Updated on 2026/08/14

写真a

 
WATANABE KEI
 
Organization
Institute of Integrated Research Quantum Navigation Research Center Specially Appointed Assistant Professor
Title
Specially Appointed Assistant Professor
External link

Papers

  • On-orbit demonstration of near real-time communication via Globalstar for time-domain astronomy

    Katsuki Tashiro, Shogo Nerome, Minori Fukuda, Hibiki Seki, Yusaku Ozeki, Hiroyuki Kobayashi, Yuki Amaki, Daiki Kobayashi, Kiyona Miyamoto, Kei Watanabe, Toshihiro Chujo, Hiroki Nakanishi, Satoru Ozawa, Saburo Matunaga, Yoichi Yatsu

    Acta Astronautica   240   208 - 218   2026.3

     More details

    Publishing type:Research paper (scientific journal)   Publisher:Elsevier BV  

    DOI: 10.1016/j.actaastro.2025.12.003

    researchmap

  • On-orbit evaluation of variable-shape satellite attitude dynamics under atmospheric drag torque and gravity gradient torque

    Kiyona Miyamoto, Toshihiro Chujo, Kei Watanabe, Saburo Matunaga

    Acta Astronautica   238   873 - 888   2026.1

     More details

    Publishing type:Research paper (scientific journal)   Publisher:Elsevier BV  

    DOI: 10.1016/j.actaastro.2025.09.003

    researchmap

  • Integrated attitude—orbit control of solar sail with single-axis gimbal mechanism

    Toshihiro Chujo, Kei Watanabe, Yuki Takao

    Astrodynamics   2024.5

     More details

    Publishing type:Research paper (scientific journal)   Publisher:Springer Science and Business Media LLC  

    Abstract

    A new attitude control method for solar sails is proposed using a single-axis gimbal mechanism and three-axis reaction wheels. The gimbal angle is varied to change the geometrical relationship between the force due to solar radiation pressure (SRP) and the center of mass of the spacecraft, such that the disturbance torque is minimized during attitude maintenance for orbit control. Attitude maneuver and maintenance are performed by the reaction wheels based on the quaternion feedback control method. Even if angular momentum accumulates on the reaction wheels due to modelling error, it can also be unloaded by using the gimbal to produce suitable torque due to SRP. In this study, we analyzed the attitude motion under the reaction wheel control by linearizing the equations of motion around the equilibrium point. Further, we newly derived the propellent-free unloading method based on the analytical formulation. Finally, we constructed the integrated attitude{orbit control method, and its validity was verified in integrated attitude{orbit control simulations.

    DOI: 10.1007/s42064-023-0192-2

    researchmap

    Other Link: https://link.springer.com/article/10.1007/s42064-023-0192-2/fulltext.html

  • Flight Model Development and Ground Tests of Variable-Shape Attitude Control Demonstration MicroSatellite HIBARI Reviewed

    Kei WATANABE, Hiroyuki KOBAYASHI, Yuki AMAKI, Naoki KAWAGUCHI, Soichi SATO, Kenichiro TAKAHASHI, Yuta SASAGAWA, Fumitaka SAGAWA, Shogo NEROME, Kiyona MIYAMOTO, Yoichi YATSU, Toshihiro CHUJO, Saburo MATUNAGA, Development Team HIBARI

    Journal of Evolving Space Activities   1   103   2024.2

     More details

    Publishing type:Research paper (scientific journal)  

    DOI: 10.57350/jesa.103

    researchmap

  • Attitude control and on-orbit performance evaluation of spacecraft with variable shape function

    Kei Watanabe, Hiroyuki Kobayashi, Yuki Amaki, Toshihiro Chujo, Saburo Matunaga

    Advances in Space Research   72 ( 6 )   2313 - 2323   2023.6

     More details

    Publishing type:Research paper (scientific journal)   Publisher:Elsevier BV  

    DOI: 10.1016/j.asr.2023.06.002

    researchmap

  • Attitude dynamics of satellites with variable shape mechanisms using atmospheric drag torque and gravity gradient torque

    Kiyona Miyamoto, Toshihiro Chujo, Kei Watanabe, Saburo Matunaga

    Acta Astronautica   202   625 - 636   2023.1

     More details

    Publishing type:Research paper (scientific journal)   Publisher:Elsevier BV  

    DOI: 10.1016/j.actaastro.2022.11.014

    Scopus

    researchmap

▼display all

MISC

  • On-orbit Operation Results and Future Prospects of the Variable Shape Attitude Control Demonstration Satellite HIBARI

