2024/10/07 更新

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写真a

バンドウ マイ
坂東 麻衣
BANDO MAI
所属
工学研究院 航空宇宙工学部門 教授
工学部 航空宇宙工学科(併任)
工学府 航空宇宙工学専攻(併任)
マス・フォア・イノベーション連係学府 (併任)
職名
教授
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メールアドレス
プロフィール
軌道力学,アストロダイナミクス,制御工学に関する教育と研究を行っている.特に,力学系理論と制御理論を用いて,理論的な側面から将来の宇宙ミッションに有用な宇宙機の軌道の研究を行っている.
外部リンク

学位

  • 博士(工学)

研究テーマ・研究キーワード

  • 研究テーマ: 非線形力学系のデータ駆動アプローチによる研究

    研究キーワード: データサイエンス、データ駆動、力学系

    研究期間: 2019年4月 - 2020年6月

  • 研究テーマ: 多体力学系における低推力宇宙機の軌道設計

    研究キーワード: アストロダイナミクス,軌道力学,制御工学

    研究期間: 2014年4月

  • 研究テーマ: 制御理論的なアプローチによる宇宙機の軌道力学と軌道設計

    研究キーワード: アストロダイナミクス,軌道力学,制御工学

    研究期間: 2008年4月

  • 研究テーマ: 非線形適応制御理論とUAVへの応用

    研究キーワード: 非線形制御,適応制御,制御理論

    研究期間: 2005年4月 - 2008年3月

受賞

  • Excellent Reviewer for the Journal of Guidance, Control, and Dynamics

    2022年12月  

  • 平成30年度科学技術分野の文部科学大臣表彰 若手科学者賞

    2018年4月   文部科学省   低推力宇宙機の軌道設計の理論的研究

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    「はやぶさ」「はやぶさ2」に搭載されたイオンエンジンに代表される低推力連続加速を行う宇宙機(以下,低推力宇宙機)は高比推力であることからミッションの長寿命化・高精度化に貢献し,今後は深宇宙探査での利用の増加が期待されている.しかし,低推力宇宙機においては,天体の重力の他に常に人工的な推力が加わる運動となるため,これまでの軌道工学の理論を適用することができない.申請者は,制御理論の考え方を軌道力学系のダイナミクスと融合することで,低推力宇宙機が惑星の重力と低推力を効率よく利用するための理論構築に貢献した.

  • 資生堂女性研究者サイエンスグラント

    2017年5月   資生堂   惑星間を自由に行き来できる惑星間ハイウェイの研究

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    「惑星間を自由に行き来できる惑星間ハイウェイの研究」の研究成果により,資生堂株式会社 第10回資生堂女性研究者サイエンスグラントを受賞した。
    「はやぶさ」「はやぶさ2」に搭載されたイオンエンジンに代表される低推力連続加速を行う宇宙機(以下,低推力宇宙機)は高比推力であることからミッションの長寿命化・高精度化に貢献し,今後は深宇宙探査での利用の増加が期待されている.しかし,低推力宇宙機においては,天体の重力の他に常に人工的な推力が加わる運動となるため,これまでの軌道工学の理論を適用することができない.申請者は,最適制御理論の考え方を多体力学系のダイナミクスと融合することで,低推力宇宙機が惑星の重力と低推力を効率よく利用し,惑星間を自由に行き来できる「惑星間ハイウェイ」の考え方を提案した.

  • SI2013優秀講演賞

    2013年12月   計測自動制御学会   講演タイトル「低推力宇宙機の平均的な軌道変化の推定」

  • 宇宙科学奨励賞

    2010年1月   財団法人宇宙科学振興会   惑星間航行・地球周回編隊飛行のための最適軌道制御理論

論文

  • Stable Orbiting around Small Moons using the J2-perturbed Elliptic Restricted Problem 招待 査読 国際誌

    Hongru Chen, Xiyun Hou and Mai Bando

    Journal of Guidance, Control, and Dynamics   2024年4月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

  • 子ども帯同出張のあれこれ

    坂東 麻衣

    日本航空宇宙学会誌   72 ( 1 )   32 - 32   2024年1月   ISSN:00214663 eISSN:24241369

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    記述言語:日本語   出版者・発行元:一般社団法人 日本航空宇宙学会  

    DOI: 10.14822/kjsass.72.1_32

    CiNii Research

  • Trajectory Design in Irregular Gravitational Fields Based on Center Manifold Theory 査読 国際誌

    Naoki Hiraiwa, Mai Bando and Shinji Hokamoto

    Journal of Guidance, Control, and Dynamics   46 ( 8 )   1637 - 1648   2023年8月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

  • TOWARDS STABLE ORBITING AROUND SMALL MOONS USING THE J2-PERTURBED ELLIPTIC-RESTRICTED THREE-BODY PROBLEM

    陳 泓儒, 坂東 麻衣

    2023年8月

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    記述言語:英語   出版者・発行元:American Astronautical Society  

    Confirmed small-body missions such as the MMX and HERA are set to explore Martian moons and the binary asteroid Didymos’ moon, Dimorphos, respectively. The dynamics around these small moons differ substantially from those of previously visited targets. Simplified models, such as the circular-restricted three-body problem, cannot yield accurate predictions for orbits and stability in real-world operations. Orbits near these small moons are significantly perturbed by the planet’s oblateness and their relative positions. The unstable 3:1 resonance around a small moon further complicates orbit maintenance. To minimize perturbation resulting from model mismatch, this research introduces the “J2-ER3BP” model, which incorporates the J2 perturbation of the planet into the elliptic-restricted three-body problem. The approach to computing bounded orbits in this model is explained. Verification using a high-fidelity dynamical model and a realistic control environment suggests that the derived reference proximity orbits around Phobos and Dimorphos can be maintained with small difficulty and cost.

    CiNii Research

  • 確率ノイズを用いた円制限三体問題の大域的な解析

    森光 翔平, 坂東 麻衣, 外本 伸治

    [第33回アストロダイナミクスシンポジウム講演後刷り集]   2023年7月

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    記述言語:英語   出版者・発行元:宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)  

    レポート番号: ASTRO-2023-C002(022)/In-person

    CiNii Research

  • 可変構造宇宙機の関節構造が非ホロノミック拘束を利用した姿勢変化に与える影響

    竹内 咲希, 坂東 麻衣, 外本 伸治

    [第33回アストロダイナミクスシンポジウム講演後刷り集]   2023年7月

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    記述言語:英語   出版者・発行元:宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)  

    レポート番号: ASTRO-2023-C019(031)/In-person

    CiNii Research

  • 二次形式の最適フィードバック制御による人工的な平衡点とその力学構造

    鶴田 彩乃, 坂東 麻衣, シアーズ ダニエル, 外本 伸治

    [第33回アストロダイナミクスシンポジウム講演後刷り集]   2023年7月

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    記述言語:英語   出版者・発行元:宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)  

    レポート番号: ASTRO-2023-C001(010)/In-person

    CiNii Research

  • Lobe dynamicsにもとづくカオス的遷移軌道の設計

    平岩 尚樹, 坂東 麻衣, 外本 伸治

    [第33回アストロダイナミクスシンポジウム講演後刷り集]   2023年7月

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    記述言語:英語   出版者・発行元:宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)  

    レポート番号: ASTRO-2023-A014(018)/In-person

    CiNii Research

  • Halo-to-Halo Low-Thrust Transfer via Successive Convex Optimization with Intermediate Orbit Design 査読 国際誌

    Naoki Hiraiwa, Mai Bando, Shinji Hokamoto

    Journal of Evolving Space Activities   2023年6月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

  • Data-Driven Guidance and Control for Asteroid Landing Based on Real-Time Dynamic Mode Decomposition 査読 国際誌

    Taiga Kajikawa, Tatsuya Shiotsuka, Mai Bando, Shinji Hokamoto

    IEEE Access   2023年6月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

  • Design of Low-Energy Transfer Trajectories from Jupiter to Europa with Ballistic Transfer 査読 国際誌

    Kanta Ikeda, Naoki Hiraiwa, Mai Bando, Shinji Hokamoto

    Journal of Evolving Space Activities   2023年6月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

  • 複眼視覚航法による運動推定精度の改善に向けた実験的研究

    本田 悠樹, 坂東 麻衣, 外本 伸治

    自動制御連合講演会講演論文集   66 ( 0 )   536 - 540   2023年

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    記述言語:日本語   出版者・発行元:自動制御連合講演会  

    DOI: 10.11511/jacc.66.0_536

    CiNii Research

  • マルチローター機のフォーメーションフライトに用いたステレオカメラに関する研究

    倉橋 征椰, 坂東 麻衣, 外本 伸治

    自動制御連合講演会講演論文集   66 ( 0 )   526 - 530   2023年

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    記述言語:日本語   出版者・発行元:自動制御連合講演会  

    DOI: 10.11511/jacc.66.0_526

    CiNii Research

  • Semantic Segmentation Technique to Identify Landing Area for Autonomous Spacecraft

    Gao, X; Bando, M; Hokamoto, S

    PROCEEDINGS OF THE 2021 ASIA-PACIFIC INTERNATIONAL SYMPOSIUM ON AEROSPACE TECHNOLOGY (APISAT 2021), VOL 2   913   897 - 910   2023年   ISSN:1876-1100 ISBN:978-981-19-2634-1 eISSN:1876-1119

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    出版者・発行元:Lecture Notes in Electrical Engineering  

    For deep space landing missions, spacecraft are required to identify their expected landing sites autonomously because of the extremely long time delay caused by the distance between the spacecraft and Earth. This identification process is desirable to finish within several seconds by onboard computers with limited calculation performance. Moreover, autonomous identification based on natural features of landing sites are highly recommended in future missions, although some artificial target markers have been used for navigation and control to the landing site in some previous missions. To make fast but reliable identification of landing sites for the automatic task, this research utilizes a deep learning processing for images taken in different light-conditions and altitudes. First, a semantic segmentation model for rocks in terrain images is developed. For robust identification, some improvements are introduced in the semantic segmentation process. Then, to identify the same place in images taken at different altitudes, a comparison algorithm based on triangular shapes is applied. Thus after training, the semantic segmentation model can detect the same place from several images in a relatively short computational time.

