori, KUME Atsushi, NAGAI Hiroki, HASHIMOTO Hirofumi, INATOMI Yuko

    2021/01

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    Space Utilization Research (January 19-20, 2021. Online Meeting)

  18. 超小型衛星のターゲットポインティング制御を活用した地球観測システムの研究開発

    藤田伸哉, 桑原聡文, 坂本祐二, 栗原純一, 國森裕生, 竹中秀樹

    電気関係学会東北支部連合大会講演論文集(CD-ROM) 2020

  19. Design of 3U CubeSat Attitude Control System for Demonstration of Space Debris Prevention Device Using Electrodynamic Tether

    佐藤悠司, 藤田伸哉, 澁谷吉彦, 桑原聡文, 鈴木大輔

    宇宙科学技術連合講演会講演集(CD-ROM) 2020

  20. High-resolution Earth Observation by 50-kg Class Microsatellites with Precision Ground Target Pointing

    藤田伸哉, 佐藤悠司, 坂本祐二, 桑原聡文, 栗原純一

    宇宙科学技術連合講演会講演集(CD-ROM) 2020

  21. Development of 3U CubeSat (IHI-SAT) Equipped with AIS Receiver

    川添悠子, 泉山卓, 篠原流, 桑原聡文, 藤田伸哉

    宇宙科学技術連合講演会講演集(CD-ROM) 2020

  22. Construction of ground station network system to support operation of micro satellite constellation

    坂本祐二, 藤田伸哉, 桑原聡文, 栗原純一

    宇宙科学技術連合講演会講演集(CD-ROM) 2020

  23. Orbit Demonstration Progress Report of RISESAT

    桑原聡文, 藤田伸哉, 佐藤悠司, 坂本祐二, 吉田和哉

    宇宙科学技術連合講演会講演集(CD-ROM) 2020

  24. A high spatial resolution multispectral remote sensing by the RISESAT microsatellite

    KURIHARA Junichi, KUWAHARA Toshinori, FUJITA Shinya, SAKAMOTO Yuji, TAKAHASHI Yukihiro

    日本地球惑星科学連合大会予稿集(Web) 2019/05/26

  25. Initial In-orbit Results of MicroDragon

    平松崇, 山浦秀作, 戸梶歩, 白坂成功, 鶴田佳宏, 青柳賢英, 松本健, 中須賀真一, 栗原純一, 高橋幸弘, 桑原聡文, 坂本祐二, 吉田和哉, 増井博一, KIM Sang-kyun, 奥山圭一, CHO Mengu, ANH Tuan Pham

    宇宙科学技術連合講演会講演集(CD-ROM) 2019

  26. Optical Ground Station Facilities for Experiment using a 1kg class Optical Communication Transmitter (VSOTA) onboard Micro Satellite RISESAT

    國森裕生, 竹中秀樹, 久保岡俊宏, 布施哲治, 豊嶋守生, 桑原聡文, 藤田伸哉, 冨尾蓮花

    電子情報通信学会技術研究報告 2019

  27. Simulation Evaluation and On-orbit Demonstration of Attitude Control System for Artificial Meteor Demonstration Satellite ALE-1

    佐藤悠司, 藤田伸哉, 澁谷吉彦, 桑原聡文, 蒲池康

    宇宙科学技術連合講演会講演集(CD-ROM) 2019

  28. Development and On-orbit operation of Attitude Control System of the Microsatellite RISESAT

    藤田伸哉, 佐藤悠司, 桑原聡文, 坂本祐二, 吉田和哉

    宇宙科学技術連合講演会講演集(CD-ROM) 2019

  29. Suggestion of autonomous operation methods for on-demand remote sensing system using microsatellite constellation

    坂本祐二, 桑原聡文, 藤田伸哉, 栗原純一, 國森裕生, 竹中秀樹

    宇宙科学技術連合講演会講演集(CD-ROM) 2019

  30. Orbit Demonstration Progress Report of RISESAT

    桑原聡文, 藤田伸哉, 佐藤悠司, 坂本祐二, 吉田和哉, 栗原純一, 國森裕生, 竹中秀樹

    宇宙科学技術連合講演会講演集(CD-ROM) 2019

  31. The preliminary experiment result using a 1kg class Optical Communication Transmitter and Optical Sensor on board a Microsatellite

    國森裕生, 竹中秀樹, 久保岡俊宏, 豊嶋守生, 桑原聡文, 藤田伸哉, 冨尾蓮花, 坂本祐二, 栗原純一

    宇宙科学技術連合講演会講演集(CD-ROM) 2019

  32. 超小型衛星RISESAT搭載の海洋観測カメラによる沿岸域観測

    齊藤誠一, 平田貴文, ALABIA Irene, 平譯享, 平譯享, 栗原純一, 高橋幸弘, 坂本祐二, 桑原聡文, 藤田伸哉, 羽生浩介, 村田悠, SAKAL Morokot, 冨尾蓮花, 佐藤悠司, LEE Ming-An, 望月貫一郎, 高橋文宏, 村上浩

    日本海洋学会大会講演要旨集 2019

  33. 東北大地上局および運用システムの10年間の実績

    坂本祐二, 桑原聡文, 藤田伸哉

    日本地球惑星科学連合大会予稿集(Web) 2019

  34. RISESAT衛星への超小型光送信器(VSOTA)搭載と光通信実 験のための地上局インタフェース

    國森 裕生, 中園 純一, 比嘉 賢二, 竹中 秀樹, 斉藤 嘉彦, 久保岡 俊宏, 豊嶋 守生, 桒原 聡文, Tomio Hannah

    第62回宇宙科学技術連合講演会 2018/10/24

  35. 膜展開式軌道離脱装置実証衛星FREEDOMの運用結果

    宇戸 大樹, 桒原 聡文

    第62回宇宙科学技術連合講演会 2018/10/24

  36. 人工流れ星ミッション計画と安全設計

    蒲池 康, 澁谷 吉彦, 及川 祐, 山田 将二郎, 飯村 紳一郎, 有坂 市太郎, 高尾 知樹, 岡島 礼奈, 桒原 聡文, 藤田 伸哉, 佐藤 悠司

    宇宙科学技術連合講演会 2018/10/24

  37. RISESAT 姿勢制御システムの開発および地上評価

    藤田伸哉, 佐藤悠司, 桒原聡文, 坂本祐二, 吉田和哉

    宇宙科学技術連合講演会 2018/10/24

  38. ALE衛星プロジェクト概要

    桒原 聡文

    宇宙科学技術連合講演会 2018/10/24

  39. Assembly and Integration of Optical Downlink Terminal VSOTA on Microsatellite RISESAT International-presentation

    Hannah Tomio, Toshinori Kuwahara, Shinya Fujita, Yuji Sato, Morokot Sakal, Hiroo Kunimori, Toshihiro Kubooka, Hideki Takenaka, Yoshihiko Saito, Morio Toyoshima

    International Conference on Space Optics 2018/10/09

  40. Evaluation of Thermal ANALYSIS OF ORBITAL ENVIRONMENT OF MICROSATELLITE ALE-1 International-presentation

    Konaka Mina, Fujita, Shinya, Sato Yuji, Shibuya Tomomasa, KUWAHARA Toshinori, Kamachi Koh

    International Astronautical Congress 2018/10/01

  41. 国際宇宙ステーション衛星放出機会を活用した50kg級衛星 DIWATA-1における国際連携と運用成果

    坂本 祐二, 桒原 聡文, 吉田 和哉, 石田 哲朗, 栗原 純一, 高橋 幸弘

    第62回宇宙科学技術連合講演会 2018/09/24

  42. Strategy of planetary observation by using RISESAT micro-satellite and ground-based telescopes International-presentation

    Masataka Imai, Yukihiro Takahashi, Wing-Huen Ip, Junichi Kurihara, Kazuya Yoshida, Toshinori Kuwahara, Yuji Sakamoto, Mitsuteru Sato, Seiko Takagi

    International Symposium on Lunar & Planetary Science 2018 2018/06/11

  43. Operation results and international collaborations on 50-kg microsatellite DIWATA-1 using satellite deployment service of International Space Station