    渡邉奎, 小林寛之, 天木祐希, 高橋健一郎, 小林大輝, 西尾陸, 尾関優作, 田代克樹, 斉藤遼, 川口雄生, 宮本清菜, 中条俊大, 谷津陽一, 松永三郎

    宇宙科学技術連合講演会講演集(CD-ROM)   67th   2023

  • Development status of Land/Sea spectral observation technology utilizing ultra-low cost and high precision attitude control satellite bus system

    谷津陽一, 小林寛之, 小澤俊貴, 小林大輝, 大坪恵人, 安田萌恵, 徳安彰大, 三木晴太, 宮本清菜, 福田美実, 大平明日香, 能登亮太郎, 早津俊祐, 渡邉奎, 中条俊大, 若生一広, 青柳賢英, 武山芸英, 江野口章人, 白籏麻衣, 小林宏章, 村田悠, 中野徹, 卯尾匡史, 楠絵莉子, 飯塚千晴

    宇宙科学技術連合講演会講演集(CD-ROM)   67th   2023

  • 衛星からの画像解析と姿勢推定—Image Recognition Utilizing Machine Learning in Space and Its Application to Attitude Determination for Space Crafts—機械学習特集(2)

    谷津 陽一, 渡邉 奎

    天文月報 = The astronomical herald   115 ( 8 )   507 - 516   2022.8

     More details

  • Flight Model Development and Operation Plan of Micro-Satellite HIBARI for Variable Shape Attitude Control Demonstration

    WATANABE Kei, KOBAYASHI Hiroyuki, KAWAGUCHI Naoki, SATO Soich, NEROME Shogo, AMAKI Yuki, SAGAWA Fumitaka, SASAGAWA Yuta, TAKAHASHI Kenichiro, MIYAMOTO Kiyona, CHUJO Toshihiro, YATSU Yoichi, MATUNAGA Saburo

    The Proceedings of the Space Engineering Conference   2021.30   A11   2022

     More details

    Language:Japanese   Publisher:The Japan Society of Mechanical Engineers  

    We have developed a 50kg class microsatellite "HIBARI". The mission of this satellite is to demonstrate a novel attitude control method for microsatellites which is called “Variable Shape Attitude Control (VSAC).” VSAC is a method using anti-torque by driving variable shape structures. HIBARI has four drivable solar array paddles, and demonstrates rapid attitude control using the reaction force that moves them. HIBARI was adopted as the demonstration theme of the Japan Aerospace Exploration Agency (JAXA) Innovative Satellite Technology Demonstration-2, and will be launched by Epsilon Rocket. This paper describes the HIBARI project outline, system design, Flight Model development and on-orbit demonstration plan.

    DOI: 10.1299/jsmesec.2021.30.a11

    CiNii Research

    researchmap

  • Development Status of Microsatellite HIBARI for Demonstration of Variable Shape Attitude Control

    2020.7

     More details

    Language:English  

    CiNii Research

    researchmap

  • Attitude control of satellites with variable shape function utilizing atmospheric drag torque and magnetic torque

    Kiyona Miyamoto, Toshihiro Chujo, Kei Watanabe, Saburo Matunaga

    Proceedings of the International Astronautical Congress, IAC   2020-October   2020

     More details

  • Mission and System Design of Microsatellite HIBARI for Demonstration of Variable Shape Attitude Control

    2019.7

     More details

    Language:English  

    CiNii Research

    researchmap

  • In-orbit performance evaluation of the Star Tracker for small satellite

    間宮英生, 小澤俊貴, 谷津陽一, 河合誠之, 菊谷侑平, 岩崎陽平, 渡邉奎, 松永三郎, 下川辺隆史

    宇宙科学技術連合講演会講演集(CD-ROM)   63rd   2019

  • Preliminary Investigation of Drive Mechanism for Pointing Stability with Variable Shape Attitude Control

    WATANABE Kei, SHINTANI Yusuke, MATUNAGA Saburo

    The Proceedings of Mechanical Engineering Congress, Japan   2018   J1920205   2018

     More details

    Language:Japanese   Publisher:The Japan Society of Mechanical Engineers  

    Recently, Matunaga proposed Variable Shape Attitude Control (VSAC) which utilizes counter torque generated by rotationally driving solar cell paddles. Past studies by the authors shows the possibility of rapid attitude control with VSAC and stable attitude control in cooperation with reaction wheels. This paper considers the compatibility between attitude change rapidity and high oriented attitude stability with only VSAC, and it shows that it is difficult to achieve it with the conventional rotationally degree of freedom(DOF) of motion for VSAC drive mechanism, and that an additional rotationally driving DOF is useful for attitude stabilization. Then, by combining these two rotationally driving DOFs, we propose an attitude control method that enables directional stable observation after the rapid attitude change.

    DOI: 10.1299/jsmemecj.2018.j1920205

    CiNii Research

    researchmap

▼display all