    DOI: 10.1007/978-981-19-2635-8_66

    Web of Science

    Scopus

  • Formation Flying Along Libration Point Orbits Using Chattering Attenuation Sliding Mode Control 招待 査読 国際誌

    Mai Bando, Hamidreza Nemati, Yuki Akiyama, Shinji Hokamoto

    Frontier in Space Technology   2022年7月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

  • Sparse Optimal Control for Nonlinear Trajectory Design in Three-Body Problem 査読 国際誌

    Yuki Kayama, Mai Bando, Shinji Hokamoto

    International Journal of Sustainable Aviation   19 ( 4 )   545 - 552   2022年5月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

  • Sparse Optimal Control for Nonlinear Trajectory Design in Three-Body Problem 招待 査読 国際誌

    Yuki Kayama, Mai Bando, Shinji Hokamoto

    Transactions of the JSASS / Aerospace Technology Japan   19 ( 4 )   545 - 552   2022年5月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

  • PSO Algorithm Parameter Settings and Optimal Multi-rotor Layout Design 招待 査読 国際誌

    Yuke Huang, Tatsuya Watanabe,Mai Bando, Shinji Hokamoto

    International Journal of Sustainable Aviation   8 ( 2 )   116 - 135   2022年4月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

  • Low-Thrust Trajectory Design with Successive Convex Optimization for Libration Point Orbits 招待 査読 国際誌

    Yuki Kayama, Kathleen Howell, Mai Bando,Shinji Hokamoto,

    Journal of Guidance, Control, and Dynamics   45 ( 4 )   623 - 637   2022年4月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

    DOI: 10.2514/1.G005916

  • An Alternative Opportunity of Future Psyche Mission using Differential Evolution and Gravity Assists 招待 査読 国際誌

    Vijil Kumar, Badam Singh Kushvah, Mai Bando

    AIMS Mathematics   7 ( 4 )   7012 - 7025   2022年2月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

    DOI: 10.3934/math.2022390

  • 複眼視覚航法を用いた小型無人航空機での距離・運動推定

    本田 悠樹, 坂東 麻衣, 外本 伸治

    自動制御連合講演会講演論文集   65 ( 0 )   1450 - 1454   2022年

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    記述言語:日本語   出版者・発行元:自動制御連合講演会  

    DOI: 10.11511/jacc.65.0_1450

    CiNii Research

  • ALTITUDE ESTIMATION BY WIDE-FIELD-INTEGRATION OF OPTIC FLOW

    Hiraiwa H., Bando M., Hokamoto S.

    33rd Congress of the International Council of the Aeronautical Sciences, ICAS 2022   8   5643 - 5653   2022年   ISBN:9781713871163

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    出版者・発行元:33rd Congress of the International Council of the Aeronautical Sciences, ICAS 2022  

    In this paper, we propose an altitude estimation method by using Wide-Field-Integration (WFI) of optic flow. WFI of optic flow is a motion estimation method inspired by a biological research on the visual processing system of flying insects' compound eyes. In the standard estimation process, altitude information of a flying vehicle is necessary to estimate the motion variables of flying vehicles. The method proposed in this paper can estimate the altitude as well as the motion variables by using two patterns of optic flow acquired by two onboard cameras. The proposed method is useful for reducing onboard instrument mass and thus suitable for small autonomous vehicles. This paper discusses the mechanism of the altitude estimation and explores the suitable positions of the WFI of optic flow sensors in simulations.

    Scopus

  • Controllability Analysis of Propellant-Free Satellite Formation Flight 招待 査読 国際誌

    Mohamed Shouman,Mai Bando,Shinji Hokamoto

    Journal of Guidance, Control, and Dynamics   44 ( 12 )   2214 - 2224   2021年12月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

    DOI: 10.2514/1.G006035

  • Two-Input-Torque for Hopping Exploration Robot to Enhance Reachability under Microgravity 招待 査読 国際誌

    Yusei Sasaki, Tomohiro Ishizuka, Mai Bando, Shinji Hokamoto

    Transactions of the JSASS / Aerospace Technology Japan   19 ( 5 )   719 - 725   2021年10月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

  • Orbit Maintenance for Quasi-Periodic Orbit in Earth-Moon System 招待 査読 国際誌

    Yang Zhou, Mai Bando, Shinji Hokamoto,Panlong Wu

    Transactions of the JSASS / Aerospace Technology Japan   19 ( 4 )   562 - 569   2021年8月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

  • Nonlinear Model Predictive Detumbling of Small Satellites with a Single-Axis Magnetorquer 招待 査読 国際誌

    Kota Kondo, Ilya Kolmanovsky, Yasuhiro Yoshimura, Mai Bando, Shuji Nagasaki,Toshiya Hanada

    Journal of Guidance, Control, and Dynamics   44 ( 6 )   1211 - 1218   2021年6月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

  • Formation-Flying Trajectory Design Based on Attractive Sets of Tschauner-Hempel Equations 招待 査読 国際誌

    Motoki Yamane,Mai Banado,Shinji Hokamoto

    Journal of Guidance, Control, and Dynamics   43 ( 10 )   1943 - 1951   2020年10月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

    DOI: 10.2514/1.G005046

    リポジトリ公開URL: http://hdl.handle.net/2324/4479056

  • Guidelines for practical navigation systems based on wide-field-integration of optic flow 招待 査読 国際誌

    Naoto Kobayashi, Mai Bando, Shinji Hokamoto, Daisuke Kubo

    Asian Journal of Control   2020年10月

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    記述言語:日本語   掲載種別:研究論文(学術雑誌)  

    DOI: 10.1002/asjc.2363

    リポジトリ公開URL: http://hdl.handle.net/2324/4479598

  • Performance Analysis of Low-Gain Feedback for Saturated Differential Drag in a High-precision Orbit Propagator 招待 査読 国際誌

    Mohamed Shouman, Mai Bando, Shinji Hokamoto

    Transactions of the Japan Society for Aeronautical and Space Sciences   63 ( 5 )   243 - 247   2020年9月

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    記述言語:日本語   掲載種別:研究論文(学術雑誌)  

    DOI: 10.2322/tjsass.63.243

    リポジトリ公開URL: http://hdl.handle.net/2324/4476143

  • Periodic and quasi-periodic orbit design based on the center manifold theory 査読

    Yuki Akiyama, Mai Bando, Shinji Hokamoto

    Acta Astronautica   160   672 - 682   2019年7月

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    記述言語:英語  

    This paper proposes a new numerical method for finding libration point orbits in the vicinity of collinear libration points in the circular restricted three-body problem. The main advantage of this method is that it requires neither an initial guess nor complex algebraic manipulations for finding both quasi-periodic and periodic orbits. The proposed method consists of two steps: center manifold design and differential correction. The first step provides a quasi-periodic orbit parametrized by a single parameter vector. In the second step, the parameter vector in the first step is used to obtain an exact periodic orbit. This method is applied to find periodic and quasi-periodic orbits in the Sun-Earth restricted three-body problem around the L1 and L2 libration points.

    DOI: 10.1016/j.actaastro.2019.02.029

    リポジトリ公開URL: http://hdl.handle.net/2324/4784354

  • Output regulation control for satellite formation flying using differential drag 査読

    Mohamed Shouman, Mai Bando, Shinji Hokamoto

    Journal of Guidance, Control, and Dynamics   42 ( 10 )   2220 - 2232   2019年1月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

    This paper proposes a new approach of using differentials in aerodynamic drag in combination with thrusters to control satellite formation flying in low Earth orbits. Parameterized output regulation theory for formation-flying missions with combined control action is developed based on the Schweighart–Sedwick relative dynamics equations. The theory is implemented to precisely track the different trajectories of reference relative motion and eliminates the effects of the J2 perturbations. The parametric Lyapunov algebraic equation is proposed to ensure the stability of the linear relative model subject to saturated inputs. The main goal of this study is to approve the viability of using the differentials in aerodynamic drag to precisely control different formation-flying missions. Numerical simulations using a high-fidelity relative dynamics model and a high-precision orbit propagator are implemented to validate and analyze the performance of the proposed control algorithm in comparison with the linear quadratic regulator algorithm based on actual satellite models.