    坂本祐二, 桑原聡文, 吉田和哉, 石田哲朗, 栗原純一, 高橋幸弘

    宇宙科学技術連合講演会講演集(CD-ROM) 2018

  44. Development and Ground Evaluation of Attitude Control System of the Microsatellite RISESAT

    藤田伸哉, 佐藤悠司, 桑原聡文, 坂本祐二, 吉田和哉

    宇宙科学技術連合講演会講演集(CD-ROM) 2018

  45. Evaluation of thermal analysis of orbital environment of microsatellite ALE-1

    Mina Konaka, Shinya Fujita, Yuji Sato, Tomomasa Shibuya, Tohsinori Kuwahara, Koh Kamachi

    Proceedings of the International Astronautical Congress, IAC 2018/01/01

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    Copyright © 2018 by the International Astronautical Federation (IAF). All rights reserved. The mission of the ALE-1 satellite is to release particles from the satellite, and then to observe the artificial shooting stars from a specific point on the ground by re-entering the meteor source at a target point. In this paper, we propose a thermal design for the ALE-1 satellite, and we show evaluation results that are verified by a Thermal Desktop/SINDA/Fluint. ALE-1 is scheduled for launch from Japan in December 2018 on the Epsilon rocket. Given the surface area and power limitations, passive thermal control is deemed necessary to guarantee a successful mission under extreme environments resulting from the varying orbit beta angles. Based on the worst-case scenario, such as the Hot case and Cold case, we determine that onboard avionics are within temperature tolerance levels. The trajectory of the satellite while maintaining the direction in which the sunlight is most widely received by the satellite in which the effective cross section area with respect to the sunlight was the largest is called the Hot case. Moreover, the trajectory in which only the cover surface of the MLI continues to receive sunlight is called the Cold case. The ALE-1 satellite is with components which are critical for low temperature. The simulation results of ALE-1 satellite found that the temperature can be passively controlled to the desired range by optimizing the thermal resistance of connecting parts, the thermal optical characteristics of the satellite surface, and the double structure configuration of the satellite. We perform thermal simulations of the ALE-1 satellite to modify its performance within the tolerant temperature range.

  46. Design and Ground Evaluation of Attitude Control System of the Microsatellite RISESAT

    藤田伸哉, 佐藤悠司, 桑原聡文, 坂本祐二, 吉田和哉

    宇宙科学技術連合講演会講演集(CD-ROM) 2017

  47. Improvement of Model based Power Balance Simulation for Micro-Satellite

    KATAGIRI Hiroto, KUWAHARA Toshinori, FUJITA Shinya, SATO Yuji, TABA Ryo, SAKAMOTO Yuji, OKAJIMA Lena

    The Proceedings of the Space Engineering Conference 2017

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    Space Robotics Laboratory (SRL) of Tohoku University established a ground test environment system called: MEVIμS (Model-based Environment for Verification and Integration of Micro-Satellites). The core of this system is the software simulator called: SSES (Satellite and Space Environment Simulator). SSES can perform simulations such as attitude control simulation, orbit determination simulation and power balance simulation. This paper aims to improve the results of power balance simulation by adding certain functionalities to the power supply system, which allows SSES to perform the detailed power balance simulation.

  48. On-ground verification of attitude control system for 50-kg-class microsatellite using a hardware-in-the-loop-simulator

    Shinya Fujita, Yuji Sato, Toshinori Kuwahara, Yuji Sakamoto, Kazuya Yoshida

    Proceedings of the International Astronautical Congress, IAC 2017/01/01

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    © 2017 by the International Astronautical Federation. All rights reserved. Space Robotics Laboratory of Tohoku University is currently developing a series of 50-kg-class microsatellites for Earth observation. In this paper, we propose design of an attitude control system (ACS) focusing on its control algorithms and computers. This ACS will be equipped on our 4th microsatellite "RISESAT" and launched by the Epsilon rocket in 2018. The primary mission of RISESAT is multi-spectral Earth observation using a 5 m GSD High-Precision-Telescope with liquid crystal tunable filters. During an observation, RISESAT has to track a ground target with an accuracy of 0.1° and 0.008°/s attitude stability because imaging and wavelength switching take several tens of seconds in total. To solve this problem, we developed a high-speed attitude control computer and precision groundtracking algorithms. Evaluations of the algorithms were carried out by a hardware-in-the-loop simulator "MEVIμS" developed by SRL. We confirmed that the ACS and its algorithms satisfies the mission requirements under the influence of sensor noise and computation time limits.

  49. Development Status of Micro-satellite RISESAT

    2016/09/06

  50. Development of De-orbit Mechanism Demonstration CubeSat FREEDOM

    2015/10/07

  51. 超小型地球観測衛星RISING‐2の開発および初期運用成果

    坂本祐二, 杉村伸雄, 冨岡義弘, 桑原聡文, 吉田和哉, 栗原純一, 福原哲哉, 高橋幸弘

    宇宙科学技術連合講演会講演集(CD-ROM) 2014

  52. 小型衛星サイエンスカメラと光通信機器VSOTAおよび地上局の連携について

    國森裕生, 久保岡俊宏, 桑原聡文, 坂本祐二, 栗原純一

    宇宙科学技術連合講演会講演集(CD-ROM) 2014

  53. Verification of RISING-2 attitude control system in generic Hardware-in-the-Loop Simulation environment

    Nobuo Sugimura, Yoshihiro Tomioka, Toshinori Kuwahara, Yuji Sakamoto, Kazufumi Fukuda, Kazuya Yoshida

    Proceedings of the International Astronautical Congress, IAC 2014/01/01

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    A micro satellite called "RISING-2" was developed by Space Robotics Laboratory (SRL) of Tohoku University, targeting scientific Earth observation on Sun-synchronous orbit using 5 m resolution telescope and technical demonstrations for future constellation by micro satellites. The attitude control system of the RISING-2 gives 3-axis zero-momentum stabilization by using three reaction wheels together with three magnetic torquers for dumping of body angular velocity. The attitude determination system is equipped with two star trackers, a gyro scope, sun direction sensors, a GPS, and a geomagnetic aspect sensor. Its behavior was evaluated by means of generic Hardware-in-the-Loop Simulation (HILS) and verification environment, which is described in detail below. RISING-2 was launched by Japanese 24th H-IIA launch vehicle on May 24th 2014 at 3:05:14 (UTC). This paper describes pre-flight evaluation results of RISING-2 in HILS environment and also includes quick reviews about the first operation in orbit. In general, micro satellites have potentials to be rapidly developed in low cost. To achieve this, A Model-based Environment for Verification and Integration of μ-Satellite named MEVIμS was set up at SRL in parallel with the development of RISING-2 and our third micro-satellite called "RISESAT". In this environment, all satellite subsystems are simulated in software based on actual components including attitude control as well as data handling and power control. MEVIμS is based on a real-time OS to realize real-time simulation of HILS environment. HILS of RISING-2 attitude control system was demonstrated by utilizing the satellite on-board computer and reaction wheels. The star tracker test system was introduced to include the failure detection and time delay. As the results, the system development became more efficient since the attitude control system verification could be carried out all of the time. From the acquisition of the RJSING-2 data in real operation, the reliability of the development environment will be increased by reflecting the results. Furthermore, it will contribute to produce next micro satellite under development. This paper puts an emphasis on the configuration and capabilities of the HILS environment including star tracker test system.

  54. Thermal Analysis of a Laser Diode Circuit for the Optical-Communications Down-Link Equipment (VSOTA) to be Loaded on a Micro Satellite

    2013/10/09

  55. Whole sky image generation process of multi-directional camera system for micro satellite

    2013/10/09

  56. S192024 Knowledge of Thermal Design for Micro and Nano Satellites Based on Design, Test, and Flight Data

    SAKAMOTO Yuji, TOMIOKA Yoshihiro, TANABE Yuta, KUWAHARA Toshinori, YOSHIDA Kazuya

    Mechanical Engineering Congress, Japan 2013/09/08

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    Recently the activities for the development of micro- and nano- satellites are being increased, and Tohoku University has developed total 4 satellites in which 2 satellites are already in space. This paper shows the efficient thermal design techniques including the environmental test method are shown which have been accumulated through the sufficient experience. And the effectiveness of the method are shown by the comparison with analysis and real flight data.

