Curriculum Vitaes

Takanao Saiki

  (佐伯 孝尚)

Profile Information

Affiliation
Professor, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
Degree
Ph.D.(Mar, 2005, The University of Tokyo)

J-GLOBAL ID
200901090793977023
researchmap Member ID
5000092383

Papers

 214
  • Shota Kikuchi, Kei Shirai, Ko Ishibashi, Koji Wada, Yasuhiro Yokota, Rie Honda, Toshihiko Kadono, Yuri Shimaki, Naoya Sakatani, Kazunori Ogawa, Hirotaka Sawada, Takanao Saiki, Yuya Mimasu, Yuto Takei, Seiji Sugita, Toru Kouyama, Naru Hirata, Satoru Nakazawa, Makoto Yoshikawa, Satoshi Tanaka, Sei-ichiro Watanabe, Yuichi Tsuda, Masahiko Arakawa
    Advances in Space Research, May, 2024  
  • Yan Hu, Frédéric Moynier, Wei Dai, Marine Paquet, Tetsuya Yokoyama, Yoshinari Abe, Jérôme Aléon, Conel M.O.D. Alexander, Sachiko Amari, Yuri Amelin, Ken ichi Bajo, Martin Bizzarro, Audrey Bouvier, Richard W. Carlson, Marc Chaussidon, Byeon Gak Choi, Nicolas Dauphas, Andrew M. Davis, Tommaso Di Rocco, Wataru Fujiya, Ryota Fukai, Ikshu Gautam, Makiko K. Haba, Yuki Hibiya, Hiroshi Hidaka, Hisashi Homma, Peter Hoppe, Gary R. Huss, Kiyohiro Ichida, Tsuyoshi Iizuka, Trevor R. Ireland, Akira Ishikawa, Shoichi Itoh, Noriyuki Kawasaki, Noriko T. Kita, Koki Kitajima, Thorsten Kleine, Shintaro Komatani, Alexander N. Krot, Ming Chang Liu, Yuki Masuda, Mayu Morita, Kazuko Motomura, Izumi Nakai, Kazuhide Nagashima, David Nesvorný, Ann Nguyen, Larry Nittler, Morihiko Onose, Andreas Pack, Changkun Park, Laurette Piani, Liping Qin, Sara S. Russell, Naoya Sakamoto, Maria Schönbächler, Lauren Tafla, Haolan Tang, Kentaro Terada, Yasuko Terada, Tomohiro Usui, Sohei Wada, Meenakshi Wadhwa, Richard J. Walker, Katsuyuki Yamashita, Qing Zhu Yin, Shigekazu Yoneda, Edward D. Young, Hiroharu Yui, Ai Cheng Zhang, Tomoki Nakamura, Hiroshi Naraoka, Takaaki Noguchi, Ryuji Okazaki, Kanako Sakamoto, Hikaru Yabuta, Masanao Abe, Akiko Miyazaki, Aiko Nakato, Masahiro Nishimura, Tatsuaki Okada, Toru Yada, Kasumi Yogata, Satoru Nakazawa, Takanao Saiki, Satoshi Tanaka, Fuyuto Terui, Yuichi Tsuda, Sei ichiro Watanabe, Makoto Yoshikawa, Shogo Tachibana, Hisayoshi Yurimoto
    Icarus, 409, Feb, 2024  Peer-reviewed
    C-type asteroids are the presumed home to carbonaceous chondrites, some of which contain abundant life-forming volatiles and organics. For the first time, samples from a C-type asteroid (162173 Ryugu) were successfully returned to Earth by JAXA's Hayabusa2 mission. These pristine samples, uncontaminated by the terrestrial environment, allow a direct comparison with carbonaceous chondrites. This study reports the stable K isotopic compositions (expressed as δ41K) of Ryugu samples and seven carbonaceous chondrites to constrain the origin of K isotopic variations in the early Solar System. Three aliquots of Ryugu particles collected at two touchdown sites have identical δ41K values, averaged at −0.194 ± 0.038‰ (2SD). The K isotopic composition of Ryugu falls within the range of δ41K values measured on representative CI chondrites, and together, they define an average δ41K value of −0.185 ± 0.078‰ (2SE), which provides the current best estimate of the K isotopic composition of the bulk Solar System. Samples of CI chondrites with δ41K values that deviate from this range likely reflect terrestrial contaminations or compositional heterogeneities at sampled sizes. In addition to CI chondrites, substantial K isotopic variability is observed in other carbonaceous chondrites and within individual chondritic groups, with δ41K values inversely correlated with K abundances in many cases. These observations indicate widespread fluid activity occurred in chondrite parent bodies, which significantly altered the original K abundances and isotopic compositions of chondrules and matrices established at their accretion.