    DOI: 10.2514/1.G004219

    リポジトリ公開URL: http://hdl.handle.net/2324/4479055

  • Controller performance for quad-rotor vehicles based on sliding mode control 査読

    Takayoshi Oba, Mai Bando, Shinji Hokamoto

    Journal of Robotics and Mechatronics   30 ( 3 )   397 - 405   2018年6月

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    記述言語:英語  

    This study applies a sliding mode control (SMC) strategy for a robust controller of a quad-rotor vehicle. First, a controller combined with a nested control loop and an SMC is introduced, because a quad-rotor vehicle has only four control inputs although the vehicle has six degrees of freedom. The control performance for the feedback gains in the nested loop is investigated in numerical simulations. Subsequently, the effects of practical system limitations (control cycle and rotor dynamics) on the control performance are examined. Finally, the robust performance of the SMC strategy on a quad-rotor vehicle is discussed.

    DOI: 10.20965/jrm.2018.p0397

  • Nonlinear attractive and reachable sets under optimal control in three-body problem 査読

    Mai Bando, Daniel J. Scheeres

    Journal of Guidance, Control, and Dynamics   41 ( 8 )   1766 - 1775   2018年1月

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    記述言語:英語  

    DOI: 10.2514/1.G003334

    リポジトリ公開URL: http://hdl.handle.net/2324/4479054

  • Tether cutting maneuver in swing-by trajectory 査読

    Tsubasa Yamasaki, Mai Bando, Shinji Hokamoto

    Acta Astronautica   142   212 - 220   2018年1月

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    記述言語:英語  

    The swing-by maneuver is known as a method to change the velocity of a spacecraft by using the gravity force of the celestial body. The powered swing-by has been studied to enhance the velocity change during the swing-by maneuver. This paper studies another way of the powered swing-by using tether cutting, which does not require additional propellant consumption, and shows that the proposed powered swing-by can increase the effect of the swing-by as same as using impulsive thrust. Moreover, it is discussed whether the system has possibility to realize both the powered swing-by of a mother satellite and the planetary capture of a subsatellite simultaneously.

    DOI: 10.1016/j.actaastro.2017.11.002

  • Station-keeping and formation flying based on nonlinear output regulation theory 査読

    Yuki Akiyama, Mai Bando, Shinji Hokamoto

    Acta Astronautica   2018年1月

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    記述言語:英語  

    Station-keeping and formation flying along a libration point orbit in the circular restricted three-body problem are considered. In order to deal with the relative motion with respect to a reference trajectory, this paper extends our previous study which derives the station-keeping controller based on the output regulation theory. First the reference orbit of the chief satellite is represented as the output of an autonomous system called exosystem, assuming the reference orbit is given by a truncated Fourier series. For the formation flying, the relative trajectory of the deputy satellite with respect to the chief satellite is also represented by the output of an exosystem. Then the reference signal to be asymptotically tracked for the formation flying is obtained by the superposition of the two exosystems. The proposed controllers are applied and verified for the station-keeping and formation flying along a periodic orbit of the Sun-Earth L2 point.

    DOI: 10.1016/j.actaastro.2018.02.004

    リポジトリ公開URL: http://hdl.handle.net/2324/4784017

  • Explicit form of station-keeping and formation flying controller for libration point orbits 査読

    Akiyama Yuki, Mai Bando, Shinji Hokamoto

    Journal of Guidance, Control, and Dynamics   41 ( 6 )   1405 - 1413   2018年1月

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    記述言語:英語  

    A new station-keeping strategy based on nonlinear output regulation theory has been proposed for the periodic orbits in the circular restricted three-body problem. A Fourier series approximation was employed to generate the desired orbits, and then the output regulation theory for nonlinear systems was applied. The output regulation problem was solved in an analytical form. The proposed controller has been applied and verified in numerical simulations for the halo orbit of the sun–Earth L2 point. In the case that the reference orbit is the natural periodic orbit, the controller can approximate the optimal controller in the sense of minimizing the station-keeping cost. As an application of the proposed method, formation flying using circular orbits around the chief satellite has been worked out.

    DOI: 10.2514/1.G002845

    リポジトリ公開URL: http://hdl.handle.net/2324/4784365

  • Integrated orbit determination and maintenance in Earth-Moon unstable dynamics environment 査読

    Yang Zhou, Mai Bando, Shinji Hokamoto, Panlong Wu

    Acta Astronautica   163   69 - 76   2018年1月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

    The hyperbolic instability of collinear libration point orbits dominates the distribution of orbit uncertainty, which is closely related with the unstable manifold of the local orbit. Exploiting the distribution of orbit uncertainty in an unstable orbital environment, an integrated orbit determination and maintenance approach is proposed. X-ray pulsar navigation embedded in the Kalman filtering architecture is adopted to determine the orbit of a spacecraft flying along the Earth-Moon L2 halo orbit. To keep the spacecraft in the vicinity of the nominal trajectory, the newly proposed orbit maintenance approach based on the covariance matrix is proposed to design the orbit maintenance maneuver. The numerical simulations show that the proposed approach has a good performance in orbit determination and maintenance.

    DOI: 10.1016/j.actaastro.2018.11.041

    リポジトリ公開URL: http://hdl.handle.net/2324/4784018

  • Chattering Attenuation Sliding Mode Approach for Nonlinear Systems 査読

    Hamidreza Nemati, Mai Bando, Shinji Hokamoto

    Asian Journal of Control   2017年9月

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    記述言語:英語  

    This study introduces a new robust nonlinear control scheme based on the theory of nonsingular terminal sliding mode control (NTSMC). Since conventional NTSMC utilizes a discontinuous switching function, a significant flaw called chattering can occur. The main purpose of this study is to design a new switching function based upon Lyapunov stability in order to alleviate this drawback over time. There are many approaches to mitigate the chattering drawback in SMC such as utilizing a smooth approximation of the switching element, or employing higher order sliding mode control (HOSMC) strategy. However, the use of a continuous approximation affects the system's performance and a finite reaching time to the sliding manifold, and in HOSMC the estimation of high-order derivatives of states is usually difficult and it still exhibits chattering in the presence of parasitic dynamics. In this study by employing a new sliding manifold including a time function, the chattering is attenuated as well as keeping the robustness. Finally, a second-order nonlinear dynamical system subject to disturbance is simulated to highlight the validity and applicability of the proposed method.

    DOI: 10.1002/asjc.1477

    リポジトリ公開URL: http://hdl.handle.net/2324/4479597

  • Improvement of Wide-Field-Integration of Optic Flow Considering Practical Sensor Restrictions 招待 査読 国際誌

    Naoto Kobayashi, Mai Bando, Shinji Hokamoto

    Journal of Mechanical Engineering and Automation   7 ( 2 )   53 - 62   2017年4月

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    記述言語:英語  

    DOI: 10.5923/j.jmea.20170702.04

  • Trajectory Design Using the Center Manifold Theory in the Circular Restricted Three-Body Problem 招待 査読 国際誌

    Yuki Akiyama, Mai Bando, Shinji Hokamoto

    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan   Pd_151 - Pd_158   2016年12月

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    記述言語:英語  

  • Attractive sets to unstable orbits using optimal feedback control 査読

    Mai Bando, Daniel J. Scheeres

    Journal of Guidance, Control, and Dynamics   39 ( 12 )   2725 - 2739   2016年12月

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    記述言語:英語  

    This paper investigates the combination of optimal feedback control with the dynamical structure of the three-body problem. The results provide new insights for the design of continuous low-thrust spacecraft trajectories. Specifically, the attracting set of an equilibrium point or a periodic orbit (represented as a fixed point) under optimal control with quadratic cost is obtained. The analysis reveals the relation between the attractive set and original dynamics. In particular, it is found that the largest dimensions of the set are found along the stable manifold and the least extent is along the left eigenvector of the unstable manifold. The asymptotic behavior of the structure of the attractive set when time tends to infinity is analytically revealed. The results generalize the use of manifolds for transfers to equilibrium points and periodic orbits in astrodynamic problems. The result is theoretical and developed for a linearized system, but it can be extended to nonlinear systems in the future.

    DOI: 10.2514/1.G000524

    リポジトリ公開URL: http://hdl.handle.net/2324/4784356

  • Design of Earth-Moon Cyclers Using Primer Vector Theory 招待 査読 国際誌

    Sho Hayashida, Mai Bando, Shinji Hokamoto

    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan   Pd_159 - Pd_165   2016年12月

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    記述言語:英語  

  • On the possibility of using small asteroids for deflecting near-Earth asteroids 査読

    Yuki Akiyama, Mai Bando, Shinji Hokamoto

    Advances in Space Research   57 ( 8 )   1820 - 1831   2016年4月

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    記述言語:英語  

    This paper presents the trajectory design and analysis of the near-Earth asteroid (NEA) deflection mission enabled by a kinetic impact of an intermediate asteroid. The sequential transfer trajectory is designed by solving two Lambert's problems that yield a chain collision between a spacecraft and an intermediate asteroid, followed by a collision between the intermediate asteroid and an NEA. The characteristics of the low-cost trajectories are then identified with respect to the optimal collision point. We show that the feasibility of the mission depends on the existence of an intermediate asteroid with small minimum orbit interception distance (MOID) with the NEA. Moreover the selection strategy of an intermediate asteroid that makes the mission feasible is discussed. We show that several asteroids exist that allow a 10 ton spacecraft with limited ΔV to be launched and impact the NEA 99442 Apophis allowing a deflection given several years warning time.