  57. ほどよし二号の開発状況

    桑原聡文, 坂本祐二, 吉田和哉, 栗原純一, 高橋幸弘, 高田淳史, 山川宏

    宇宙科学技術連合講演会講演集(CD-ROM) 2013

  58. Generic thermal design strategy for 50kg-class micro-satellites

    Yoshihiro Tomioka, Toshinori Kuwahara, Yuji Sakamoto, Kazufumi Fukuda, Nobuo Sugimura, Kazuya Yoshida

    Proceedings of the International Astronautical Congress, IAC 2013/01/01

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    Recently, development of Micro-satellites with a mass of 100 kg or less has been paid great attentions. The Space Robotics Laboratory (SRL) of Tohoku University has three 50 kg class Micro-satellite projects. The first satellite, SPRITE-SAT, has been successfully launched into low Earth orbit in 2009 and has obtained useful operational data. Now, the flight model of the second micro-satellite RISING-2 is being integrated and the development of the third micro-satellite RISESAT is ongoing at SRL. The former two have cubic shape and the solar cells are body mounted, while the last one has two deployable solar panels. Satellite is exposed to severe thermal environment in orbit. In the case of micro-satellites, it is difficult to install active thermal control equipment because their volume and mass are limited. Therefore, it is always desired that required thermal condition can be satisfied by passive thermal control method. Though the mass and structural configuration are not exactly the same, micro-satellites developed by SRL have the same thermal design approach. First of all, the satellite's internal main structure has a central pillar configuration where the most of the internal instruments are mounted on. This central pillar is thermally almost isolated from the outer panels. These outer panels are thermally well connected with each other. Furthermore, most of the surfaces of the internal components are bare aluminium surface to isolate radiative coupling. In this way the whole satellite can be regarded as two-nodes system from thermal design point of view, which makes the thermal design process considerably simple and reliable. The parameters to be adjusted are basically the optical characteristics of the outer panels, thermal conductance between the central pillar and the outer panels (which can be adjusted by type, contact area, and thickness of the insulation material). The former defines the total thermal balance between the satellite and the environment, and the latter defines the temperature range of the nodes. This strategy allows step-by-step thermal design approach and is especially suitable to 50kg-class micro-satellites. This paper will describe suggested generic thermal design strategy. The operational data obtained by SPRITE-SAT, as well as the thermal design of RISING-2 and RISESAT together with the results of thermal vacuum tests will be illustrated. Also detailed numerical thermal simulation results will be summarized to discuss the influence of deployable solar panels. Copyright© (2013) by the International Astronautical Federation.

  59. Model-based simulation and verification environment for space plug-and-play avionics

    Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto, Yoshihiro Tomioka, Kazufumi Fukuda, Nobuo Sugimura

    Proceedings of the International Astronautical Congress, IAC 2013/01/01

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    Recently small satellite development activities became popular throughout the world and the number of satellites being developed and launched a year is becoming larger. The Space Robotics Laboratory of Tohoku University has been developing multiples of micro-satellites for years and has gathered experiences in their development, verification, integration, and operation. SRL has recently started development of model-based simulation, verification and integration environment to realize rapid and cost-effective development of reliable micro-satellites. The conceptual design and its functionality have been verified through the real-life 50kg class micro-satellite projects. The developed environment can be utilized in different configurations depending on requirements in each satellite development phase. This environment is designed to be modular and very flexible and can be utilized for other micro-satellites and possibly even much smaller space system projects in the future. The forth micro-satellite of SRL, which is named RISESAT (Rapid International Scientific Experiment Satellite), introduces Space Plug-and- Play Avionics standard for payload instruments' electrical architecture. By applying a virtual system integration technology, remote integration of satellite components spread all over the world via internet becomes possible without getting together at a certain place. In this way the integration of a variety of scientific instruments becomes simple and the effort required can be dramatically reduced. According to this background, SRL started investigation of extending above mentioned model-based simulation environment for SPA compatible instruments. This environment shall enable software-based simulation and early functional verification of the SPA devices together with the satellite's bus system. This will improve the rapid and cost-effective development performance of small satellites which introduces SPA technology. Copyright© (2013) by the International Astronautical Federation.

  60. Down link optical communication experiment using micro satellite body pointing and collaboration with co-located science instrument

    Hiroo Kunimori, Toshihiro Kubooka, Tetsuharu Fuse, Hideki Takenaka, Morio Toyoshima, Toshinori Kuwahara, Kazuya Yoshida, Yoshihiro Tomioka, Kazufumi Fukuda, Junichi Kurihara, Yukihiro Takahashi

    Proceedings of the International Astronautical Congress, IAC 2013/01/01

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    The laser communication terminal called VSOTA and a 5m GSD multi-spectral high-resolution Cassegrain telescope called HPT will be equipped on a 50kg-class micro satellite RISESAT. VSOTA aims to demonstrate satellite-to-ground laser communication by means of accurate attitude control of the satellite body itself. The HPT is designed to be able to send the coordinate information of the light spot from laser on ground to the attitude control system with a frequency of 10 Hz. RISESAT also carries a single retro-reflector which serves to make sure to keep acquisition and pointing for ground station. Link analysis between HPT and ground station as well as laser ranging laser as a pilot signal in initial acquisition scenario is discussed. ©2013 by the International Astronautical Federation. All rights reserved.

  61. Dynamic closed loop attitude control simulation and verification environment for micro-satellites

    Kazufumi Fukuda, Toshinori Kuwahara, Yoshihiro Tomioka, Yuji Sakamoto, Kazuya Yoshida

    Proceedings of the International Astronautical Congress, IAC 2013/01/01

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    Tohoku University has been developing multiple micro-satellites for years. The most recent 50-kg class micro-satellite "RISESAT" is equipped with a high-resolution multi-spectral Cassegrain telescope with 5m GSD, as well as an optical communication terminal named "VSOTA." VSOTA requires high-performance attitude control of less than 0.04 deg angle error to keep communication link with the optical ground station because the transmitting laser direction is fixed on the satellite body. Although main methods of testing attitude control system (ACS) before launch are mathematical simulation or static closed loop tests, it is difficult to reproduce sensor noises and actuator errors in mathematical models perfectly. Furthermore, the more severe the attitude determination and control requirements are, the more important it is that the assembled ACS is tested in motion before the launch. Due to these reasons, Tohoku University has started development of a dynamic closed loop test environment. This environment is based on a low friction 3-axis motion table using spherical air bearing. Each sensor and actuator, as well as the total performance of the ACS of RISESAT will be evaluated using this environment. This test environment is designed to be able to evaluate attitude control accuracy of down to 0.04 deg. The table size is 1.2 × 1.0 × 1.0 m including air bearing stand. In this paper, the details of designed specification and the results of system integration of this dynamic closed loop simulation environment will be described. ©2013 by the International Astronautical Federation. All rights reserved.

  62. A series of de-orbit mechanism for active prevention and reduction of space debris

    Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto, Yoshihiro Tomioka, Kazufumi Fukuda, Nobuo Sugimura

    Proceedings of the International Astronautical Congress, IAC 2013/01/01

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    Recently small satellite development activities became popular throughout the world and the number of satellites being developed and launched a year is becoming larger. Many of these satellites are launched into orbits where they remain orbiting around the Earth for centuries in vain even after their mission life time. It became recently a world's serious concern that these space debris prevent human beings from safe space development and exploration activities in the near future. Therefore there is a great interest on debris prevention and reduction methods. Tohoku University has been very active in satellite development activities for years and has already successfully developed, tested, and launched its first microsatellite SPRITE-SAT (renamed as RISING-1 after the launch) in 2009 and CubeSat RAIKO in 2013, and is completing the second and third microsatellites RISING-2 and RISES AT. Due to the above mentioned background, Tohoku University has also initiated a development activity of sail deployment mechanisms in order to de-orbit the used microsatellite mainly by means of the residual atmospheric drags. The mechanism itself has a cylinder form and utilizes unique deployable booms which can be folded down very compactly. The stored thin film inside the mechanism is pulled out of the case by the deployment force produced by the booms. Three different sizes of models have been developed, and their functionalities are verified. The important characteristic of this mechanism is that the size of the sail can be modified very easily depending on the requirements of the spacecraft. Preparing deferent size of sails, this kind of de-orbit mechanism can become the standard prevention and reduction measures of space debris. This paper describes the development and qualification results of these mechanisms.