  • Toru Matsumoto, Takaaki Noguchi, Akira Miyake, Yohei Igami, Mitsutaka Haruta, Yusuke Seto, Masaaki Miyahara, Naotaka Tomioka, Hikaru Saito, Satoshi Hata, Dennis Harries, Aki Takigawa, Yusuke Nakauchi, Shogo Tachibana, Tomoki Nakamura, Megumi Matsumoto, Hope A. Ishii, John P. Bradley, Kenta Ohtaki, Elena Dobrică, Hugues Leroux, Corentin Le Guillou, Damien Jacob, Francisco de la Peña, Sylvain Laforet, Maya Marinova, Falko Langenhorst, Pierre Beck, Thi H.V. Phan, Rolando Rebois, Neyda M. Abreu, Jennifer Gray, Thomas Zega, Pierre M. Zanetta, Michelle S. Thompson, Rhonda Stroud, Kate Burgess, Brittany A. Cymes, John C. Bridges, Leon Hicks, Martin R. Lee, Luke Daly, Phil A. Bland, Michael E. Zolensky, David R. Frank, James Martinez, Akira Tsuchiyama, Masahiro Yasutake, Junya Matsuno, Shota Okumura, Itaru Mitsukawa, Kentaro Uesugi, Masayuki Uesugi, Akihisa Takeuchi, Mingqi Sun, Satomi Enju, Tatsuhiro Michikami, Hisayoshi Yurimoto, Ryuji Okazaki, Hikaru Yabuta, Hiroshi Naraoka, 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
    Nature Astronomy, 8(2) 207-215, Feb, 2024  Peer-reviewed
    Large amounts of nitrogen compounds, such as ammonium salts, may be stored in icy bodies and comets, but the transport of these nitrogen-bearing solids into the near-Earth region is not well understood. Here, we report the discovery of iron nitride on magnetite grains from the surface of the near-Earth C-type carbonaceous asteroid Ryugu, suggesting inorganic nitrogen fixation. Micrometeoroid impacts and solar wind irradiation may have caused the selective loss of volatile species from major iron-bearing minerals to form the metallic iron. Iron nitride is a product of nitridation of the iron metal by impacts of micrometeoroids that have higher nitrogen contents than the CI chondrites. The impactors are probably primitive materials with origins in the nitrogen-rich reservoirs in the outer Solar System. Our observation implies that the amount of nitrogen available for planetary formation and prebiotic reactions in the inner Solar System is greater than previously recognized.
  • Kazuhiko Ninomiya, Takahito Osawa, Kentaro Terada, Taiga Wada, Shunsaku Nagasawa, I‐Haun Chiu, Tomoki Nakamura, Tadayuki Takahashi, Yasuhiro Miyake, M. Kenya Kubo, Soshi Takeshita, Akihiro Taniguchi, Izumi Umegaki, Shin Watanabe, Toshiyuki Azuma, Miho Katsuragawa, Takahiro Minami, Kazumi Mizumoto, Koichiro Shimomura, Shin'ichiro Takeda, Tomoyo Morita, Mizuha Kikuiri, Kana Amano, Eiichi Kagawa, Yoshihiro Furukawa, Hisayoshi Yurimoto, Takaaki Noguchi, Ryuji Okazaki, Hikaru Yabuta, Hiroshi Naraoka, Kanako Sakamoto, Shogo Tachibana, 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
    Meteoritics & Planetary Science, Jan 31, 2024  Peer-reviewed
    Abstract Samples from asteroid Ryugu, brought back by asteroid explorer Hayabusa2, are important for investigating the origin and evolution of the solar system. Here, we report the elemental compositions of a 123‐mg Ryugu sample determined with a nondestructive muon elemental analysis method. This method is a powerful tool for determining bulk chemical composition, including light elements such as C, N, and O. From the muonic x‐ray spectra with three carbonaceous chondrites, the relationship between the elemental composition and muonic x‐ray intensity was determined for each element. Calibration curves showed linearity, and the elemental composition of Ryugu was quantitatively determined. The results reflect the average bulk elemental composition of asteroid Ryugu owing to the large amount of samples. Ryugu has an elemental composition similar to that of Orgueil (CI1) and should be classified as CI1. However, the O/Si ratio of Ryugu is 25% lower than that of Orgueil, indicating that Orgueil may have been seriously contaminated by terrestrial materials after its fall to Earth. These results indicate that the Ryugu sample is more representative than the CI chondrites as a solid material of the solar system.
