研究者業績

佐伯 孝尚

サイキ タカナオ  (Takanao Saiki)

基本情報

所属
国立研究開発法人宇宙航空研究開発機構 宇宙科学研究所 教授
学位
博士(工学)(2005年3月 東京大学)

J-GLOBAL ID
200901090793977023
researchmap会員ID
5000092383

学歴

 3

受賞

 23

論文

 229
  • Bradley De Gregorio, George D. Cody, Rhonda M. Stroud, A. L. David Kilcoyne, Scott Sandford, Corentin Le Guillou, Larry R. Nittler, Jens Barosch, Hikaru Yabuta, Zita Martins, Yoko Kebukawa, Taiga Okumura, Minako Hashiguchi, Shohei Yamashita, Yasuo Takeichi, Yoshio Takahashi, Daisuke Wakabayashi, Cécile Engrand, Laure Bejach, Lydie Bonal, Eric Quirico, Laurent Remusat, Jean Duprat, Maximilien Verdier-Paoletti, Smail Mostefaoui, Mutsumi Komatsu, Jérémie Mathurin, Alexandre Dazzi, Ariane Deniset-Besseau, Emmanuel Dartois, Yusuke Tamenori, Hiroki Suga, Gilles Montagnac, Kanami Kamide, Miho Shigenaka, Megumi Matsumoto, Yuma Enokido, Makoto Yoshikawa, Takanao Saiki, Satoshi Tanaka, Fuyuto Terui, Satoru Nakazawa, Tomohiro Usui, Masanao Abe, Tatsuaki Okada, Toru Yada, Masahiro Nishimura, Aiko Nakato, Akiko Miyazaki, Kasumi Yogata, Hisayoshi Yurimoto, Tomoki Nakamura, Takaaki Noguchi, Ryuji Okazaki, Hiroshi Naraoka, Kanako Sakamoto, Shogo Tachibana, Sei-ichiro Watanabe, Yuichi Tsuda
    Nature Communications 15 7488 2024年8月29日  査読有り
    Abstract Primordial carbon delivered to the early earth by asteroids and meteorites provided a diverse source of extraterrestrial organics from pre-existing simple organic compounds, complex solar-irradiated macromolecules, and macromolecules from extended hydrothermal processing. Surface regolith collected by the Hayabusa2 spacecraft from the carbon-rich asteroid 162173 Ryugu present a unique opportunity to untangle the sources and processing history of carbonaceous matter. Here we show carbonaceous grains in Ryugu can be classified into three main populations defined by spectral shape: Highly aromatic (HA), Alkyl-Aromatic (AA), and IOM-like (IL). These carbon populations may be related to primordial chemistry, since C and N isotopic compositions vary between the three groups. Diffuse carbon is occasionally dominated by molecular carbonate preferentially associated with coarse-grained phyllosilicate minerals. Compared to related carbonaceous meteorites, the greater diversity of organic functional chemistry in Ryugu indicate the pristine condition of these asteroid samples.