    DOI: 10.1016/j.asr.2015.08.016

  • Satellite Formation-keeping about Libration Points in the Presence of System Uncertainties 招待 査読 国際誌

    Mai Bando, Hamidreza Nemati

    Advances in the Astronautical Sciences   156   737 - 756   2015年8月

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    記述言語:英語  

  • 未知の低推力加速運動を行う人工衛星の軌道推定(第2報:接触軌道要素の推定) 招待 査読 国際誌

    伊達直輝, 坂東麻衣, 外本 伸治

    日本機械学会論文集   81 ( 826 )   2015年6月

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    記述言語:日本語   掲載種別:研究論文(学術雑誌)  

    DOI: DliD2rhdIa

  • 未知の低推力加速運動を行う人工衛星の軌道推定(第1報:平均軌道要素の推定) 招待 査読 国際誌

    伊達直輝, 坂東麻衣, 外本 伸治

    日本機械学会論文集   81 ( 826 )   2015年6月

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    記述言語:日本語   掲載種別:研究論文(学術雑誌)  

    DOI: AUJ6UxEFLM

  • Optimal Selection of Impulse Times For Formation Flying 国際誌

    Mai Bando, Akira Ichikawa

    Advances in the Astronautical Sciences   153   861 - 872   2015年1月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)  

  • Formation flying along halo orbit of circular-restricted three-Body problem 査読

    Mai Bando, Akira Ichikawa

    Journal of Guidance, Control, and Dynamics   38 ( 1 )   123 - 129   2015年1月

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    記述言語:英語  

    A new control strategy based on output regulation theory is proposed for formation flying along a halo orbit near a libration point in the circular-restricted three-body problem. The reference orbit is a periodic or shifted perturbation of the halo orbit generated by an exosystem, and modification of linear output regulation theory is employed. First, the station keeping problem is considered, and the total velocity change required for the halo orbit maintenance is found to be negligible. The reasonable size of a perturbation can be determined numerically, and hence the formation flying proposed in this paper is useful for the design of a reference orbit along a halo orbit. The proposed relative orbit and control strategy are independent of halo orbits and can be applied to formation flying along an arbitrary path.

    DOI: 10.2514/1.G000463

  • 円制限三体問題を題材とした航空宇宙工学分野における研究室インターシップ 査読

    Mai Bando, 外本 伸治

    工学教育   62 ( 2 )   73 - 78   2014年3月

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    記述言語:日本語  

  • Formation Flying Along an Elliptic Orbit by Pulse Control 国際誌

    Mai Bando, Akira Ichikawa

    Advances in the Astronautical Sciences   150   1433 - 1446   2014年1月

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    記述言語:英語  

  • In-plane motion control of Hill-Clohessy-Wiltshire equations by single input 査読

    Mai Bando, Akira Ichikawa

    Journal of Guidance, Control, and Dynamics   36 ( 5 )   1512 - 1521   2013年9月

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    記述言語:英語  

    The in-plane motion of the Hill-Clohessy-Wiltshire (HCW) equations is controllable with along-track input but not controllable with crosstrack input. However, in the controllable subspace of the latter, the drift velocity is zero and the free motion is periodic. Thus, formation reconfiguration for the in-plane motion is possible by cross-track input. In the case of the continuous-time feedback controllers, the total velocity change of the along-track controller is larger than that of the two-input controller, but the difference is less than 8% for the settling time larger than five periods. In the case of pulse feedback controllers, the sampling time used for discretization is one-half of the period for the two-input controller and one-quarter of the period for all other single-input controller. The two-input and along-track feedback controllers are robust and effective for the nonlinear relative dynamics.

    DOI: 10.2514/1.57197

  • Formation Flying near the Libration Points by Impulse Control 国際誌

    Mai Bando, Akira Ichikawa

    Advances in the Astronautical Sciences   146   3045 - 3057   2013年9月

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    記述言語:英語  

  • Optimal Trajectory Design for Asteroid Deflection Mission 査読 国際誌

    Mai Bando, Hiroshi Yamakawa

    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan   10 ( ists28 )   2013年1月

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    記述言語:英語  

  • Spacecraft formation flying dynamics and control using the geomagnetic lorentz force 査読

    Shu Tsujii, Mai Bando, Hiroshi Yamakawa

    Journal of Guidance, Control, and Dynamics   36 ( 1 )   136 - 148   2013年1月

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    記述言語:英語  

    The motion of a charged satellite subjected to the Earth's magnetic field is considered. The Lorentz force, which acts on a charged particle when it is moving through a magnetic field, provides a new concept of propellantless electromagnetic propulsion. A dynamic model of a charged satellite, including the effect of the Lorentz force in the vicinity of a circular or an elliptic orbit, is derived and its application to formation flying is considered. Based on Hill-Clohessy-Wiltshire equations and Tschauner-Hempel equations, analytical approximations for the relative motion in Earth orbit are obtained. The analysis based on the linearized equations shows the controllability of the system by stepwise charge control. The sequential quadratic programming method is applied to solve the orbital transfer problem of the original nonlinear equations in which the analytical solutions cannot be obtained.Astrategy to reduce the charge amount using sequential quadratic programming is also developed.

    DOI: 10.2514/1.57060

  • Active formation flying along an elliptic orbit 査読

    Mai Bando, Akira Ichikawa

    Journal of Guidance, Control, and Dynamics   36 ( 1 )   324 - 332   2013年1月

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    記述言語:英語  

    An active formation flying for the Tschauner-Hempel equations (TH) is considered, in which the desired relative orbit of the follower is generated by an exosystem. This allows for flexibility of the shape and period of the reference orbit. The regulator differential equation is solved algebraically, exploiting the special structure of the Tschauner-Hempel equations. Hence, control implementation is straight forward. In the case of active formation, the total velocity change increases with penalty on the input. The settling time is independent of the frequency of the reference orbit. For the Tschauner-Hempel equations, the total velocity change for transition increases with frequency of the reference orbit, but the settling time remains almost constant, as in the circular case. For the eccentricity up to 0.3, the total velocity change for maintenance remains at the same level as in the circular case. Using these relations, feedback controls for active formation with given specifications and constraints can be designed effectively.

    DOI: 10.2514/1.57703

  • 円制限三体問題のラグランジュポイントの安定性に関する陰的制御的考察 査読

    坂東 麻衣, 大須賀公一, 藤井隆雄, 山川 宏

    計測自動制御学会論文集   38 ( 7 )   431 - 440   2012年7月

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    記述言語:日本語  

  • Trajectory Design of DESTINY Mission 査読 国際誌

    Mai Bando, Masaki Nakamiya, Yasuhiro Kawakatsu

    Advances in the Astronautical Sciences   146   321 - 322   2012年5月

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    記述言語:英語  

  • Graphical generation of periodic orbits of tschauner-hempel equations 査読

    Mai Bando, Akira Ichikawa

    Journal of Guidance, Control, and Dynamics   35 ( 3 )   1002 - 1007   2012年5月

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    記述言語:英語  

    Graphical generation of periodic orbits of Tschauner-Hempel (TH) equations is presented. The general solution of the relative dynamics based on the orbital elements is obtained, and the relative motion invariant manifold, where the solution lies, is determined. The region where all periodic solutions lie is determined by two ellipses, whose size depends on the eccentricity of the leader orbit. Size and phase parameters for periodic orbits are introduced for the TH equations, and a simple way to draw a periodic orbit is proposed for a given pair of size and phase parameters and a given initial true anomaly of the elliptic orbit. Results show that the design of a relative orbit with size and position specifications is as simple as in the Hill-Clohessy-Wiltshire (HCW) case.

    DOI: 10.2514/1.56326

  • Attitude dynamics of a pendulum-shaped charged satellite 査読

    Hiroshi Yamakawa, Shinji Hachiyama, Mai Bando

    Acta Astronautica   70   77 - 84   2012年1月

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    記述言語:英語  

    In this paper, we investigate the possibility of the use of the Lorentz force, which acts on charged satellite when it is moving through the magnetic field, as a means of satellite attitude control. We first derive the equations of attitude motion of charged satellite and then investigate the stability of the motion. Finally we propose an attitude control method using the Lorentz force. Our method requires moderate charge level for future Lorentz-augmented satellite.

    DOI: 10.1016/j.actaastro.2011.07.019

  • Optimal pulse strategies for relative orbit transfer along a circular orbit 査読

    Ryo Jifuku, Akira Ichikawa, Mai Bando

    Journal of Guidance, Control, and Dynamics   34 ( 5 )   1329 - 1341   2011年9月

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    記述言語:英語  

    This paperisconcerned withafuel-optimal relative orbit transfer problem for Hill-Clohessy-Wiltshire equations. The input is of the pulse type and the performance index is the total velocity change required for a transfer. For the in-plane motion, the existence of optimal three-pulse strategies is shown and the minimum total velocity change is explicitly given under the condition that the difference of orbit size is relatively larger than that of drift velocity. For the out-of-plane motion, the existence of optimal single-pulse strategies is shown. The orbit transfer problem covers formation reconfiguration problem as a special case. Midpoints of the optimal pulses coincide with those points at which the velocity along the radial direction is zero. Using this information and null controllability with vanishing energy of the Hill-Clohessy-Wiltshire equations, suboptimal feedback controllers are designed. Simulation results with optimal open-loop strategies and feedback controls are given for two formation reconfiguration problems.