  • Mayu Morita, Hiroharu Yui, Shu Hei Urashima, Morihiko Onose, Shintaro Komatani, Izumi Nakai, Yoshinari Abe, Yasuko Terada, Hisashi Homma, Kazuko Motomura, Kiyohiro Ichida, Tetsuya Yokoyama, Kazuhide Nagashima, Jérôme Aléon, Conel M. Conel, Sachiko Amari, Yuri Amelin, Ken Ichi Bajo, Martin Bizzarro, Audrey Bouvier, Richard W. Carlson, Marc Chaussidon, Byeon Gak Choi, Nicolas Dauphas, Andrew M. Davis, Wataru Fujiya, Ryota Fukai, Ikshu Gautam, Makiko K. Haba, Yuki Hibiya, Hiroshi Hidaka, Peter Hoppe, Gary R. Huss, Tsuyoshi Iizuka, Trevor R. Ireland, Akira Ishikawa, Shoichi Itoh, Noriyuki Kawasaki, Noriko T. Kita, Kouki Kitajima, Thorsten Kleine, Sasha Krot, Ming Chang Liu, Yuki Masuda, Frédéric Moynier, Ann Nguyen, Larry Nittler, Andreas Pack, Changkun Park, Laurette Piani, Liping Qin, Tommaso Di Rocco, Sara S. Russell, Naoya Sakamoto, Maria Schönbächler, Lauren Tafla, Haolan Tang, Kentaro Terada, Tomohiro Usui, Sohei Wada, Meenakshi Wadhwa, Richard J. Walker, Katsuyuki Yamashita, Qing Zhu Yin, Shigekazu Yoneda, Edward D. Young, Ai Cheng Zhang, Tomoki Nakamura, Hiroshi Naraoka, Takaaki Noguchi, Ryuji Okazaki, Kanako Sakamoto, Hikaru Yabuta, Masanao Abe, Akiko Miyazaki, Aiko Nakato, Masahiro Nishimura, Tatsuaki Okada, Toru Yada, Kasumi Yogata, Satoru Nakazawa, Takanao Saiki, Satoshi Tanaka, Fuyuto Terui, Yuichi Tsuda, Sei Ichiro Watanabe, Makoto Yoshikawa, Shogo Tachibana, Hisayoshi Yurimoto
    Analytical Chemistry, 96(1) 170-178, Jan 9, 2024  
    Characterization of the elemental distribution of samples with rough surfaces has been strongly desired for the analysis of various natural and artificial materials. Particularly for pristine and rare analytes with micrometer sizes embedded on specimen surfaces, non-invasive and matrix effect-free analysis is required without surface polishing treatment. To satisfy these requirements, we proposed a new method employing the sequential combination of two imaging modalities, i.e., microenergy-dispersive X-ray fluorescence (micro-XRF) and Raman micro-spectroscopy. The applicability of the developed method is tested by the quantitative analysis of cation composition in micrometer-sized carbonate grains on the surfaces of intact particles sampled directly from the asteroid Ryugu. The first step of micro-XRF imaging enabled a quick search for the sparsely scattered and micrometer-sized carbonates by the codistributions of Ca2+ and Mn2+ on the Mg2+- and Fe2+-rich phyllosilicate matrix. The following step of Raman micro-spectroscopy probed the carbonate grains and analyzed their cation composition (Ca2+, Mg2+, and Fe2+ + Mn2+) in a matrix effect-free manner via the systematic Raman shifts of the lattice modes. The carbonates were basically assigned to ferroan dolomite bearing a considerable amount of Fe2+ + Mn2+ at around 10 atom %. These results are in good accordance with the assignments reported by scanning electron microscopy-energy-dispersive X-ray spectroscopy, where the thin-sectioned and surface-polished Ryugu particles were applicable. The proposed method requires neither sectioning nor surface polishing; hence, it can be applied to the remote sensing apparatus on spacecrafts and planetary rovers. Furthermore, the non-invasive and matrix effect-free characterization will provide a reliable analytical tool for quantitative analysis of the elemental distribution on the samples with surface roughness and chemical heterogeneity at a micrometer scale, such as art paintings, traditional crafts with decorated shapes, as well as sands and rocks with complex morphologies in nature.