  • Satoru Iguchi, Toru Yamada, Yasumasa Yamasaki, Toshikazu Onishi, Daisuke Yamauchi, Fuminori Tsuchiya, Keitaro Takahashi, Takeru Matsumoto, Naoki Isobe, Takahiro Iwata, Naoto Usami, Yutaro Sekimoto, Yasuyuki Miyazaki, Takanao Saiki, Osamu Mori, Tetsuo Yoshimitsu
    Space Telescopes and Instrumentation 2024: Optical, Infrared, and Millimeter Wave 99-99 2024年8月23日  
  • Takeru Matsumoto, Yasumasa Yamasaki, Toshikazu Onishi, Satoru Iguchi, Toru Yamada, Daisuke Yamauchi, Fuminori Tsuchiya, Keitaro Takahashi, Naoki Isobe, Takahiro Iwata, Naoto Usami, Yutaro Sekimoto, Yasuyuki Miyazaki, Takanao Saiki, Osamu Mori, Tetsuo Yoshimitsu
    Space Telescopes and Instrumentation 2024: Optical, Infrared, and Millimeter Wave 214-214 2024年8月23日  
  • Yoshinori Takano, Hiroshi Naraoka, Jason P. Dworkin, Toshiki Koga, Kazunori Sasaki, Hajime Sato, Yasuhiro Oba, Nanako O. Ogawa, Toshihiro Yoshimura, Kenji Hamase, Naohiko Ohkouchi, Eric T. Parker, José C. Aponte, Daniel P. Glavin, Yoshihiro Furukawa, Junken Aoki, Kuniyuki Kano, Shin Ichiro M. Nomura, Francois Regis Orthous-Daunay, Philippe Schmitt-Kopplin, Hisayoshi Yurimoto, Tomoki Nakamura, Takaaki Noguchi, Ryuji Okazaki, Hikaru Yabuta, Kanako Sakamoto, Toru Yada, Masahiro Nishimura, Aiko Nakato, Akiko Miyazaki, Kasumi Yogata, Masanao Abe, Tatsuaki Okada, Tomohiro Usui, Makoto Yoshikawa, Takanao Saiki, Satoshi Tanaka, Fuyuto Terui, Satoru Nakazawa, Sei Ichiro Watanabe, Yuichi Tsuda, Shogo Tachibana
    Nature communications 15(1) 5708 2024年7月10日  
    We report primordial aqueous alteration signatures in water-soluble organic molecules from the carbonaceous asteroid (162173) Ryugu by the Hayabusa2 spacecraft of JAXA. Newly identified low-molecular-weight hydroxy acids (HO-R-COOH) and dicarboxylic acids (HOOC-R-COOH), such as glycolic acid, lactic acid, glyceric acid, oxalic acid, and succinic acid, are predominant in samples from the two touchdown locations at Ryugu. The quantitative and qualitative profiles for the hydrophilic molecules between the two sampling locations shows similar trends within the order of ppb (parts per billion) to ppm (parts per million). A wide variety of structural isomers, including α- and β-hydroxy acids, are observed among the hydrophilic molecules. We also identify pyruvic acid and dihydroxy and tricarboxylic acids, which are biochemically important intermediates relevant to molecular evolution, such as the primordial TCA (tricarboxylic acid) cycle. Here, we find evidence that the asteroid Ryugu samples underwent substantial aqueous alteration, as revealed by the presence of malonic acid during keto-enol tautomerism in the dicarboxylic acid profile. The comprehensive data suggest the presence of a series for water-soluble organic molecules in the regolith of Ryugu and evidence of signatures in coevolutionary aqueous alteration between water and organics in this carbonaceous asteroid.
  • Mutsumi Komatsu, Hikaru Yabuta, Yoko Kebukawa, Lydie Bonal, Eric Quirico, Timothy J. Fagan, George D. Cody, Jens Barosch, Laure Bejach, Emmanuel Dartois, Alexandre Dazzi, Bradley De Gregorio, Ariane Deniset‐Besseau, Jean Duprat, Cecile Engrand, Minako Hashiguchi, Zita Martins, Jérémie Mathurin, Gilles Montagnac, Smail Mostefaoui, Larry R. Nittler, Takuji Ohigashi, Taiga Okumura, Laurent Rémusat, Scott Sandford, Rhonda Stroud, Hiroki Suga, Yoshio Takahashi, Yasuo Takeichi, Yusuke Tamenori, Maximilien Verdier‐Paoletti, Shohei Yamashita, Hisayoshi Yurimoto, Tomoki Nakamura, Takaaki Noguchi, Ryuji Okazaki, Hiroshi Naraoka, Kanako Sakamoto, Makoto Yoshikawa, Takanao Saiki, Satoshi Tanaka, Fuyuto Terui, Satoru Nakazawa, Tomohiro Usui, Masanao Abe, Tatsuaki Okada, Toru Yada, Masahiro Nishimura, Aiko Nakato, Akiko Miyazaki, Kasumi Yogata, Shogo Tachibana, Sei‐ichiro Watanabe, Yuichi Tsuda
    Meteoritics & Planetary Science 2024年7月4日  

MISC

 205
  • 荒川 政彦, 門野 敏彦, 高木 靖彦, 和田 浩二, 平田 成, 小林 正規, 本田 理恵, 白井 慶, 早川 雅彦, 岡本 千里, 小川 和律, 矢野 創, 中澤 暁, 飯島 祐一, 佐伯 孝尚, 今村 裕志, 澤田 弘崇