  63. Establish the environment to support cost-effective and rapid development of micro-satellites

    Yoshihiro Tomioka, Kazuya Yoshida, Yuji Sakamoto, Toshinori Kuwahara, Kazufumi Fukuda, Nobuo Sugimura, Masato Fukuyama, Yoshihiko Shibuya

    Proceedings of the International Astronautical Congress, IAC 2012/12/01

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    Recently, the development of Micro-satellites weighing 100 kg or less has been paid great attentions. The Space Robotics Laboratory of Tohoku University has three 50kg Micro-satellite projects. The first satellite "SPRITE-SAT" has been successfully launched into Earth orbit, and also been operated. The flight model of the second satellite "RISING-2" has been assembled and its software development is now finalized, being ready for the launch planned in next year. The third satellite "RISESAT" project is during the EM (Engineering Model) development phase at the time of writing. The launch is planned in the second half of 2013. Because of their easy handling characteristics, Micro-satellites are expected to be tools for orbit demonstration of latest engineering technologies and science observations with latest high-performance instruments. To meet these expectations, enhancement of cost-effective and rapid development capability of Micro-satellites becomes essential. Space Robotics Laboratory aims to establish a cost-effective and rapid development environment for microsatellites through the RISESAT project. After the establishment of this environment, it can be applied for future microsatellite missions. We have established basic functional requirements of this environment and named it as MEVIfiS: Model-based Environment for Verification and Integration of Satellite. MEVIjiS will be capable of supporting model-based SILS (Software in the Loop Simulation), HILS (Hardware in the Loop Simulation) with satellite's various hardware components and even operation. The paper will discuss detail of composition and development progress of MEVIUS in conjunction with ongoing RISESAT's project.©2012 by the International Astronautical Federation.

  64. Qualification results of a sail deployment mechanism for active prevention and reduction of space debries

    Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto, Yoshihiro Tomioka, Kazufumi Fukuda, Masato Fukuyama, Yuta Tanabe, Yoshihiko Shibuya

    Proceedings of the International Astronautical Congress, IAC 2012/12/01

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    Recently small satellite development activities became popular throughout the world and the number of satellites being developed and launched a year is becoming larger. Many of these satellites are launched into orbits where they remain orbiting around the Earth for centuries in vain even after their mission life time. It became recently a world's serious concern that these space debris prevent human beings from safe space development and exploration activities in the near future. Therefore there is a great interest on debris prevention and reduction methods. Tohoku University has been very active in satellite development activities for years and has already successfully developed, tested, and launched its first microsatellite SPRITE-SAT (renamed as RISING-1 after the launch) in 2009, and is completing the second and third microsatellite RISING-2 and R1SESAT, and launched a CubeSat RAIKO which is now in the International Space Station and will be deployed into orbit very soon. Due to the above mentioned background, Tohoku University has also initiated a development activity of sail deployment mechanisms in order to de-orbit the used microsatellite mainly by means of the residual atmospheric drags. The mechanism itself has a cylinder form and utilizes unique deployable booms which can be folded down very compactly. The stored thin film inside the mechanism is pulled out of the case by the deployment force produced by the booms. Three different sizes of models have been developed, and their functionalities are verified. The smallest is flown on the RAIKO, the second will fly on the RISING-2, and the third on the RISESAT. The important characteristic of this mechanism is that the size of the sail can be modified very easily depending on the requirements of the spacecraft. Preparing deferent size of sails, this kind of de-orbit mechanism can become the standard prevention and reduction measures of space debris. This paper describes the development and application status of this mechanism and the results of initial qualifications. Copyright © (2012) by the International Astronautical Federation.

  65. Space plug and play avionics for small satellites

    Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto, Yoshihiro Tomioka, Kazufumi Fukuda, Yoshihiko Shibuya

    Proceedings of the International Astronautical Congress, IAC 2012/12/01

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    Professor Shinichi Nakasuka of University of Tokyo is now leading a small satellite development activity within the scope of a Japanese FIRST (Funding Program for World-Leading Innovative R&D on Science and Technology) program. In this program several 50-kg class micro-satellites are going to be developed and launched by the end of Japanese fiscal year of 2013, including one scientific micro-satellite under international cooperation. This program as whole shall contribute to enhance the activities of world's small satellite research societies and industries, and to build the basis of new paradigm for the future, where cost-effective and reliable small satellites are widely utilized for both research and business purposes. Tohoku University has been assigned as the project leader of the above mentioned international scientific micro-satellite, named as R1SESAT (Rapid International Scientific Experiment Satellite), and is developing the bus system as well as organizing scientific payload instruments from abroad. R1SESAT employs a payload main computer based on Space Plug and Play Avionics (SPA) technology for controlling all of these scientific instruments. By applying virtual system integration technology, remote integration of satellite components spread all over the world becomes possible without getting together at a certain place. In this way the integration of a variety of payload instruments becomes simple and the effort required can be dramatically reduced. RISESAT project is now at the end of Engineering Model development phase and has experienced first mechanical and electrical integration activity of the Engineering Models of payload instruments. RISESAT is the first example of applying SPA for real-life international scientific missions. Copyright © (2012) by the International Astronautical Federation.

  66. Development Status of Microsatellite RISESAT International-presentation

    坂本祐二, 吉田和哉

    UN/Japan Nano-Satellite Symposium 2012/10/10

  67. Performance Evaluation for Pointing Control System of the Balloon-boarn Telescope International-presentation

    Toshihiko Nakano, Kasuya Yoshida

    13th International Space Conference of Pacific - basin Societies 2012/05/15

  68. 超小型人工衛星RISESATの姿勢制御系開発/評価環境

    坂本祐二, 吉田和哉

    第20回スペース・エンジニアリング・コンファレンス SEC'11 2012/01/26

  69. RISING2およびRAIKO開発に基づく超小型衛星のためのC&DHサブシステムの開発手法

    坂本祐二, 吉田和哉

    第20回スペース・エンジニアリング・コンファレンス SEC'11 2012/01/26

  70. A Japanese microsatellite bus system for international scientific missions

    Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto, Yukihiro Takahashi, Junichi Kurihara, Hiroshi Yamakawa, Atsushi Takada

    62nd International Astronautical Congress 2011, IAC 2011 2011/12/01

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    Professor Shinichi Nakasuka of University of Tokyo is now leading a small satellite development activity within the scope of a Japanese FIRST (Funding Program for World-Leading Innovative R&D on Science and Technology) program. In this program several 50-kg class micro-satellites are going to be developed and launched by the end of Japanese fiscal year of 2013, including one scientific micro-satellite under international cooperation. This program as whole shall contribute to enhance the activities of world's small satellite research societies and industries, and to build the basis of new paradigm for the future, where cost-effective and reliable small satellites are widely utilized for both research and business purposes. Tohoku University has been assigned as the project leader of the above mentioned international scientific micro-satellite, named as RISESAT (Rapid International Scientific Experiment Satellite), and is developing the bus system as well as organizing scientific payload instruments from all over the world together with Hokkaido University and Kyoto University. This satellite shall demonstrate the performance of its bus system which is supposed to be offered as a common bus system for international scientific missions in the future. The selection of scientific instruments is almost finished. The orbit of me RISESAT is planned to be a sun-synchronous orbit with an altitude of between 500km and 800km. In order to accommodate as many payload instruments as possible, the satellite is equipped with two deployable side solar panels enabling a maximum power consumption of up to about 100 W. Many of the attitude determination and control components are going to be developed by the Space Robotics Laboratory of the Tohoku University achieving an attitude control accuracy of better than 0.1 deg. It is also equipped with an X-band transmitter for mission data downlink. The electrical interface between the payload instruments and the bus system is based on a space plug and play avionics standard. The development of engineering model of the RISESAT will be completed by March 2012. This paper summarizes the system design of the satellite and progress report of the development activities, as well as the brief description of selected scientific instruments. Copyright ©2011 by the International Astronautical Federation. All rights reserved.