    DOI: 10.2514/1.51230

  • Formation Flying Along a Circular Orbit with Control Constraints

    Mai Bando, Akira Ichikawa

    Advances in the Astronautical Sciences   142   1393 - 1406   2011年8月

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    記述言語:英語  

  • Near-Earth asteroid flyby survey mission using solar sailing technology 査読

    Mai Bando, Hiroshi Yamakawa

    Journal of the Astronautical Sciences   58 ( 4 )   569 - 581   2011年1月

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    記述言語:英語  

    The purpose of this paper is to investigate the possibility of on asteroid (NEA) survey mission enabled by advanced solar sailing technology. The study is focused not on the solar sail spacecraft itself but on its orbital dynamics to realize the missions. A novel NEA flyby survey mission with a lightweight solar sail spacecraft to increase the accessibility to NEA flybys located in the vicinity of the Earth's orbit is proposed. A numerical study suggests that our approach increases the opportunities in proximity to NEAs, which have eccentric and inclined orbits.

    DOI: 10.1007/BF03321532

  • Near-Earth Asteroid Survey Mission Concept Using Solar Sailing Technology

    Mai Bando, Hiroshi Yamakawa

    Advances in the Astronautical Sciences   138   257 - 269   2010年7月

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    記述言語:英語  

  • New lambert algorithm using the Hamilton-Jacobi-Bellman equation 査読

    Mai Bando, Hiroshi Yamakawa

    Journal of Guidance, Control, and Dynamics   33 ( 3 )   1000 - 1008   2010年5月

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    記述言語:英語  

    A study was conducted to demonstrate the formulation of the new Lambert Algorithm using the Hamilton-Jacobi-Bellman Equation (HJB). The two-point boundary-value problem (TPBVP) of the Hamiltonian system was treated as an optimal control problem where the Lagrangian function played a role as a performance index. The approach demonstrated in the study was based on the expansion of the value function in the Chebyshev series with unknown coefficients, considering the computational advantages of the use of Chebyshev polynomials. The differential expressions that arose in the HJB equation were expanded in Chebyshev series with the unknown coefficients. The new algorithm had the potential to provide a solution to the TPVBP using the spectral information about the gravitation potential function and was applicable to the problem under a higher-order perturbed potential function without any modification.

    DOI: 10.2514/1.46751

  • Periodic orbits of nonlinear relative dynamics along an eccentric orbit 査読

    Mai Bando, Akira Ichikawa

    Journal of Guidance, Control, and Dynamics   33 ( 2 )   385 - 395   2010年3月

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    記述言語:英語  

    This paper is concerned with formation acquisition and reconfiguration problems with an eccentric reference orbit. As a first step, the characterization problem is considered for all initial conditions that constitute periodic solutions of the nonlinear equations of relative motion. Under the condition that the inertial orbits of the leader and a follower are coplanar, initial conditions of all periodic relative orbits are generated in terms of parameters of their orbits and their initial positions. Then the inertial orbit of the follower is rotated successively around the two axes of its perifocal reference system, and the initial conditions of all noncoplanar relative orbits are derived. Based on these periodic relative orbits, formation acquisition and reconfiguration problems by a feedback controller are formulated. The main performance index of a feedback controller is the total velocity change during the operation. Using the property of null controllability with vanishing energy of the Tschauner-Hempel equations, suboptimal controllers are designed via the differential Riccati equation of the linear regulator theory of periodic systems.

    DOI: 10.2514/1.46024

  • Satellite formation and reconfiguration with restricted control interval 査読

    Mai Bando, Akira Ichikawa

    Journal of Guidance, Control, and Dynamics   33 ( 2 )   607 - 615   2010年3月

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    記述言語:英語  

    A new formulation of formation flying in an elliptic orbit with restricted control interval is discussed. The main performance index is the L1 norm of the control input generated by an employed feedback control, which is proportional to the fuel consumption. The null controllability with vanishing energy (NCVE) property enables to design feedback controllers through the linear quadratic regulator (LQR) theory, which generate control inputs with arbitrarily small L2 norms by imposing a large penalty on control. The L1 norm of the control input decreases monotonically as the penalty on control increases, and suboptimal controllers are designed. The velocity of the satellite near the apogee is smaller, a relatively small velocity change is required for orbit control and it is assumed that t = 0 is the perigee passage time of the leader, and restrict the control input to the interval.

    DOI: 10.2514/1.46139

  • Solution to Lambert's Problem Using Generalized Canonical Transformations 査読

    Mai Bando, Hiroshi Yamakawa

    Advances in the Astronautical Sciences   136   587 - 603   2010年2月

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    記述言語:英語  

  • Orbital Design for Multiple Flyby Missions 査読

    Mai Bando, Hiroshi Yamakawa

    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan   8 ( ists27 )   2010年1月

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    記述言語:英語  

  • From Elliptic Restricted Three-Body Problem to Tschauner-Hempel Equations:A Control Strategy Based on Circular Problems

    Mai Bando, Akira Ichikawa

    Advances in the Astronautical Sciences   135   301 - 313   2009年8月

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    記述言語:英語  

  • Periodic orbits of nonlinear relative dynamics and satellite formation 査読

    Mai Bando, Akira Ichikawa

    Journal of Guidance, Control, and Dynamics   32 ( 4 )   1200 - 1208   2009年7月

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    記述言語:英語  

    In this paper, leader-follower formation and reconfiguration problems based on the periodic orbits of the nonlinear relative dynamics along a circular orbit are considered. First, initial conditions of coplanar and noncoplanar relative orbits are characterized by the initial true anomaly, mean motion, semimajor axis, eccentricity, and inclination angle of the follower's inertial orbit. Based on the property of null controllability with vanishing energy of the Hill-Clohessy-Wiltshire equations, L1 suboptimal feedback controllers are designed via the linear quadratic regulator theory. Simulation results for three examples are given. A comparison with the reconfiguration problem based on the periodic orbits of the Hill-Clohessy-Wiltshire equations shows that replacement by nonlinear periodic orbits does not increase the L 1-norm of the feedback control.

    DOI: 10.2514/1.41438

    リポジトリ公開URL: http://hdl.handle.net/2324/4476142

  • A New Optimal Orbit Control for Two-Point Boundary-Value Problem Using Generating Functions

    Mai Bando, Hiroshi Yamakawa

    Advances in the Astronautical Sciences   134   245 - 260   2009年2月

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    記述言語:英語  

    リポジトリ公開URL: http://hdl.handle.net/2324/4479053

  • Adaptive Regulation of Nonlinear Systems by Output Feedback

    Mai Bando, Akira Ichikawa

    Journal of Robotics and Mechatronics   20 ( 5 )   2008年9月

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    記述言語:英語  

  • A Stable Approach for Modular Learning and Its Application to Autonomous Aero-Robot

    Mai Bando, Hiroaki Nakanishi

    Journal of Robotics and Mechatronics   18 ( 1 )   44 - 50   2006年1月

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    記述言語:英語  

▼全件表示

書籍等出版物

  • 人類が生きる場所としての宇宙 (シリーズ〈宇宙総合学〉 1)

    磯部 洋明 (著), 土井 隆雄 (著), 坂東 麻衣 (著), 柴田 一成 (著), 石原 昭彦 (著), 伊勢田 哲治 (著), 小山 勝二 (著), 寺田 昌弘 (著), 京都大学宇宙総合学研究ユニット (編集)(担当:共著)

    2020年6月 

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    記述言語:日本語  

講演・口頭発表等

  • Data-Driven Modeling for Multirotor Autonomous Control 国際会議

    Tatsuya Shiotuska,Mai Bando, Shinji Hokamoto

    AIAA SciTech 2024  2024年1月 

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    開催年月日: 2024年1月

    記述言語:英語   会議種別:口頭発表(一般)  

    国名:アメリカ合衆国  

  • Data-Driven Orbital Control in Perturbed Environment 国際会議

    Komsun Tamanakijprasart,Mai Bando,Shinji Hokamoto

    SICE Annual Conference 2022  2023年9月 

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    開催年月日: 2023年9月 - 2022年9月

    記述言語:英語  

    開催地:Kumamoto   国名:日本国  

  • Stabilization of Spacecraft in Spatial Periodic Orbits using Linear Quadratic Regulator (LQR) 国際会議

    Nishanth Pushparaj, Yuta Hayashi, Mai Bando

    The 34th International Symposium on Space Technology and Science  2023年6月 

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    開催年月日: 2023年6月

    記述言語:英語  

    国名:日本国  

  • A New Gravitational Wave Observatory Formation Configuration Design and Control Method 国際会議

    Zhengxu Pan, Mai Bando, Zhanxia Zhu and Shinji Hokamoto

    The 34th International Symposium on Space Technology and Science  2023年6月 

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    開催年月日: 2023年6月

    記述言語:英語  

    国名:日本国  

  • Discrete-Time Attitude Control for Spacecraft Using Iterative Learning 国際会議

    Yuta Hayashi, Mai Bando, Shinji Hokamoto

    The 34th International Symposium on Space Technology and Science  2023年6月 

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    開催年月日: 2023年6月

    記述言語:英語  

    国名:日本国  

  • Trajectory Design by Stochastic Gradient Descent Algorithm Adam 国際会議

    Shodai Hirayama, Naoki Hiraiwa, Mai Bando, Shinji Hokamoto

    The 34th International Symposium on Space Technology and Science  2023年6月 

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    開催年月日: 2023年6月

    記述言語:英語  

    国名:日本国  

  • New Equilibria in Quadratic Optimal Control Systems 国際会議

    Ayano Tsuruta, Mai Bando, Daniel J. Scheeres, Shinji Hokamoto

    The 34th International Symposium on Space Technology and Science  2023年6月 

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    開催年月日: 2023年6月

    記述言語:英語  

    国名:日本国  

  • Optimization of Structural Configurations of Spacecraft for Efficient Attitude Change Utilizing Non-holonomic Features 国際会議