    日本惑星科学会秋期講演会予稿集 2012 114-114 2012年10月24日  
  • 荒川 政彦, 渡邊 誠一郎, 小林 正規, 和田 浩二, 田中 智, 白石 浩章, 飯島 祐一, 小林 直樹, 佐伯 孝尚, 本田 理恵, 門野 敏彦, 鈴木 絢子, 保井 みなみ
    遊・星・人 : 日本惑星科学会誌 21(3) 247-252 2012年9月  査読有り
  • 佐伯孝尚, 今村裕志, 澤田弘崇, 早川雅彦, 白井慶, 荒川政彦, 門野敏彦, 高木靖彦, 和田浩二
    宇宙科学技術連合講演会講演集(CD-ROM) 56th 2012年  
  • 澤田弘崇, 佐伯孝尚, 今村裕志, 小川和律, 白井慶, 本田理恵, 荒川政彦
    宇宙科学技術連合講演会講演集(CD-ROM) 56th 2012年  
  • Takanao Saiki, Hiroshi Imamura, Hirotaka Sawasa, Chisato Okamoto, Kei Shirai, Masahiko Hayakawa, Masahiko Arakawa, Toshihiko Kadono, Yasuhiko Takagi, Koji Wada, Makoto Yoshikawa
    Proceedings of the International Astronautical Congress, IAC 3 1654-1659 2012年  
    JAXA's next asteroid investigator is now under development supposing a launch in 2014. The new mission is called HAYABUSA-2. It is a similar sample return mission to HAYABUSA, however its target asteroid is different from HAYABUSA. From the point of the scientific objective, 1999JU3 which is the asteroid with the primitive composition (C-type) is chosen as the target. HAYABUSA-2 is planned to be equipped with some new components. A small carry-on impactor (SCI) is one of the new challenges that were not seen with HAYABUSA. SCI is a small impact system for creating an artificial crater. One of the most important scientific objectives of HAYABUSA-2 is to investigate chemical and physical properties of the internal materials in order to understand the formation history of small bodies. The impact system is considered one of the most effective methods for investigating the inner structure of asteroids. We can extend our knowledge about asteroids by observing the diameter, depth and shape of the artificial crater. Additionally, the direct investigation of the inner materials of the asteroid becomes possible by sampling materials inside of the crater. This paper presents the development status of SCI and the results of its development tests. Copyright © (2012) by the International Astronautical Federation.
  • Yuya Mimasu, Tomohiro Yamaguchi, Masaki Nakamiya, Ryu Funase, Takanao Saiki, Yuichi Tsuda, Osamu Mori, Jun'ichiro Kawaguchi
    Advances in the Astronautical Sciences 142 3547-3560 2012年  
    It is well known that the thrust force of the solar sail due to the solar radiation pressure is changed by the orientation of the sail with respect to the Sun direction. Therefore, the orbit of the solar sail can be controlled by changing the attitude of the spacecraft. In this study, we consider the spinning solar power sail IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun), which succeeded to become the world's first flight solar sail in orbit. The IKAROS attitude, i.e. the spin-axis direction is nominally controlled by the rhumb-line control method. By utilizing the solar radiation pressure (SRP) torque, however, we are able to change the direction of the spin-axis only by controlling its spin rate. This is because the spin axis direction relates to the balance between the angular momentum of spinning and the SRP torque. Thus, we can control the solar sail's orbit by controlling the spin rate. The main objective in this study is to construct the orbit control strategy of the spinning solar sail via the spin rate control.
  • Ryu Funase, Yuya Mimasu, Yoshikazu Chishiki, Yoji Shirasawa, Yuichi Tsuda, Takanao Saiki, Jun'ichiro Kawaguchi
    Advances in the Astronautical Sciences 142 1737-1754 2012年  
    A fuel-free attitude control system for a spinning solar sail which utilizes solar radiation pressure was developed. This system consists of thin-film devices attached to the sail that electrically control their optical parameters such as reflectivity, and the attitude control torque is generated by switching their optical parameters synchronizing with spin motion. Attitude control torque model for a sail of arbitrary shape and deformation was derived. The control system was implemented for Japanese interplanetary solar sail demonstration spacecraft IKAROS and the on-orbit attitude control performance was evaluated.