  71. A sail deployment mechanism for active prevention and reduction of space debries

    Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto, Yoshihiro Tomioka, Kazufumi Fukuda, Yuta Tanabe, Masato Fukuyama

    62nd International Astronautical Congress 2011, IAC 2011 2011/12/01

    More details Close

    Recently small satellite development activities became popular throughout the world and the number of satellites being developed and launched a year is becoming larger. Many of these satellites are launched into orbits where they remain orbiting around the Earth for centuries in vain even after their mission life time. It became recently a world's serious concern that these space debris prevent human beings from safe space development and exploration activities in the near future. Therefore there is a great interest on debris prevention and reduction methods. Tohoku University has been very active in satellite development activities for years and has already successfully developed, tested, and launched its first microsatellite SPRITE-SAT (renamed as RISING-1 after the launch) in 2009, and is completing the second microsatellite RISING-2. Due to the above mentioned background, Tohoku University has also initiated a development activity of sail deployment mechanisms in order to de-orbit the used microsatellite mainly by means of the residual atmospheric drags. The mechanism itself has a cylinder form and utilizes unique deployable booms which can be folded down very compactly. The stored thin film inside the mechanism is pulled out of the case by the deployment force produced by the booms. The engineering model of this mechanism is now under development, which exemplary has a diameter of 20 cm, a thickness of 5cm, and a mass of about 0.5 kg for deploying a 1.5 m square thin film. This size is meant to be sufficient for de-orbiting of the second microsatellite RISING-2 with a mass of about 41kg within 25 years. It is estimated that the volume of the mechanism can be reduced down to 2/3 for the flight model. The third microsatellite RISESAT with a mass of about 50 kg is planned to be equipped with a 4.5 m square sail. The important characteristic of this mechanism is that the size of the sail can be modified very easily depending on the requirements of the spacecraft. Preparing deferent size of sails, this kind of de-orbit mechanism can become the standard prevention and reduction measures of space debris. This paper describes the basic idea of this sail deployment mechanism, the results of initial functional verification of the test model, and proposes an efficient way of space debris mitigation for future space activities.

  72. One satellite per country - How emerging space-faring nations can benefit from technology transfer through free open-source projects

    Claas Ziemke, Toshinori Kuwahara

    62nd International Astronautical Congress 2011, IAC 2011 2011/12/01

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    Today many developing countries are implementing or planning to implement a national space program. One of the main goals of these emerging space-faring nations often is the establishment of an own national space industry in order to avoid brain-drain and to foster the national economy A problem faced by many of these nations is the inherent lack of heritage in the field of space technology. Because of this lack, these nations are dependent of technology transfer from other space-faring nations. A multitude of different mechanisms for technology transfer exist. Free open-source technology is one of the cheapest, yet most effective solution for technology transfer. This is because the source-codes and designs are free of charge and the underlying technology is open for inspection. This fact also minimizes transaction costs of communication, licensing and negotiations. Thus the available funds can be spent effectively for technology advance. In this paper the mechanism of technology transfer through free open-source projects is described and the mechanism is applied to space projects. Many universities and amateur groups in developed as well as developing countries maintain small-satellite projects. The vast majority of these projects are closed-source and thus are inherently redundant in technology aspects. If only a small percentage of these projects decide to open their sources and designs it seems to be possible to develop a catalogue of free open-source satellite hardware components and interfaces. The establishment of free interface definitions and communication protocols is especially important to foster interoperability and interchangeability. Also many small-satellites have very similar mission designs, leading to the belief that it is possible to define a set of baseline designs for free and open small-satellite platforms. The design principles for such a open small-satellite platform are established and described in this paper. The main design principles are the usage of commercial of the shelf parts and the focus on the "keep it simple, stupid!" principle. The conclusion is, that a "One Satellite per Country" project similar to the "One Laptop per Child" project is feasible and may lead to a huge increase in the speed of technology transfer not only in the area of space technology. The core of this project is formed by a set of existing open-source software projects which will be integrated to the OpenSatDK. The aim of this is to provide the possibility to do system engineering with dedicated open-source tools. Copyright ©2011 by Claas Ziemke. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.

  73. S192025 Pre-Flight Verification for the Bus System Development of Earth Observation Microsatellite RISING-2

    SAKAMOTO Yuji, KUWAHARA Toshinori, YOSHIDA Kazuya, TAKAHASHI Yukihiro

    Mechanical Engineering Congress, Japan 2011/09/11

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    The development of 50-kg class microsatellite RISING-2 was started in July, 2009 by Tohoku Univ. and Hokkaido Univ. At the time of May, 2011, the fabrication and evaluation tests of engineering model (EM) and the fabrication of flight model (FM) were finished. The launch opportunity has been not decided yet. The satellite has a telescope with 10-cm diameter and 1-m focal length, and the resolution of image is 5 meters. It observes multi-spectrum images of cumulonimbus clouds using liquid crystal tunable filter as well as RGB color photos. Also, transient luminous events in upper atmosphere such as sprite are observed using CMOS sensors. This paper shows the final specifications of FM, and the verification tests of bus system.

  74. 小型人工衛星のデブリ化防止のための軌道離脱装置の宇宙実証

    小型衛星による実証シンポジウム 2011/09/07

  75. Next-generation International Scientific Observation Satellite Project International-presentation

    冨岡義弘, 海老沼拓史

    Japan Geoscience Union Meeting 2011 2011/05/20

  76. B1 Trend of European Small Satellite Development Activities

    Kuwahara Toshinori, Sakamoto Yuji, Yoshida Kazuya

    2011/01/27

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    This paper briefly summarizes the trend of small satellite development activities in European community. Recently, the importance of small satellite development activity, especially in terms of education, is getting recognized in Europe and a large amount of organizations and institutions are now taking part of the stream. Though the initiation of the CubeSat projects in Europe was relatively late, there are nowadays not only CubeSat projects but also many middle-sized small satellites under development. In this paper some exemplary small satellite projects in Europe both CubeSats and middle-sized small satellites are described. Based on the experience of author obtained through a 5-years-long research activity at the University of Stuttgart in Germany, exemplary system architecture of modern middle-sized small satellites is described. Along the European small satellite development activities future key technologies are becoming available, which can be also of Japanese interest. For example, space plug and play avionics products marketed in Europe are possible targets to be introduced to Japanese future small satellites. The aspect that most of the European products are ITAR-free makes them very attractive to communities outside Europe including Japan. On the contrary, Japanese small satellites-related products and technologies will be highly welcomed by the European community. In this sense Europe can be one of the strong partners of Japan as well as a possible customer of Japanese small satellite technologies. The author strongly recommends that Japan actively cooperate with European community to achieve rapid technology development and demonstrations.

  77. F3 Evaluation of Efficient Development Methods of 50-kg Microsatellites Based on SPRITE-SAT and RISING-2

    Sakamoto Yuji, Kuwahara Toshinori, Yoshida Kazuya, Takahashi Yukihiro

    スペース・エンジニアリング・コンファレンス講演論文集 : Space Engineering Conference 2011/01/27

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    Tohoku University and Hokkaido University started the development of a new 50-kg microsatellite RISING-2 at July 2009. This satellite inherits the development technique of RISING (SPRITE-SAT) launched on January 2009. The progress is shown in this paper. Using a Cassegrain telescope with 10-cm diameter and 1-m focal length, earth surface is observed with 5-m resolution from 700-km-alt sun synchronous orbit. By 3-axis attitude stabilization using reaction wheels and star sensors, the designated area on earth surface can be observed. In addition to color images, multi-spectrum images of cumulonimbus are observed by using a liquid crystal tunable filter. As a secondary mission, transient luminous events such as sprite are observed, which is same mission as SPRITE-SAT.

  78. 欧州における小型人工衛星開発の動向

    坂本祐二, 吉田和哉

    日本機会学会 スペース・エンジニアリング・コンファレンス 2011/01/27

  79. Evaluation of Efficient Development Methods of 50-kg Microsatellites Based on SPRITE-SAT and RISING-2

    Sakamoto Yuji, Kuwahara Toshinori, Yoshida Kazuya, Takahashi Yukihiro

    JSME Space Engineering Conference 2011/01/27

  80. System Integration of Small Satellites International-presentation

    International 2010/12/21

  81. An integrated development framework for rapid development of platform-independent and reusable satellite on-board software