    Saki Takeuchi, Mai Bando, Shinji Hokamoto

    The 34th International Symposium on Space Technology and Science  2023年6月 

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    開催年月日: 2023年6月

    記述言語:英語  

    国名:日本国  

  • New Trends in Celestial Mechanics and Dynamical Astronomy 国際会議

    Mai Bando

    International Workshop on Celestial Mechanics and Dynamical Astronomy (IWCMDA-2023)  2023年1月 

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    開催年月日: 2023年1月

    記述言語:英語   会議種別:口頭発表(招待・特別)  

    国名:インド  

  • An Improved YOLO for Tiny Rocks Detection in Spacecraft Autonomous Landing Xi Chen, Mai Bando, Shinji Hokamoto 国際会議

    Xi Chen, Mai Bando, Shinji Hokamoto

    2022 Asia-Pacific International Symposium on Aerospace Technology (APISAT2022)  2022年10月 

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    開催年月日: 2022年10月

    記述言語:英語  

    国名:日本国  

  • Design of Optimal Low-Thrust Orbit-to-Orbit Transfers via Convex Approach 国際会議

    Naoki Hiraiwa, Mai Bando, Shinji Hokamoto

    73rd International Astronautical Congress,  2022年9月 

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    開催年月日: 2022年9月

    記述言語:英語  

    国名:フランス共和国  

  • Data-Driven Guidance for Asteroid Landing Based on Real-Time Dynamic Mode Decomposition 国際会議

    Taiga Kajikawa, Mai Bando, Shinji Hokamoto

    73rd International Astronautical Congress,  2022年9月 

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    開催年月日: 2022年9月

    記述言語:英語  

    国名:フランス共和国  

  • Design of Satellites Tours Using Periapsis Poincar\'{e} Map in Multibody Dynamics of Jovian System 国際会議

    Kanta Ikeda, Naoki Hiraiwa, Mai Bando, Shinji Hokamoto

    73rd International Astronautical Congress,  2022年9月 

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    開催年月日: 2022年9月

    記述言語:英語  

    国名:フランス共和国  

  • A Data-Driven Nonlinear Optimal Control Using Koopman Operator on Hamiltonian Flow 国際会議

    Kyosuke Sato, Mai Bando, Shinji Hokamoto

    73rd International Astronautical Congress,  2022年9月 

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    開催年月日: 2022年9月

    記述言語:英語  

    国名:フランス共和国  

  • Altitude Estimation by Wide-Field-Integration Optic Flow 国際会議

    Hiromitsu Hiraiwa, Mai Bando, Shinji Hokamoto,

    33rd Congress of the International Council of the Aeronautical Sciences  2022年9月 

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    開催年月日: 2022年9月

    記述言語:英語  

    国名:スウェーデン王国  

  • Influence of Overall Layout Design of Compound Multi-Rotor Vehicles on Flight Performance 国際会議

    Yuke Huang, Mai Bando, Shinji Hokamoto

    33rd Congress of the International Council of the Aeronautical Sciences  2022年9月 

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    開催年月日: 2022年9月

    記述言語:英語  

    国名:スウェーデン王国  

  • Robust Nonlinear Optimal Control Using Koopman Operator Theory 国際会議

    Erica L. Jenson,Mai Bando,Kyosuke Sato, Daniel J. Scheeres

    2022 AAS/AIAA Astrodynamics Specialist Conference  2022年8月 

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    開催年月日: 2022年8月

    記述言語:英語  

    国名:アメリカ合衆国  

  • Effects of Rotational Joint Directions of Variable Structure on Non-holonomic Features 国際会議

    Saki Takeuchi, Kanta Ikeda, Mai Bando, Shinji Hokamoto

    The 33rd International Symposium on Space Technology and Science  2022年2月 

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    開催年月日: 2022年2月

    記述言語:英語  

    国名:日本国  

  • Design of low energy transfer trajectories from Earth to Europa with ballistic capture 国際会議

    Kanta Ikeda, Naoki Hiraiwa, Mai Bando, Shinji Hokamoto

    The 33rd International Symposium on Space Technology and Science  2022年2月 

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    開催年月日: 2022年2月

    記述言語:英語   会議種別:口頭発表(一般)  

    国名:日本国  

  • Halo-to-Halo Low-Thrust Transfer via Successive Convex Optimization with Intermediate Orbit Design

    Naoki Hiraiwa, Mai Bando, Shinji Hokamoto

    The 33rd International Symposium on Space Technology and Science  2022年2月 

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    開催年月日: 2022年2月

    記述言語:英語  

    国名:日本国  

  • Spacecraft Trajectory Design Using Data-Driven Model Predictive Control

    Yuto Hirose, Mai Bando, Shinji Hokamoto

    72nd International Astronautical Congress  2021年10月 

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    開催年月日: 2021年10月

    記述言語:英語  

    国名:日本国  

  • Analysis of Ballistic Escape Based on Lobe Dynamics 国際会議

    Naoki Hiraiwa, Mai Bando, Shinji Hokamoto

    72nd International Astronautical Congress  2021年10月 

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    開催年月日: 2021年10月

    記述言語:英語  

    国名:日本国  

  • Multirotor Vehicles Design Based on Dynamic Manipulability for Underactuated Flying Systems 国際会議

    Yoshiki Matsumura, Mai Bando, Shinji Hokamoto

    32nd Congress of the International Council of the Aeronautical Sciences  2021年9月 

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    開催年月日: 2021年9月

    記述言語:英語  

    国名:日本国  

  • A Data-Driven Nonlinear Optimal Control of Unstable Fixed Points

    Kyosuke Sato, Mai Bando and Shinji Hokamoto

    2021 AAS/AIAA Astrodynamics Specialist Conference  2021年8月 

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    開催年月日: 2021年8月

    記述言語:英語  

    国名:日本国  

  • Data-Driven Analysis of Chaotic Orbits in the Circular Restricted Three Body Problem 国際会議

    Taiki Urashi, Mai Bando and Shinji Hokamoto

    2021 AAS/AIAA Astrodynamics Specialist Conference  2021年8月 

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    開催年月日: 2021年8月

    記述言語:英語   会議種別:口頭発表(一般)  

    国名:その他  

  • Optimal Layout Design of Multi-Rotor Vehicle Based on PSO Algorithm 国際会議

    Yuke Huang, Mai Bando, Shinji Hokamoto,

    International Symposium on Aircraft Technology 2021  2021年6月 

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    開催年月日: 2021年6月

    記述言語:日本語   会議種別:口頭発表(一般)  

    国名:日本国  

  • Global Optimization of Manifold-Based Transfers to Halo and Butterfly Orbits Using Highly-Parallel GPU Architecture

    Foo Yang, Hideaki Ogaawa, Satoshi Ueda and Mai Bando

    31st AAS/AIAA Space Flight Mechanics Meeting  2021年2月 

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    開催年月日: 2021年2月

    記述言語:日本語  

    国名:その他  

  • Application of Halo Orbit on Extension for Launch Window limited by Direct Earth-Mars Transfer

    Zhe Xu, Mai Bando, Hideaki Ogawa and Shinji Hokamoto

    31st AAS/AIAA Space Flight Mechanics Meeting  2021年2月 

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    開催年月日: 2021年2月

    記述言語:日本語  

    国名:その他  

  • Low Thrust Trajectory Design with Convex Optimization for Libration Point Orbits

    Yuki Kayama, Kathleen C. Howell, Mai Bando and Shinji Hokamoto

    31st AAS/AIAA Space Flight Mechanics Meeting  2021年2月 

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    開催年月日: 2021年2月

    記述言語:日本語  

    国名:その他  

  • Trajectory Design to Mars from Earth-Moon System with Three-dimensional Transit Orbits

    Noma Wataru, Zhe Xu, Mai Bando and Shinji Hokamoto,

    71st International Astronautical Congress (IAC 2020)  2020年10月 

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    開催年月日: 2020年10月

    記述言語:日本語  

    国名:その他  

  • Three-Dimensional Attitude Control of Spacecraft by Three Thrusters

    Yusei Sasaki, Mai Bando and Shinji Hokamoto

    71st International Astronautical Congress (IAC 2020),  2020年10月 

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    開催年月日: 2020年10月

    記述言語:日本語  

    国名:その他  

    リポジトリ公開URL: http://hdl.handle.net/2324/4479733

  • Formation Control Using Differential Atmospheric Drag Considering Attitude Constraints

    Takehiro Yasuda, Mai Bando and Shinji Hokamoto

    71st International Astronautical Congress (IAC 2020)  2020年10月 

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    開催年月日: 2020年10月

    記述言語:日本語  

    国名:その他  

  • Cycler Orbit Design Using Low-thrust in the Sun-Earth-Moon system

    Miyahara Keitaro, Yuki Kayama, Mai Bando, Shinji Hokamoto

    71st International Astronautical Congress (IAC 2020),  2020年10月 

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    開催年月日: 2020年10月

    記述言語:日本語  

    国名:その他  

  • Optimal Landing Problem for a Binary Asteroid System and Its Error Sensitivity

    Anviksha Sharma, Mai Bando, Shinji Hokamoto and Daniel Scheeres

    59th Annual Conference of the Society of Instrument and Control Engineers of Japan, SICE 2020  2020年9月 