  • Yuichi Tsuda, Takanao Saiki, Yuya Mimasu, Ryu Funase, Kenji Kitamura
    Advances in the Astronautical Sciences 142 1319-1331 2012年  
    This paper describes an attitude determination strategy for spinner spacecraft based on the Sun and the Earth angles. This method realizes a complete spin vector determination using only one sun sensor. Thus this method is suitable for low cost, resource-limited spacecraft with a moderate attitude determination accuracy requirement. The method has been developed for and is actually used in IKAROS, which is a Japanese interplanetary solar sail demonstration mission. This paper introduces theoretical backgrounds of Sun-Earth based attitude determination and shows how the actual implementation was done in the IKAROS mission. Then the attitude determination performance achieved during the actual operation is evaluated.
  • 荒川 政彦, 本田 理恵, 門野 敏彦, 鈴木 絢子, 保井 みなみ, 渡邊 誠一郎, 小林 正規, 和田 浩二, 田中 智, 白石 浩章, 飯島 祐一, 小林 直樹, 佐伯 孝尚
    日本惑星科学会誌遊星人 21(3) 247-252 2012年  
    小惑星イトカワの再探査は,一度探査したイトカワを再び調査することにより,イトカワから得られる科学的知見をさらに深化させることを目的としている.再探査においては,すでに対象天体の基本的情報(表面地形,重力場等)を持っているので,探査計画の立案においては未知の天体とは大きく異なり,より具体的に探査対象に特化した観測機器を搭載することが可能である.今回提案するミッションは,この再探査のメリットを最大限に生かすために,イトカワ表面で宇宙衝突実験を行う.そして,小惑星環境での衝突物理の解明と衝突によるアクティブ探査を通した内部構造探査を実施する.
  • 米倉 克英, 星野 宏和, 森 治, 津田 雄一, 澤田 弘崇, 船瀬 龍, 佐伯 孝尚, 白澤 洋次, 三桝 裕也, 尾川 順子, 南野 浩之, IKAROS, デモンストレーションチーム
    第 12 回宇宙科学シンポジウム講演集録 P3-05B 2012年1月  
  • Yuichi Tsuda, Takanao Saiki, Mutsuko Y. Morimoto, Naoko Ogawa, Jun'ichiro Kawaguchi
    Proceedings of The 21st Workshop on Astrodynamics and Flight Mechanics 2011年7月  
  • 加藤久敦, 佐伯孝尚
    火薬学会年会講演要旨集 2011 2011年  
  • 佐伯孝尚, 田中啓太
    宇宙科学技術連合講演会講演集(CD-ROM) 55th 2011年  
  • 佐伯孝尚, 津田雄一, 船瀬龍, 三桝裕也, 白澤洋次
    誘導制御シンポジウム資料 28th 2011年  
  • 船瀬龍, 三桝裕也, 津田雄一, 佐伯孝尚, 岡野仁庸, 管野剛
    宇宙科学技術連合講演会講演集(CD-ROM) 55th 2011年  
  • 松本純, 佐伯孝尚, 津田雄一
    宇宙科学技術連合講演会講演集(CD-ROM) 55th 2011年  
  • 津田雄一, 佐伯孝尚, 尾川順子, 森本睦子
    宇宙科学技術連合講演会講演集(CD-ROM) 55th 2011年  
  • 地福亮, 田中啓太, 大谷翔, 川口淳一郎, 津田雄一, 佐伯孝尚, 白澤洋次
    宇宙科学技術連合講演会講演集(CD-ROM) 55th 2011年  
  • 大谷翔, 川口淳一郎, 津田雄一, 佐伯孝尚, 白澤洋次, 田中啓太, 地福亮
    宇宙科学技術連合講演会講演集(CD-ROM) 55th 2011年  
  • 地福亮, 川口淳一郎, 津田雄一, 佐伯孝尚
    アストロダイナミクスシンポジウム講演後刷り集(Web) 20th 2011年  
  • 三桝裕也, 船瀬龍, 佐伯孝尚, 津田雄一, 川口淳一郎
    アストロダイナミクスシンポジウム講演後刷り集(Web) 20th 2011年  
  • 森治, 津田雄一, 津田雄一, 澤田弘崇, 船瀬龍, 山本高行, 佐伯孝尚, 米倉克英, 星野宏和, 南野浩之, 遠藤達也, 川口淳一郎
    日本機械学会年次大会講演論文集(CD-ROM) 2011 2011年  
  • Yuichi Tsuda, Takanao Saiki, Yuya Mimasu, Ryu Funase
    Advances in the Astronautical Sciences 140 147-161 2011年  
    This paper describes a method of modeling attitude dynamics of spinning solar sail spacecraft under influence of solar radiation pressure (SRP). This method is verified and actually exploited in the operation of Japanese interplanetary solar sail demonstration spacecraft IKAROS. IKAROS shows a unique attitude behavior due to strong SRP effect. This paper shows a new attitude model of spinning sail, which is verified by flight data of IKAROS. It is also shown that the model proposed in this paper has a direct relation with the Generalized Sail Model.