    Claas Ziemke, Toshinori Kuwahara, Ivan Kossev

    61st International Astronautical Congress 2010, IAC 2010 2010/12/01

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    Even in the field of small satellites, the on-board data handling subsystem has become complex and powerful. With the introduction of powerful CPUs and the availability of considerable quantities of memory on-board a small satellite it has become possible to utilize the flexibility and power of contemporary platform-independent real-time operating systems. Especially the non commercial sector like university institutes and community projects such as AMSAT or SSETI are characterized by the inherent lack of financial as well as manpower resources. The opportunity to utilize such real-time operating systems will contribute significantly to achieve a successful mission. Nevertheless the on-board software (OBSW) of a satellite is much more than just an operating system. It has to fulfil a multitude of functional requirements such as: Telecommand interpretation and execution, execution of control loops, generation of telemetry data and frames, failure detection isolation and recovery, the communication with peripherals and so on. Most of the aforementioned tasks are of generic nature and have to be conducted on any satellite with only minor modifications. A general set of functional requirements as well as a protocol for communication is defined in the ESA ECSS-E-70-41A standard "Telemetry and telecommand packet utilization". This standard not only defines the communication protocol of the satellite-ground link but also defines a set of so called services which have to be available on-board of every compliant satellite and which are of a generic nature. In this paper a platform-independent and reusable framework is described which is implementing not only the ECSS-E-70-41A standard but also functionalities for inter-process communication, scheduling and a multitude of tasks commonly performed on-board of a satellite. By making use of the capabilities of the high-level programming language C/C++, the powerful open source library BOOST, the real-time operating system RTEMS and finally by providing generic functionalities compliant to the ECSS-E-70-41A standard the proposed framework can provide a great boost in productivity. Together with open source tools such like the GNU tool-chain, Eclipse SDK, the simulation framework OpenSimKit, the emulator QEMU, the proposed OBSW framework forms an integrated development framework. It is possible to design, code and build the on-board software together with the operating system and then run it on a simulated satellite for performance analysis and debugging purposes. This makes it possible to rapidly develop and deploy a full-fledged satellite OBSW with minimal cost and in a limited time frame. Copyright ©2010 by Claas Ziemke. Published by the American Institute of Aeronautics and Astronautics, Inc.

  82. FPGA-based on-board computers for reconfigurable computing on space systems

    Toshinori Kuwahara, M. Dittmar, C. Ziemke, H. P. Röser

    60th International Astronautical Congress 2009, IAC 2009 2009/12/01

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    The goal of this paper is to present the development status of the Field Programmable Gate Array (FPGA) based on-board computer for reconfigurable computing on space systems, which is currently under development at the Institute of Space Systems of the Universitaet Stuttgart. Together with the capability of reconfigurable computing, the extremely high throughputs and flexibilities of FPGAs due to their internal parallel processing mechanisms are the ideal solutions for future space applications. This computer is designed for Low Earth Orbit applications and especially optimized for small satellites. It is internally organized in a combination of multiple SRAM-FPGAs and Flash-FPGAs. In order to mitigate radiation effects, Single Event Upsets (SEUs) in the multi-chip redundant SRAM-FPGAs are monitored, detected, isolated and recovered from the monitoring Flash-FPGA, whose configuration memory is inherently immune against SEUs. The radiation effects on both these reconfigurable FPGAs and their mitigation methods are summarized. The developed breadboard model for the concept verification are illustrated. The first flight model of this computer designed for a small satellite will demonstrate reconfigurable computing for attitude control, image processing, and Ka-band high-speed communications.

  83. Improved land surface temperature retrieval method for the small satellite flying laptop

    Ursula Kirchgäßner, Toshinori Kuwahara, Maria Von Schönermark

    International Astronautical Federation - 59th International Astronautical Congress 2008, IAC 2008 2008/12/01

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    The enhanced algorithms developed in this study for land surface temperature retrieval combine the split-window method with the multi-angle method, employing a large number of view angles between nadir and 60 degrees zenith angle. The new algorithms are intended for analysing data from the Thermal Infrared Camera System of the small satellite Flying Laptop, a technology demonstration and earth observation satellite currently being developed at the Institute of Space Systems, Universitaet Stuttgart. The Thermal Infrared Camera System will observe at 8.0 to 9.2 μm and at 10.4 to 12.6 μm. The attitude control system of the satellite permits arbitrary pointing angles. This combination of bi-spectral camera system and multi-angle observation capability offers means of improving land surface temperature retrieval. In order to investigate the utility of the prospective observations, data has been modelled numerically for a wide range of atmospheric properties, using the radiation transport model MODTRAN. The resulting data was analysed statistically and a number of algorithms for temperature retrieval have been derived, depending on available angles. The multi-angle method improves accuracy of the retrieved temperature compared to the employment of the split-window method only, especially for very humid atmospheres. A standard deviation below one Kelvin can be achieved for land surface temperature.

  84. QSAT mission analysis and operation plan design

    Alexander Uryu, Jozef C. Van, Der Ha, Hans Peter Röser, Toshinori Kuwahara

    International Astronautical Federation - 59th International Astronautical Congress 2008, IAC 2008 2008/12/01

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    This paper deals with the operations concept for the small satellite QSAT. It aims to guarantee the survivol of the satellite ond to accomplish the scientific observations during the planned lifetime of one year. QSAT is developed at the Space Systems Dynamics Laboratory of Kyushu University in Fukuoka, Japan. Its main objectives are the porallel measurements of the geomagnetic field and the electric potential of the satellite, which may lead to new insights on the mechanisms of spacecraft charging. The uniqueness of this mission is the regard of Field-Aligned-Currents as the reason for spacecraft charging. Simulation results are presented, which are the basis for the operations plan along with common-sense considerations. Specific strategies are presented which allow to accomplish the mission requirements within the given constraints. The paper gives the break-down of QSAT lifetime into specific phases and cycles, and the allocation of the defined modes. Only about 32 minutes of ground-station visibility are available per day, thus only about 2 Mbytes of data can be downlinked at the transmission rate of 9.6 kbits per second. As part of mission operations, "predict-prevent" style considerations of contingency procedures are discussed. This facilitates o rapid answer to occurring anomalies.

  85. Operational design and on-board payload data processing of the small satellite "Flying Laptop" with an FPGA-based onboard computing system

    Toshinori Kuwahara, F. Böhringer, A. Falke, J. Eickhoff, F. Huber, H. P. Röser

    International Astronautical Federation - 59th International Astronautical Congress 2008, IAC 2008 2008/12/01

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    The small satellite Flying Laptop is the first satellite developed by the Institute of Space Systems at the Universität Stuttgart within the "Stuttgart Small Satellite Program." In this paper the operational design and the on-board payload data processing of the satellite are described. The Flying Laptop is a test bed for an on-board computer with a reconfigurable, redundant and self-controlling high computational ability which is based on a field programmable gate array (FPGA). In addition to this, it has more than ten mission goals including technology demonstration and scientific Earth observation. The designed operational concept enables the achievement of these mission goals, and the developed payload data processing methods expand the scientific usage and enable new possibilities for real-time applications. The operational concept which reflects the aspects of attitude control mode, ground communication, power management, and on-board data handling has been established. The hierarchical architecture of the subsystem and components mode are developed in a state-machine diagram and tested by means of Math Works Simulink-/Stateflow Toolbox. Furthermore, the concept of the on-board payload data processing and its implementation is described and possible applications are discussed.

  86. System design of the small satellite flying laptop, as the technology demonstrator of the FPGA-based on-board computing system

    Toshinori Kuwahara, F. Huber, A. Falke, M. Lengowski, S. Walz, G. Grillmayer, H. P. Röser

    International Astronautical Federation - 58th International Astronautical Congress 2007 2007/12/01

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    The small satellite Flying Laptop is the first satellite which is developed by the Institute of Space Systems at the Universität Stuttgart within the "Stuttgart Small Satellite Program". In this paper the detailed system design of this satellite is described which enables its mission objectives: new technology demonstration and scientific earth observation. The Flying Laptop is the test bed for an on-board computer with a reconfigurable, redundant and self-controlling high computational ability which is based on a field programmable gate array. The attitude control system with pointing knowledge of better than 7.4 arcseconds makes it easy to achieve maximum ground sample distance of 25m for Multi-spectral Imaging Camera System and 100m for Thermal Imaging Camera System of payload, and the high speed communication channel in Ka-band up to 500 Mbit/s allows enough data transfer budget, which is exceptional for small satellites. All input/output signals of the on-board computer, in total more than 200 lines, include interfaces of RS422, LVDM, M-LVDS, TTL and I2C. The harness system is developed using mock-up model of the whole satellite in its original size. The introduced operational scenario and defined attitude control modes ensures the validity of the system design. Copyright IAF/IAA. All rights reserved.