Misc.

 201
  • 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  
  • 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  
    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  
    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  
    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  
    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.
  • Arakawa M., Honda R., Kadono T., Suzuki A., Yasui M., Watanabe S., Kobayashi M., Wada K., Tanaka S., Shiraishi H., Iijima Y., Kobayashi N., Saiki T.
    Planetary People - The Japanese Society for Planetary Sciences, 21(3) 247-252, 2012  
  • Katsuhide Yonekura, Hirokazu Hoshino, Osamu Mori, Yuichi Tsuda, Hirotaka Sawada, Ryu Funase, Takanao Saiki, Yoji Shirasawa, Yuya Mimasu, Naoko Ogawa, Hiroyuki Minamino, IKAROS Demonstration Team
    12th Space Science Symposium, P3-05B, Jan, 2012  
  • Yuichi Tsuda, Takanao Saiki, Mutsuko Y. Morimoto, Naoko Ogawa, Jun'ichiro Kawaguchi
    Proceedings of The 21st Workshop on Astrodynamics and Flight Mechanics, Jul, 2011  
  • 加藤久敦, 佐伯孝尚
    火薬学会年会講演要旨集, 2011, 2011  
  • 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  
  • 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  
  • 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  
  • 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  
  • 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  
  • 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  
  • 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  
  • 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  
  • 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  
  • 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  
  • Yuichi Tsuda, Takanao Saiki, Yuya Mimasu, Ryu Funase
    Advances in the Astronautical Sciences, 140 147-161, 2011  
    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  
    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.
  • MORI Osamu, ENDO Tatsuya, KAWAGUCHI Junichiro, TSUDA Yuichi, SAWADA Hirotaka, FUNASE Ryu, YAMAMOTO Takayuki, Saiki Takanao, YONEKURA Katsuhide, HOSHINO Hirokazu, MINAMINO Hiroyuki
    The Proceedings of Mechanical Engineering Congress, Japan, 2011 _J191063-1-_J191063-5, 2011  Peer-reviewed
    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
    IEICE technical report, 110(250) 155-160, Oct 20, 2010  
    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, Oct 6, 2010  
  • MORI Osamu, Shirasawa YOJI, IMAIZUMI Tsuguo, MIMASU Yuya, MOTOOKA Norizumi, SATO Shogo, TANAKA Keita, URAMACHI Hikaru, ZEMBA Yusuke, KITAJIMA Marie, HASOME Mitsue, SHIDA Maki, TANAKA Koji, SAWADA Hirotaka, FUNASE Ryu, ENDO Tatsuya, OKUIZUMI Nobukatsu, YANO Hajime, OKAMOTO Chisato, YOKOTA Rikio, TSUDA Yuichi, SAIKI Takanao, KAWAGUCHI Jun'ichiro, Solar Sail Working Group
    JAXA research and development report, 9(09-007) 73-84, Mar, 2010  
    The Japan Aerospace Exploration Agency (JAXA) will make the solar power sail craft demonstrate for both its photon propulsion and thin film solar power generation during its interplanetary cruise. The spacecraft deploys and spans its membrane taking the advantage of the spin centrifugal force. The deployment system of large membrane was developed. The overall deployment experiment of solar power sail using a balloon was planned. However the balloon was not launched due to the bad weather. In this paper, the contents and significance of the experiment are reported.
  • 加藤久敦, 塩田誠, 佐伯孝尚
    火薬学会年会講演要旨集, 2010, 2010  
  • 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  
  • 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  
  • 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  
  • 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  
  • 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  
  • 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  
  • 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  
    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  Peer-reviewed
    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
    IEICE technical report, 107(2) 19-24, Apr 9, 2007  
    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.
  • Saito Hirobumi, Mizuno Takahide, Kawahara Kosuke, Shinkai Kenji, Saiki Takanao, Fukushima Yosuke, Hamada Yusuke, Sasaki Hiroyuki, Katsumoto Sachiko, Kajikawa Yasuhiro
    (6) 27-34, Mar 30, 2007  
    Miniature space GPS (Global Positioning System) receivers have been developed by means of automobile-navigation technology. The weight and power consumption of the GPS receiver are 35 g and 1 W, respectively. We expanded the frequency sweep range in order to cover large Doppler shift in orbit. We tested the performance in low earth orbits by means of a GPS simulator. The GSP receiver succeeded in cold start acquisition in less than 30 minutes. This GPS receiver was on-boarded on INDEX satellite launched in August 2005. The performances of cold start acquisition and position accuracy was verified in orbit.
  • 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  
  • 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  
  • SAITO Hirobumi, MIZUNO Takahide, KAWAHARA Kousuke, TUDA Yuichi, SHINKAI Kenji, SAIKI Takanao, FUKUSHIMA Yousuke, HAMADA Yusuke, SASAKI Hiroyuki, KATUMOTO Sachiko, KUROKI Seiji, KAJIKAWA Yasuhiro