  • Takanao Saiki, Hirotaka Sawada, Chisato Okamoto, Hajime Yano, Yasuhiko Takagi, Yasuhiro Akahoshi, Makoto Yoshikawa
    62nd International Astronautical Congress 2011, IAC 2011 2 1343-1348 2011年  
    The Japanese asteroid explorer HAYABUSA launched in 2003 arrived at its target asteroid ITOKAWA in September, 2005. HAYABUSA has made amount of scientific discoveries and technological achievements during its stay at ITOKAWA and it came back to the Earth on June 13, 2010. Under this situation, the next asteroid exploration mission started. The spacecraft is called HAYABUSA-2. Although its design basically follows HAYABUSA, some new components are planned to be equipped in HAYABUSA-2 mission. A small carry-on impactor is one of the new challenges that were not seen with HAYABUSA. One of the most important scientific objectives of HAYABUSA-2 is to investigate chemical and physical properties of the internal materials and the internal structures in order to understand the formation history of small bodies. In order to achieve this objective, the impactor is required to remove the surface regolith and create an artificial crater on the surface of the asteroid. Ulis paper presents the overview of our small carry-on impactor system and impact operation of HAYABUSA-2 mission. And how to improve this impactor when it is applied to another small body exploration mission is also presented in this paper. Copyright ©2011 by the International Astronautical Federation. All rights reserved.
  • 森 治, 遠藤 達也, 川口 淳一郎, 津田 雄一, 澤田 弘崇, 船瀬 龍, 山本 高行, 佐伯 孝尚, 米倉 克英, 星野 宏和, 南野 浩之
    年次大会 2011 _J191063-1-_J191063-5 2011年  査読有り
    Japan Aerospace Exploration Agency (JAXA) successfully achieved the world's first solar power sail technology by IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun) mission in 2010. It demonstrated a photon propulsion and thin film solar power generation during its interplanetary cruise. The 200m2-span sail was deployed and kept extended by centrifugal force of the spacecraft rotation. IKAROS also succeeded in accelerating and controlling the orbit by actively exploiting solar radiation pressure, and thus became the world's first actual solar sailer flying an interplanetary voyage. This paper presents the design of IKAROS solar sail system, operation results and introduces a perspective of this new technology to apply to the next generation mission toward Jupiter and Trojan asteroids.
  • Mori Osamu, Tsuda Yuichi, Sawada Hirotaka, FUNASE Ryu, YAMAMOTO Takayuki, SAIKI Takanao, YONEKURA Katsuhide, HOSHINO Hirokazu, MINAMINO Hiroyuki, ENDO Tatsuya, KAWAGUCHI Junichiro
    電子情報通信学会技術研究報告. SANE, 宇宙・航行エレクトロニクス 110(250) 155-160 2010年10月20日  
    The Japan Aerospace Exploration Agency (JAXA) makes the world's first solar power sail craft IKAROS demonstration of photon propulsion and thin film solar power generation during its interplanetary cruise. The spacecraft deploys and spans a membrane of 20 meters in diameter using the spin centrifugal force. It also deploys thin film solar cells on the membrane, in order to evaluate its thermal control property and anti-radiation performance in the real operational field. The spacecraft weighs approximately 310kg, launched together with the agency's Venus Climate Orbiter, AKATSUKI on May 21, 2010. This paper presents the summary of development and operation of IKAROS.