  87. Kyushu university micro-satellite qtex project

    T. Kuwahara, T. Yasaka, T. Hanada, H. Hirayama, Y. Sakamoto, T. Itahashi

    International Astronautical Federation - 55th International Astronautical Congress 2004 2004/12/01

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    The project of micro-satellite QTEX (KYUshu university Tethered satellites Experiments) which is progressing at Kyushu University in Japan is reported in this paper. QTEX is assumed to be launched as a piggy-back satellite using Japanese domestic rocket H-IIA in 2006. The dimension of the satellite is approximately 50×50×50 cm3. The weight of the satellite is less than 50 kg. QTEX, consisting of tether deployment system and bus system, performs deployment of 2 km length of tether connected with a mother and a daughter satellite at its both ends. We named the daughter satellite of QTEX as QTEX-PR (QTEX - Public Relations) which includes bus system only and bread board model of QTEX-PR are now being developed under student initiative. It enabled to develop tether deployment system and bus system separately, and furthermore, because QTEX-PR can function as one satellite, we can launch QTEX-PR alone if we get an opportunity to launch it before the completion of whole QTEX. Structural analysis, thermal analysis and simulation of attitude determination and control having done at the present time prove that the designs of QTEX-PR are valid enough.

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Industrial Property Rights 9

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    Holder: 株式会社ALE

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    桒原聡文, 小島 要, 株式会社アドニクス

    特許第6103496号

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    齋藤勇士, 桒原聡文, 小林稜平

    Property Type: Patent

  9. ハイブリッドロケットエンジンの燃焼状態解析方法、燃焼状態解析システム、および燃焼状態解析プログラム

    齋藤勇士, 桒原聡文, 小林稜平

    Property Type: Patent

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Research Projects 6

  1. High time/space-resolved solid fuel regression and combustion mechanism of a hybrid propulsion system

    Offer Organization: Japan Society for the Promotion of Science

    System: Grants-in-Aid for Scientific Research

    Category: Grant-in-Aid for Scientific Research (B)

    Institution: Tohoku University

    2023/04/01 - 2027/03/31

  2. High time/space-resolved solid fuel regression and combustion mechanism of a hybrid propulsion system

    Offer Organization: Japan Society for the Promotion of Science

    System: Grants-in-Aid for Scientific Research

    Category: Grant-in-Aid for Scientific Research (B)

    Institution: Tohoku University

    2023/04/01 - 2027/03/31

  3. High-Precision Real-Gas Aerodynamic Performance Prediction Technique Using High-Speed Vacuum Ultraviolet Absorption Spectral Fitting Method

    Offer Organization: Japan Society for the Promotion of Science

    System: Grants-in-Aid for Scientific Research

    Category: Grant-in-Aid for Scientific Research (B)

    Institution: Tohoku University

    2023/04/01 - 2026/03/31

  4. Research on High-Precision Real-Gas Aerodynamics Prediction Technique Using High-Speed Vacuum Ultraviolet Absorption Spectra Fitting Method

    Offer Organization: Japan Society for the Promotion of Science

    System: Grants-in-Aid for Scientific Research

    Category: Grant-in-Aid for Scientific Research (B)

    Institution: Tohoku University

    2023/04/01 - 2026/03/31

  5. Study on relationship between strong rainfall and local circulation in the Fukui plain

    Nakajo Tomoyuki, Aoyama Takashi, Ujihashi Yasuyuki, Kato Yoshinobu, Hashiguchi Hiroyuki, YAMAMOTO Masayuki, Takahashi Yukihiro, Sakamoto Yuji, Kuwahara Toshinori

    Offer Organization: Japan Society for the Promotion of Science

    System: Grants-in-Aid for Scientific Research

    Category: Grant-in-Aid for Scientific Research (C)

    Institution: Fukui University of Technology

    2013/04/01 - 2016/03/31

    More details Close

    We statistically compared wind data at lower troposphere based on wind profiler radars with precipitation distribution data based on C-band weather radar in order to investigate the effects of interaction between terrain and lower wind on precipitation patterns in the Fukui plain. The results show detailed precipitation patterns in the Fukui plain are classified by wind at altitude lower than 1 km. In particular, localized strong rainfall often occurs in the northern area of Fukui plain in the condition that wind at altitude lower than 1 km is westerly. These results indicate the measurement of lower wind at altitude lower than 1 km is important on local weather forecasting.

  6. Low-cost Rapid Development and Verification Environment for Micro-satellites

    KUWAHARA Toshinori

    Offer Organization: Japan Society for the Promotion of Science

    System: Grants-in-Aid for Scientific Research

    Category: Grant-in-Aid for Young Scientists (B)

    Institution: Tohoku University

    2012/04/01 - 2015/03/31

    More details Close

    Recently, not only research and development of micro-satellite technologies, but also their actual utilization is becoming very active in the world. This research has established an integrated and comprehensive development and verification environment of micro-satellites in order to improve their reliability in the orbit, as well as to enable rapid and low-cost development. This environment is capable of full software simulation, dynamic closed-loop simulation, and real operation based on the same platform. This environment can be also configured and extended very flexibly according to the project's demands. The functionality of this environment has been evaluated as it was applied to Tohoku University's real-life micro-satellite project.

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Social Activities 4

  1. 超小型衛星ミッションアシュアランス・ハンドブック / Mission Assurance Handbook for the University-built Lean Satellite 策定

    2023/03 -

  2. 超小型衛星Mission Assurance(機能保証) 情報共有Webサイト 設置

    2022 -

  3. 国連宇宙部(UNOOSA: UNITED NATIONS Office for Outer Space Affairs)KiboCUBE Academy(宇宙工学講座) 講師

    2020/11/01 -

  4. Chairperson of UNISEC (University Space Engineering Consortium)

    2020/10/01 -

Media Coverage 57

  1. 宇宙産業東北の中小奮闘 スタートアップ誕生で参入機会拡大

    株式会社河北新報社 河北新報 4面

    2024/08/27

    Type: Newspaper, magazine

  2. 東北大発・エレベーションスペース 新たに14億円資金調達

    株式会社河北新報社 河北新報 6面

    2024/07/12

    Type: Newspaper, magazine

  3. カプセル切り離し試験成功 仙台・エレベーションスペース 衛星取得データ基に詳細設計へ

    株式会社河北新報社 河北新報 6面

    2024/06/21

    Type: Newspaper, magazine

  4. 東北大発ベンチャー仙台の「ELS」KDDIの宇宙事業参画

    株式会社河北新報社 河北新報 4面

    2024/06/05

    Type: Newspaper, magazine

  5. 仙台・エレベーションスペース 帰還カプセル回収確実に 着水衝撃試験始まる

    株式会社河北新報社 河北新報 4面

    2024/04/25

    Type: Newspaper, magazine

  6. 仙台・エレベーションスペース 最新の宇宙産業紹介 東京でセミナー・8日開講

    株式会社河北新報社 河北新報 4面

    2024/03/05

    Type: Newspaper, magazine

  7. 宇宙の魅力に触れよう 仙台・20日東北大生がイベント

    株式会社河北新報社 河北新報 15面

    2024/03/04

    Type: Newspaper, magazine

  8. カプセル帰還へ試験成功 仙台・エレベーションスペース 衛星初号機の製造前進

    株式会社河北新報社 河北新報 4面

    2024/01/10

    Type: Newspaper, magazine

  9. 東北大学発宇宙スタートアップElevationSpaceがJapan Venture Awardsで地域貢献特別賞を受賞

    東北大学 プレスリリース

    2023/12/21

    Type: Internet

  10. 東北の民間企業初の人工衛星に 東北の名産品を搭載 25年打ち上げ

    株式会社科学新聞社 The Science News 科学新聞 2面

    2023/12/01

    Type: Newspaper, magazine

  11. 桒原聡文准教授がベトナム科学技術院主催 日越外交関係樹立50周年記念ワークショップに出席

    東北大学 プレスリリース

    2023/11/28

    Type: Internet

  12. 人工衛星開発ELS 異業種人事交流 デンソー皮切り

    株式会社河北新報社 河北新報 4面

    2023/11/22

    Type: Newspaper, magazine

  13. 東北ゆかりの品宇宙へ ElevationSpace打ち上げ事業開始

    株式会社日刊工業新聞社 日刊工業新聞 22面

    2023/11/17

    Type: Newspaper, magazine

  14. 東北産品宇宙の旅 人工衛星搭載25年打ち上げへ

    株式会社河北新報社 河北新報 3面

    2023/11/16

    Type: Newspaper, magazine

  15. 交流から共創へ 宇宙プレーヤー躍動!