    IEICE technical report, 106(217) 17-22, Aug 18, 2006  
    Miniature space GPS receivers have been developed by means of automobile-navigation technology. The weight and power consumption of the GPS receiver are 35g and 1W, respectively. We expanded the frequency sweep range in order to cover large Doppler shift in orbit. We tested the performance in low earth orbits by means of a GPS simulator. The GSP receiver succeeded in cold start acquisition in less than 30 minutes. This GPS receiver was on-boarded on INDEX satellite launched in August 2005. The performances of cold start acquisition and position accuracy was verified in orbit.
  • Saito Hirobumi, Mizuno Takahide, Tsuda Yuichi, Saiki Takanao, Hamada Yusuke, Sasaki Hiroyuki
    Proceedings of the IEICE General Conference, 2006(1) "SE-11"-"SE-12", Mar 8, 2006  
  • 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  
  • 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  
  • Keiko Kuroshima, Shuhei Nishimaki, Takanao Saiki, Jun'ichiro Kawaguchi
    Advances in the Astronautical Sciences, 123 III 2593-2607, 2006  
    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.
  • Takanao Saiki, Jun'ichiro Kawaguchi
    Advances in the Astronautical Sciences, 124 I 879-893, 2006  
    In formation flight missions, it is very important to control and keep the relative positions of spacecrafts. Although there have been many researches on the relative position control, most of them assumes that each spacecraft uses the absolute information about its position and velocity. In this case, various optimizations with the absolute information are possible. However, in order to keep the formation strictly and to avoid the collisions, the feedback control with the relative information between the members is effective. The formations of birds, insects and fish and automatic control of cars are classified as this control system. In this control system, the information propagation structure of the system as well as the local control law of each member determines the control performance of the system. This information propagation structure means the adjacency relation of the formation, that is, "whose relative information can each spacecraft acquire". In this study, the information propagation structure of the formation is focused on and how the information propagation structure influences the behavior of the formation is investigated.
  • 佐伯孝尚
    宇宙科学技術連合講演会講演集(CD-ROM), 49th, 2005  
  • Takanao Saiki, Jun'ichiro Kawaguchi
    Advances in the Astronautical Sciences, 119(SUPPL.) 2555-2569, 2005  
    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.
  • Takanao Saiki, Jun'ichiro Kawaguchi
    International Astronautical Federation - 56th International Astronautical Congress 2005, 5 2993-3001, 2005  
    In formation flying missions, the spacecrafts should keep particular formation, so it is very important to control the relative positions between them. Although there have been many researches on the relative position control, most of them assumes that each satellite use the absolute information about its position and velocity. However, in order to keep the formation strictly and to avoid the collisions, the feedback control with the relative information between the members is effective. In such formation maintenance control, 1) the local control law (control gain, etc.) of each spacecraft and 2) "whose relative information can each spacecraft acquire" (we call this "the information propagation structure") determine the behavior of the formation. Especially, the information propagation structure significantly influences the behavior of the formation. However there are few researches about the information propagation structure. In this study, the information propagation structure of the formation is focused on and how the information propagation structure influences the behavior of the formation is investigated. First, we express the information propagation structure of the formation by a matrix and derive the transfer function matrix of the whole system. Next, from this transfer function matrix, we clarify the relation between the information propagation structure and the stability, the steady-state error and the reactivity of the formation and derive the indexes of these control performances. Finally the method for constructing the information propagation structure by optimizing these indexes is shown.
  • Jun'ichiro Kawaguchi, Takanao Saiki
    European Space Agency, (Special Publication) ESA SP, (548) 417-422, 2004  
    The paper presents how the formation is controlled to the intended shape by a decentralized control. The formation behaviour is dealt via a z-transformation method and a uniformly convergent strategy that each spacecraft performs is proposed. Not only one-dimensional but tow-dimensional examples are shown. Since the strategy is highly flexible, it is applicable to a variety of the formation flying space missions.
  • 日野聡史, 佐伯孝尚
    宇宙科学技術連合講演会講演集, 45th, 2001  
  • 佐伯孝尚
    宇宙科学技術連合講演会講演集, 45th, 2001  

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