  • 高木 靖彦, 中村 良介, 北里 宏平, 岡田 達明, 矢野 創, 津田 雄一, 佐伯 孝尚, 岡本 千里, 吉川 真, はやぶさ2プリプロジェクトチーム
    日本惑星科学会秋期講演会予稿集 2010 85-85 2010年10月6日  
  • 森 治, 白澤 洋次, 今泉 継男, 三桝 裕也, 元岡 範純, 佐藤 祥悟, 田中 啓太, 浦町 光, 善場 祐介, 北嶋 麻里絵, 羽染 円絵, 志田 真樹, 田中 孝治, 澤田 弘崇, 船瀬 龍, 遠藤 達也, 奥泉 信克, 矢野 創, 岡本 千里, 横田 力男, 津田 雄一, 佐伯 孝尚, 川口 淳一郎, ソーラーセイルWG
    宇宙航空研究開発機構研究開発報告 9(09-007) 73-84 2010年3月  
    ソーラーセイルWG では,太陽の光子の圧力を受けて進む光子セイルに,薄膜太陽電池を貼り付けて大電力を発生し高比推力のイオンエンジンを駆動する推進システム,ソーラー電力セイルの検討を進めている.このシステムの確立において重要な技術課題である大型膜面の展開機能を検証するため,大気球を用いた大型膜面の展開総合実験を計画し,展開システムの開発を行った.あいにく実験場の天候不良により平成20 年度に続き,放球を実施できなかったが,本論文では,この実験の内容および位置付けについて紹介する.
  • 加藤久敦, 塩田誠, 佐伯孝尚
    火薬学会年会講演要旨集 2010 2010年  
  • 津田雄一, 佐伯孝尚, 三桝裕也, 船瀬龍, 山口智宏, 中宮賢樹, 白澤洋次, 池田人
    宇宙科学技術連合講演会講演集(CD-ROM) 54th 2010年  
  • 三桝裕也, 山口智宏, 池田人, 中宮賢樹, 船瀬龍, 佐伯孝尚, 津田雄一, 川口淳一郎
    宇宙科学技術連合講演会講演集(CD-ROM) 54th 2010年  
  • 船瀬龍, 川口淳一郎, 森治, 津田雄一, 佐伯孝尚, 澤田弘崇
    宇宙科学技術連合講演会講演集(CD-ROM) 54th 2010年  
  • 森治, 津田雄一, 澤田弘崇, 船瀬龍, 山本高行, 佐伯孝尚, 米倉克英, 南野浩之, 星野宏和, 遠藤達也, 森本睦子, 川勝康弘, 川口淳一郎
    宇宙科学技術連合講演会講演集(CD-ROM) 54th 2010年  
  • 佐伯孝尚, 津田雄一, 船瀬龍, 三桝裕也, 白澤洋次
    宇宙科学技術連合講演会講演集(CD-ROM) 54th 2010年  
  • 船瀬龍, 三桝裕也, 白澤洋次, 津田雄一, 佐伯孝尚, 森治
    宇宙科学技術連合講演会講演集(CD-ROM) 54th 2010年  
  • Yuichi Tsuda, O. Mori, R. Funase, H. Sawada, T. Yamamoto, T. Saiki, T. Endo, J. Kawaguchi
    61st International Astronautical Congress 2010, IAC 2010 12 10379-10386 2010年  
    JAXA launched the world's first deep-space solar sail demonstration spacecraft "IKAROS" on May 21, 2010. IKAROS was injected to an Earth-Venus trajectory to demonstrate several key technologies for solar sail utilizing the deep space flight environment. IKAROS succeeded in deploying a 20m-span solar sail on June 9, and is now flying toward Venus with the assist of solar photon acceleration. This paper describes the mission design, system design, solar sail deployment operation and current flight status of IKAROS. Copyright ©2010 by the International Astronautical Federation. All rights reserved.