    株式会社日本経済新聞社 日本経済新聞 22-23面

    2023/11/14

    Type: Newspaper, magazine

  16. デンソーから出向受け入れ 東北大発宇宙新興

    株式会社日刊工業新聞社 日刊工業新聞 4面

    2023/11/08

    Type: Newspaper, magazine

  17. 東北大発新興の衛星愛称

    株式会社日本経済新聞社 日本経済新聞 39面

    2023/10/21

    Type: Newspaper, magazine

  18. 小型衛星 愛称「あおば」に エレベーションスペース

    株式会社河北新報社 河北新報 4面

    2023/10/20

    Type: Newspaper, magazine

  19. 東北大学発宇宙スタートアップ「ElevationSpace」が開発中の第1号衛星の愛称が決まりました

    2023/10/19

    Type: Internet

  20. 次期ISS事業に参画 エレベーションスペース パートナー企業に

    株式会社河北新報社 河北新報 4面

    2023/09/22

    Type: Newspaper, magazine

  21. 次期ISS事業に参加 エレベーションスペース パートナー企業に

    河北新報 4面

    2023/09/22

    Type: Newspaper, magazine

  22. 宇宙でミドリムシ培養 エレベーションスペースの衛星に装置搭載

    株式会社河北新報社 河北新報 4面

    2023/08/31

    Type: Newspaper, magazine

  23. エレベーションスペース 推進装置 燃焼試験成功 地球帰還人工衛星 実用化へ大きく前進

    株式会社河北新報社 河北新報 4面

    2023/08/26

    Type: Newspaper, magazine

  24. 世界初の宇宙実証へ向け、小型人工衛星を地球に帰還させるための高推力&経済性&安全性を兼ね備える"ハイブリッドスラスタ"、軌道離脱に必要な長時間燃焼に成功

    2023/08/25

    Type: Internet

  25. ElevationSpaceとJAXA、「地球低軌道拠点からの高頻度再突入・回収事業」に関する共創活動を開始

    ElevationSpace Inc.

    2023/04/27

    Type: Internet

  26. 本学発の宇宙ベンチャー 株式会社ElevationSpaceが「すごいベンチャー100 2022年最新版」に選出

    東北大学 プレスリリース

    2022/09/21

    Type: Internet

  27. 北大・東北大共同開発のフィリピン共和国第2号衛星「DIWATA-2」が台風11号の目の撮影に成功 - 今後の台風・積乱雲など極端気象の高精度・高頻度観測に期待 -

    2022/09/14

    Type: Internet

  28. 東北大・北大共同開発の地球観測結果が防災・減災×サステナブル大賞2023にて「グローバル賞」及び「優秀賞」をW受賞

    2022/09/14

    Type: Internet

  29. ミャンマー連邦共和国と超小型衛星開発を開始 ~ミャンマーの農林水産業や大規模自然災害の軽減に貢献~

    2022/07/24

    Type: Internet

  30. 東北大 世界をリードする宇宙研究 月面探査ロボット&帰還型人工衛星開発 チャージ!第2部

    東日本放送

    2022/04/20

    Type: TV or radio program

  31. 産学連携のチームによる陸・海観測超小型衛星プロジェクト

    2020/07/13

    Type: Internet

  32. 工学研究科 桒原准教授、阿部助教が「第34回 独創性を拓く先端技術大賞」にて、各賞を受賞しました

    2020/06/08

    Type: Internet

  33. 航空宇宙工学専攻の吉田教授,坂本特任准教授,桒原准教授,藤田特任助教が、北海道大学と共同で第4回 宇宙開発利用大賞「宇宙航空研究開発機構理事長賞」を受賞しました

    2020/03/30

    Type: Internet

  34. ALEとJAXA、宇宙デブリ拡散防止装置の事業化に向けたJ-SPARC事業共同実証を開始

    2020/03/25

    Type: Internet

  35. 人工流れ星実証衛星「ALE-1」に搭載された膜展開式軌道離脱装置「DOM®」の軌道上での展開実証およびその動画撮影に成功

    2020/02/18

    Type: Internet

  36. 地球低軌道上にて将来の月探査のための新たな推進・航法技術を実証 JAXA J-CUBE プログラムにHOKUSHIN-1 衛星が採択

    2020/01/06

    Type: Internet

  37. 世界を先導する研究フロンティア開拓のためのプロジェクト 「新領域創成のための挑戦研究デュオ ~ Frontier Research in Duo(FRiD) ~」の採択課題決定

    2019/12/26

    Type: Internet

  38. 海洋観測カメラによる有色溶存有機物の観測に成功 ~超小型人工衛星を利用した北極域観測技術の構築に期待~

    2019/10/02

    Type: Internet

  39. 国際理学観測衛星ライズサット(RISESAT)の 打ち上げ成功・初期運用開始

    2019/02/13

    Type: Internet

  40. フィリピン共和国 第2号衛星「DIWATA-2」による初画像撮影に成功

    2018/12/19

    Type: Internet

  41. ベトナムとの共同開発衛星マイクロドラゴン(MicroDragon)の打ち上げ・電波受信に成功

    2018/12/19

    Type: Internet

  42. 創業から7年、ついに株式会社ALEの人工衛星初号機が完成 〜 2019年1月17日、いよいよ宇宙へ 〜

    2018/12/13

    Type: Internet

  43. 膜展開式軌道離脱装置「DOM®」を搭載した超小型人工衛星2機がイプシロンロケット4号機によって打ち上げられます

    2018/12/13

    Type: Internet

  44. 膜展開式軌道離脱装置が第3回宇宙開発利用大賞「宇宙航空研究開発機構理事長賞」を受賞

    2018/03/20

    Type: Internet

  45. フィリピン科学技術大臣が本学を訪問

    2017/03/30

    Type: Internet

  46. 国際宇宙ステーション・「きぼう」からの超小型衛星利用に関するJAXA、東北大学、北海道大学との包括的な連携協力について

    2017/03/10

    Type: Internet

  47. 膜展開式軌道離脱装置実証衛星「FREEDOM」の実験結果について

    2017/03/01

    Type: Internet

  48. フィリピン共和国 第 1 号超小型衛星「DIWATA-1」によるクラス最高の高解像度撮影に成功

    2016/08/26

    Type: Internet

  49. フィリピン共和国 第1号衛星「DIWATA-1」による初画像撮影に成功

    2016/06/02

    Type: Internet

  50. フィリピン共和国 国産開発第1号となる「DIWATA-1」の国際宇宙ステーション・「きぼう」からの放出成功(JAXA初となる50㎏級超小型衛星の放出成功)

    2016/04/28

    Type: Internet

  51. フィリピン共和国との超小型衛星の開発に関する共同プロジェクトについて

    2015/03/10

    Type: Internet

  52. 雷神2衛星が高解像度スペクトル撮影に成功

    2014/12/18

    Type: Internet

  53. UNIFORM-1 衛星で御嶽山噴火の観測に成功 ~超小型衛星(50kg)による災害即応観測~

    2014/10/06

    Type: Internet

  54. 宇宙ゴミ問題に解決の糸口を 膜展開式軌道離脱装置実証衛星「FREEDOM」が「きぼう」放出超小型衛星として採択決定

    2014/09/26

    Type: Internet

  55. 超小型衛星「雷神2」がクラス最高の高解像度地表撮影に成功

    2014/07/04

    Type: Internet

  56. 「雷神2」本格的な観測に向けて順調に調整中

    2014/06/12

    Type: Internet

  57. 超小型衛星と地上間の光通信実験に関する共同研究の開始について

    2012/03/13

    Type: Internet

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Academic Activities 4

  1. 日本航空宇宙学会 宇宙ビジネス共創委員会

    2020/12/10 - Present

    Activity type: Academic society, research group, etc.

  2. 日本航空宇宙学会 北部支部幹事

    2016/04 - Present

    Activity type: Academic society, research group, etc.

  3. 日本航空宇宙学会 論文編集委員会

    2023/04 -

    Activity type: Academic society, research group, etc.

  4. International Academy of Astronautics, Committee on Small Satellites

    2017/04 -

    Activity type: Academic society, research group, etc.

Other 6

  1. 東北大学学生団体FROM THE EARTH(F.T.E.) 顧問

  2. 株式会社中島田鉄工所 技術顧問

  3. 東北大学学生団体FROM THE EARTH(F.T.E.) 副顧問

  4. 東北大学研究成果活用型ベンチャー企業 株式会社ElevationSpace創業 共同創業者兼取締役CTO(後に共同創業者兼取締役)

  5. Chairperson of UNISEC: University Space Engineering Consortium

  6. 株式会社ALE CTO(後に技術顧問)

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