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    開催年月日: 2020年9月

    記述言語:日本語  

    国名:その他  

  • Trajectory design in the vicinity of 65803 Didymos based on the center manifold theory

    Naoki Hiraiwa, Mai Bando and Shinji Hokamoto

    2020 AAS/AIAA Astrodynamics Specialist Conference  2020年8月 

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    開催年月日: 2020年8月

    記述言語:日本語  

    国名:その他  

  • Minimum Fuel Trajectory Design Using Sparse Optimal Control in Three-Body Problem

    Yuki Kayama, Mai Bando and Shinji Hokamoto

    2020 AIAA SciTech Forum,  2020年1月 

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    開催年月日: 2020年1月

    記述言語:日本語  

    国名:アメリカ合衆国  

  • Detumbling of Small Satellites with Only a Single-Axis Magnetorquer

    Kota Kondo, Yasuhiro Yoshimura, Mai Bando, Shuji Nagasaki and Toshiya Hanada

    2020 AIAA SciTech Forum  2020年1月 

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    開催年月日: 2020年1月

    記述言語:日本語  

    国名:日本国  

  • Riemannian optimization for spacecraft trajectory design

    Kyosuke Asaki, Mai Bando, Shinji Hokamoto

    70th International Astronautical Congress, IAC 2019  2019年10月 

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    開催年月日: 2019年10月

    記述言語:英語  

    開催地:Washington   国名:アメリカ合衆国  

    Many of the equations of motion appearing in the aerospace field are nonlinear, and the problem of input optimization under this equation of motion is important. There are two methods for solving the nonlinear optimal control problem: direct method and indirect method. In the direct method, the equation of motion is discretized, and the problem is solved as a nonlinear programming problem with motion equations as constraints. In the direct method, it is possible to solve the problem by adding various constraints, but the solution becomes complicated and it is difficult to guarantee the convergence to the optimal solution. In this study, we consider a set of unknowns that satisfy constraints as Riemannian manifolds, and treat the problem as an unconstrained optimization problem on Riemannian manifolds. A simplified rocket trajectory optimization problem illustrates the proposed method.

  • Manifold-based robust stationkeeping of libration-point orbit with navigational uncertainty

    Y. Zhou, M. Bando, S. Hokamoto, P. L. Wu

    70th International Astronautical Congress, IAC 2019  2019年10月 

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    開催年月日: 2019年10月

    記述言語:英語  

    開催地:Washington   国名:アメリカ合衆国  

    This paper investigated the manifold-based robust stationkeeping approach for the halo orbit near the Earth-Moon L2 point in the ephemeris model. The well-known Hamiltonian structure-preserved (HSP) method is utilized to design the controller for stationkeeping. However, conventional HSP method is proposed under the ideal condition, where the equations of motion are constructed in the circular restricted three-body problem, and the navigational uncertainty is not considered as well. Actually, these uncertainties always exist and have significant influence on the performance of stationkeeping. To make the results more realistic, the dynamics in the ephemeris model is used to describe the motion of a spacecraft. A filtering structure-based navigation is incorporated in the stationkeeping, where the navigational uncertainty is introduced. In addition, the navigation filter is reformed to compensate for the control uncertainty. Simulation is performed to observe the influence of the control gain and the magnitude of the uncertainty on the stationkeeping performance.

  • Manifold-to-manifold transfers using low-thrust acceleration

    Yuri Hachiya, Yuki Kayama, Mai Bando, Shinji Hokamoto

    70th International Astronautical Congress, IAC 2019  2019年10月 

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    開催年月日: 2019年10月

    記述言語:英語  

    開催地:Washington   国名:アメリカ合衆国  

    This paper considers manifold-to-manifold transfers in the circular-restricted three-body problem enabled by low-thrust acceleration where an initial and target states lie on invariant manifolds associated to libration point orbits with different Jacobi constant. The basic idea is to utilize a family of stable and center manifolds that lie arbitrarily close to the target invariant manifold to reduce the cost of transfer. The linear quadratic regulator is used to design feedback control to transfer to the target manifold. Time invariant and time periodic controlleres are derived based on the linearized motion around the equilibrium point and periodic orbit respectively. The results show that the feedback controller can shape the linearized motion around manifold to be that around the equilibrium point or a periodic orbit. As a demonstration, transfer trajectories are designed to target the unstable manifold associated with an unstable Lyapunov orbit in the Earth-Moon system.

  • Station-keeping of Unstable Orbits Based on Sparse Optimal Control

    Yuki Kayama, Mai Bando and Shinji Hokamoto

    58th Annual Conference of the Society of Instrument and Control Engineers of Japan, SICE 2019  2019年9月 

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    開催年月日: 2019年9月

    記述言語:日本語  

    国名:日本国  

  • Orbit maintenance for quasi periodic orbits in Earth-Moon system

    Yang Zhou, Mai Bando, Shinji Hokamoto and Panlong Wu

    32nd International Symposium on Space Technology and Science (ISTS)  2019年6月 

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    開催年月日: 2019年6月

    記述言語:日本語  

    国名:日本国  

  • Reachability of Hopping Exploration Robot to a Destination Point Under Microgravity 国際会議

    Yusei Sasaki, Tomohiro Ishizuka, Mai Bando and Shinji Hokamoto

    32nd International Symposium on Space Technology and Science (ISTS)  2019年6月 

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    開催年月日: 2019年6月

    記述言語:日本語  

    国名:日本国  

  • Direct Method of Optimal Trajectory Design in Three-Body Problem

    Yuki Kayama, Mai Bando and Shinji Hokamoto

    32nd International Symposium on Space Technology and Science (ISTS)  2019年6月 

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    開催年月日: 2019年6月

    記述言語:日本語  

    国名:日本国  

  • Performance Analysis of Formation Flying Using Differential Aerodynamic Drag

    Shouman Mohamed, Mai Bando and Shinji Hokamoto

    32nd International Symposium on Space Technology and Science (ISTS)  2019年6月 

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    開催年月日: 2019年6月

    記述言語:日本語  

    国名:日本国  

  • Trajectory design in the circular restricted three-body problem using artificial invariant manifolds

    Yuki Oshima, Mai Bando, Shinji Hokamoto

    29th AAS/AIAA Space Flight Mechanics Meeting, 2019  2019年1月 

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    開催年月日: 2019年1月

    記述言語:英語  

    開催地:Maui   国名:アメリカ合衆国  

    This paper generalizes the invariant manifolds of unstable libration point orbits through the application of continuous thrust. Considering Jacobi constant of the end of invariant manifolds, an artificial periodic orbit around a libration point realizes heteroclinic connections between itself and an unforced periodic orbit with same Jacobi constant of the end of invariant manifolds. Heteroclinic connections between libration point orbits are constructed by detecting intersections of states of manifolds on the Poincaré map. We reveal low-energy spacecraft can transfer to some periodic orbits with different Jacobi constant. In addition, this paper defines New Jacobi constant of low-thrust spacecraft. By utilizing new Jacobi constant, we illustrate zero-velocity curves of low-thrust spacecraft and reveal that there is a crack of zero-velocity curves and spacecraft can pass the crack.

  • Controllability analysis of propellant-free satellite formation flight

    Mohamed Shouman, Mai Bando, Shinji Hokamoto

    29th AAS/AIAA Space Flight Mechanics Meeting, 2019  2019年1月 

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    開催年月日: 2019年1月

    記述言語:英語  

    開催地:Maui   国名:アメリカ合衆国  

    This paper proposes the controllability analysis of relative motion using different configurations for hybrid control actions of space environmental forces. It tends to present a minimal configuration for the missions exploiting these forces. It illustrates the constraints in each space environmental force and analyzes the integration between these forces to achieve full controllability of the satellite formation flight for near-circular low earth orbits with different orbit configurations. The paper implements a Kalman decomposition approach to decompose the system into controllable and uncontrollable subspaces for linear time-invariant control actions. Numerical simulations are investigated to study the controllability analysis for nonlinear models and substantiate the success of the controllability study for all hybrid control actions with different orbit configurations.

  • Output regulation control for satellite formation flying using differential drag

    Mohamed Shouman, Mai Bando, Shinji Hokamoto

    29th AAS/AIAA Space Flight Mechanics Meeting, 2019  2019年1月 

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    開催年月日: 2019年1月

    記述言語:英語  

    開催地:Maui   国名:アメリカ合衆国  

    This paper proposes a new hybrid control action of differentials aerodynamic drag and thrusters to control satellite formation flying in low Earth orbits. Parameterized output regulation algorithm for formation flying missions is developed based on the Schweighart-Sedwick relative dynamics equations. It is implemented to precisely track the different trajectories of reference relative motion and eliminates the effects of the J2 perturbations. Parametric Lyapunov algebraic equation is derived to ensure the stability of the linear relative model subject to saturated inputs. The main goal of this study is to approve the viability of using the differentials in aerodynamic drag to precisely control different formation flying missions. Numerical simulations using a high fidelity relative dynamics model are implemented to analyze the performance of the proposed control algorithm in comparison with the linear quadratic regulator algorithm for actual satellite parameters. The paper exploits a high-precision orbit propagator model to verify the robustness of the control algorithm.