  • Ryu Funase, Osamu Mori, Yuichi Tsuda, Yoji Shirasawa, Takanao Saiki, Yuya Mimasu, Junichiro Kawaguchi
    61st International Astronautical Congress 2010, IAC 2010 6 4720-4725 2010年  査読有り
    This paper introduces new attitude control system for solar sail which leverages solar radiation pressure and achieves completely fuel-free and oscillation-free attitude control of flexible spinning solar sail. Novel attitude control device was developed, which is a thin film-type device and can electrically control its optical parameters such as reflectivity to generate unbalance of the solar radiation pressure applied to the edge of the sail. By using this device, minute and continuous control torque can be applied to the sail so that very stable and fuel-free attitude control of large and flexible membrane is realized. The control system was implemented as an optional attitude control system for small solar power sail demonstrator IKAROS. On-orbit attitude control experiments were conducted and the performance of the controller was successfully verified compared with the ground-based analytical performance estimation. Copyright ©2010 by the International Astronautical Federation. All rights reserved.
  • Saito Hirobumi, Mizuno Takahide, Kawahara Kousuke, SHINKAI Kenji, SAIKI Takanao, FUKUSHIMA Yousuke, HAMADA Yusuke, SASAKI Hiroyuki, KATUMOTO Sachiko, KAJIKAWA Yasuhiro
    電子情報通信学会技術研究報告. SANE, 宇宙・航行エレクトロニクス 107(2) 19-24 2007年4月9日  
    Miniature space GPS receivers have been developed by means of automobile-navigation technology. We expanded the frequency sweep range in order to cover large Doppler shift on orbit. The GPS receiver was modified to output pseudorange data with accurate time tag. We tested the performance in low earth orbits by means of a GPS simulator. The range error caused by the receiver is measured to be 1 meter. The position accuracy is estimated to be less than 17 meters (rms) in the low earth orbits. This GPS receiver was on-boarded on INDEX satellite, which launched in 2005. Cold start positioning was confirmed repeatedly to finish within 30 minutes on orbit. The orbit determination was performed to evaluate the random position error of GPS receiver by means of the residual error. The random error of GPS position is as large as 2 meter for PDDP=2 on orbit. These results on orbit are consistent with the simulation results in use of a GPS simulator.
  • 齋藤 宏文, 水野 貴秀, 川原 康介, 新開 研児, 佐伯 孝尚, 福島 洋介, 浜田 裕介, 佐々木 博幸, 勝本 幸子, 梶川 泰広, Saito Hirobumi, Mizuno Takahide, Kawahara Kosuke, Shinkai Kenji, Saiki Takanao, Fukushima Yosuke, Hamada Yusuke, Sasaki Hiroyuki, Katsumoto Sachiko, Kajikawa Yasuhiro
    宇宙航空研究開発機構特別資料: 先進的軌道計測・決定技術に関する研究会論文集 = JAXA Special Publication: Proceedings of Advanced Orbit Measurement and Orbit Calculation Technologies (6) 27-34 2007年3月30日  
    重量35gの民生用車載GPS(Global Positioning System)受信機を基に、宇宙用の超小型GPS受信機を開発し、これをJAXA宇宙科学研究所が開発して2005年8月に打ち上げられた小型科学衛星れいめいに搭載した。本稿では、車載用GPSからの改修内容、軌道上での性能を報告する。車載用GPS衛星は、そのままでは衛星軌道上では動作しない。これは、衛星軌道上でのドップラー周波数が最大50kHz程度あるからである。車載用GPS受信機の初期捕捉時の周波数掃引範囲を広げるために、車載GPSメーカーにソフトウェアの改修を依頼した。われわれの手で、GPSシミュレーターを用いた軌道上性能の評価試験を行い、(1)30分以内のコールドスタート測位、(2)測位精度15m(電離層効果ふくむ)の性能を地上にて確認した。このGPS受信機は、トータルドーズ20krad、プロトン照射ではSELフリー、軌道上SEU(Single Event Upset)予測頻度1週間あたり数回程度という放射線耐性を持っている。資料番号: AA0063223005レポート番号: JAXA-SP-06-015
  • 松山行一, 阿部直彦, 中村信乃夫, 佐伯孝尚, 志村康治
    宇宙科学技術連合講演会講演集(CD-ROM) 51st 2007年  
  • 齋藤宏文, 水野貴秀, 川原康介, 新開研児, 佐伯孝尚, 福島洋介, 浜田裕介, 佐々木博幸, 勝本幸子, 梶川泰広
    宇宙航空研究開発機構特別資料 JAXA-SP- (06-015) 2007年  
  • 齋藤 宏文, 水野 貴秀, 川原 康介, 津田 雄一, 新開 研児, 佐伯 孝尚, 福島 洋介, 浜田 裕介, 佐々木 博幸, 勝本 幸子, 黒木 聖司, 梶川 泰広
    電子情報通信学会技術研究報告. SANE, 宇宙・航行エレクトロニクス 106(217) 17-22 2006年8月18日  
    35gの車載用GPS受信機をベースに宇宙用の超小型のGPS受信機を開発した。衛星軌道では大きなドップラー周波数があるため、GPS受信機の捕捉周波数掃引範囲を広げる改修を行った。GPSシミュレータを用いて、コールドスタート機能は30分以内にできること、15m以下の測位精度があることを検証をした。このGPS受信機を小型衛星れいめいに搭載した。軌道上でのコールドスタート性能、測位精度などを評価した結果を紹介する。
  • Saito Hirobumi, Mizuno Takahide, Tsuda Yuichi, Saiki Takanao, Hamada Yusuke, Sasaki Hiroyuki
    電子情報通信学会総合大会講演論文集 2006(1) "SE-11"-"SE-12" 2006年3月8日  
  • 佐伯孝尚, 水田大哉, 川口淳一郎
    誘導制御シンポジウム資料 23rd 2006年  
  • 齋藤宏文, 水野貴秀, 川原康介, 津田雄一, 新開研児, 佐伯孝尚, 福島洋介, 浜田裕介, 佐々木博幸, 勝本幸子, 黒木聖司, 梶川泰広
    宇宙科学技術連合講演会講演集(CD-ROM) 50th(06-015) 2006年  
  • Keiko Kuroshima, Shuhei Nishimaki, Takanao Saiki, Jun'ichiro Kawaguchi
    Advances in the Astronautical Sciences 123 III 2593-2607 2006年  
    This paper presents a very high altitude, Sun-Synchronous orbit around the Earth for astronomy satellites. It includes a cart wheel orbit in Hill's motion. Considering the perturbation owing to the Earth gravity, the period of the in-plane motion and out-of-plane motion are different and trajectory becomes Lissajous. The results analytically obtained are examined and compared with those via numerical integration. In addition, it is shown that the fuels amount, which is inquired to keep nominal Cart Wheel orbit properties, decreases as the altitude increases. And, the conclusion is that the Cart Wheel orbit is a kind of sun-synchronous orbit and highly practical with affordable correction velocity increment.
  • 佐伯孝尚, 川口淳一郎
    システム制御情報学会研究発表講演会講演論文集 124 I 879-893 2006年  
  • 佐伯孝尚
    宇宙科学技術連合講演会講演集(CD-ROM) 49th 2005年  
  • Takanao Saiki, Jun'ichiro Kawaguchi
    Advances in the Astronautical Sciences 119(SUPPL.) 2555-2569 2005年  
    In formation flight missions, it is very important to control the relative positions of satellites. Although there have been many researches on the relative position control for formation flight, most of them assumes the centralized architecture in which an administrator collects every relative position and velocity information about the formation. However, in case the formation consists of many satellites, it takes long time to collect the information of all the satellites and to distribute the command to every satellite. Therefore, the centralized architecture is unsuitable for the control system that requires a rapid response. Beside, if the central control is down, the system loses the formation control functions thoroughly. One strategy that overcomes these flaws is to make each satellite be controlled by using the information on its nearby satellites. This paper discusses the guidance law based on the regional limited information to maintain the formation. In this case, the information structure of the system greatly influences the control law and the control performance. In this study, we discuss how the control laws are designed, first. And how the information structure influence the configuration of the formation is focused on. Copyright © 2004 by The American Astronautical Society.

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