  • Sparse optimal trajectory design in three-body problem

    Yuki Kayama, Mai Bando, Shinji Hokamoto

    29th AAS/AIAA Space Flight Mechanics Meeting, 2019  2019年1月 

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    開催年月日: 2019年1月

    記述言語:英語  

    開催地:Maui   国名:アメリカ合衆国  

    A structure of the optimal trajectory for minimizing fuel consumption in an unstable dynamical environment such as the three-body problem is not well studied. Recently, it has been found that a sparse solution structure appears in the optimal control of a dynamical system. The concept of sparsity explains the property that the minimum fuel trajectory corresponds to the trajectory which minimizes the total thrusting time. In this paper, we propose a numerical method to obtain the minimum fuel sparse optimal trajectory in the unstable dynamical system. As an example, proposed methods are applied to the transfer in the Sun-Earth system.

  • Optimal trajectory design for safety rendezvous based on sparse modeling

    Satoshi Nagashima, Mai Bando, Shinji Hokamoto

    69th International Astronautical Congress: #InvolvingEveryone, IAC 2018  2018年10月 

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    開催年月日: 2018年10月

    記述言語:英語  

    開催地:Bremen   国名:ドイツ連邦共和国  

    In trajectory design of a spacecraft, reducing the fuel consumption is important factor. In order to find the minimum fuel trajectory, this paper considers the L 1 norm as the performance index. This paper discuss design parameters characterizing the L 1 optimal trajectory, such as sampling time, flight time and magnitude of thrust. Also, this paper compare with the conventional method from the viewpoint of fuel consumption. In addition, this paper consider the rendezvous problem considering safety.

  • Extended state space approach for trajectory design in elliptic restricted three-body problem

    Yuki Akiyama, Mai Bando, Shinji Hokamoto

    69th International Astronautical Congress: #InvolvingEveryone, IAC 2018  2018年10月 

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    開催年月日: 2018年10月

    記述言語:英語  

    開催地:Bremen   国名:ドイツ連邦共和国  

    This paper presents novel methods to provide libration point orbits (LPOs) and invariant manifolds (IMs) associated with libration point orbits in the elliptic restricted three-body problem (ERTBP). First, we introduce an extended autonomous system to describe the ERTBP. By introducing an autonomous system which generates a periodic function and integrating it with the ERTBP which is non-autonomous, we can obtain the extended autonomous system. Then, the center manifold design method which can uniquely provide an LPO in the circular restricted three-body problem is applied to the ERTBP. Next, we present a design method for IMs in the ERTBP by using the local stability characteristics obtained by the state transition matrix along LPOs of the extended system. The proposed design methods are applied and verified for the Earth-Moon L 1 ERTBP. We show various LPOs in the ERTBP by changing design parameters, and IMs associated with a libration point and an LPO.

  • Optimal control of spacecraft attitude motion using Port-Hamiltonian systems

    Tomoya Sakamoto, Mai Bando, Shinji Hokamoto

    69th International Astronautical Congress: #InvolvingEveryone, IAC 2018  2018年10月 

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    開催年月日: 2018年10月

    記述言語:英語  

    開催地:Bremen   国名:ドイツ連邦共和国  

    In this study, a concept of optimality is introduced into Port-Hamilton systems for attitude control of spacecraft. Port-Hamiltonian systems make it possible to design asymptotically stable controllers in a uniform procedure for a wide variety of physical systems. By introducing optimality to Port-Hamilton system, conventional error systems of Port-Hamilton systems are expanded to minimize a quadratic form of evaluation function. In this study, as an optimal control method of Port-Hamiltonian system, Hamilton-Jacobi-Bellman (HJB) equation is considered. Since solving HJB equation is not easy, the equation is simplified through generalized canonical transformation, which is a unique conversion of Port-Hamiltonian system. Furthermore, by considering the minimum evaluation function as a Hamiltonian transformed through the generalized canonical transformation, the analytical solution of the HJB equation can be derived. This method can be used for a time-varying error system and applied for tracking control of spacecraft to specified trajectories. The optimality of the control input obtained from the proposed procedure is verified in numerical simulations.

  • Influence of unstable dynamics on orbit determination with x-ray pulsar navigation

    Yang Zhou, Mai Bando, Shinji Hokamoto, Panlong Wu

    4th IAA Conference on Dynamics and Control of Space Systems, DYCOSS 2018  2018年5月 

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    開催年月日: 2018年5月

    記述言語:英語  

    開催地:Changsha   国名:中華人民共和国  

    This paper explores the influence of unstable dynamics on orbit determination. A halo orbit about the Earth-Moon L2 is considered to be the nominal orbit and the dynamics model is constructed based on the Earth-Moon circular restricted three body problem. X-ray pulsar navigation method is introduced for orbit determination that is performed by Kalman filter. Simulation results show that unstable manifold of halo orbit dominates the growth of orbit-determination error and the corresponding uncertainty. However, when the orbit-determination measurements are incorporated in, the results change and are greatly influenced by the characteristic of the X-ray pulse measurements.

  • Trajectory design to triangular libration points based on resonant orbits

    Nobuki Yamaguchi, Mai Bando, Shinji Hokamoto

    68th International Astronautical Congress: Unlocking Imagination, Fostering Innovation and Strengthening Security, IAC 2017  2017年9月 

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    開催年月日: 2017年9月

    記述言語:英語  

    開催地:Adelaide   国名:オーストラリア連邦  

    In this paper, we extend the flow function method for finding resonant orbits. The relation between flow function, resonance number and order of the resonant orbit are revealed. The resonant orbits design in the Sun-Earth CRTBP are demonstrated and the results show that the resonant orbits can be found globally and systematically by the flow function method. The flow function method can also be applied to obtain higher order resonant orbits. As an application, we propose a transfer trajectory to the L4/L5 SPOs by using various resonant orbits. Our results reveals that two types of insertion is possible for SPO insertion with small ΔV.

  • Optic flow-based navigation system for planetary rovers

    Naoto Kobayashi, Mai Bando, Shinji Hokamoto

    68th International Astronautical Congress: Unlocking Imagination, Fostering Innovation and Strengthening Security, IAC 2017  2017年9月 

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    開催年月日: 2017年9月

    記述言語:英語  

    開催地:Adelaide   国名:オーストラリア連邦  

    This paper proposes a novel optic flow-based navigation system for planetary rovers. Optic flow is a vector field of relative velocities between the camera mounted on a rover and environments, and it is often utilized for motion estimations or relative distance estimations. However, only either one of them can be estimated in general optic flow processing. The method proposed in this paper enables both of the estimations by utilizing an image segmentation technique in computer vision and applying Wide-Field-Integration (WFI) of optic flow for robust estimations. Thus, both obstacle avoidance and avoidance of getting stuck, which are key technologies for planetary exploration rovers, are realized in the method. Furthermore, since the estimation is accomplished in linear processing, a real-time estimation is possible by onboard computers. The effectiveness of the proposed method is examined through numerical simulations, considering sensor noises and the shape of obstacles.

  • Quaternion based attitude stabilization in the circular restricted three-body problem

    Yuki Akiyama, Mai Bando, Shinji Hokamoto

    68th International Astronautical Congress: Unlocking Imagination, Fostering Innovation and Strengthening Security, IAC 2017  2017年9月 

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    開催年月日: 2017年9月

    記述言語:英語  

    開催地:Adelaide   国名:オーストラリア連邦  

    This paper presents a novel method to realize station-keeping and control attitude motion simultaneously on a libration point orbit based on the nonlinear output regulation. First, the coupled orbit-attitude motion of a rigid spacecraft subject to three-body dynamics is formulated using the quaternion. Next, the reference orbit and attitude are represented as the output of an autonomous system called exosystem, assuming the reference orbit and attitude are given by a truncated Fourier series. Then the controller is derived by solving the output regulation problem. The derived controller has the explicit form and can achieve the asymptotically tracking for any reference orbit and attitude represented in the Fourier series. The proposed controllers are applied and verified for the Sun-pointing attitude control and station-keeping along Sun-Earth L2 Halo orbits.

  • Formation flying along elliptical orbit using attractive sets of optimal control

    Motoki Yamane, Mai Bando, Shinji Hokamoto

    68th International Astronautical Congress: Unlocking Imagination, Fostering Innovation and Strengthening Security, IAC 2017  2017年9月 

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    開催年月日: 2017年9月

    記述言語:英語  

    開催地:Adelaide   国名:オーストラリア連邦  

    This paper proposes a new method of optimal trajectory design for formation flying along an elliptical orbit. Under linearized assumptions and a quadratic performance index, the optimal cost is quadratic in the initial state. Attractive sets of optimal control are defined as contours of the optimal cost based on linear quadratic regulator theory. It describes a set of all initial states to reach a desired state by a given cost. By solving the optimal control problem for TH equations, the optimal cost is obtained as a time-periodic function. This paper develops the attractive set for a time-periodic system and procedure to draw the attractive set is shown. The advantage of using attractive sets for optimal trajectory design is that it can determine the optimal initial state immediately. The various shape of the periodic orbit and the attractive sets are demonstrated by weight parameters of optimal control theory.

  • Considerations on design parameters for attitude control of spacecraft using port-controlled Hamiltonian systems

    Tomoya Sakamoto, Yuki Akiyama, Mai Bando, Shinji Hokamoto

    56th Annual Conference of the Society of Instrument and Control Engineers of Japan, SICE 2017  2017年11月 

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    開催年月日: 2017年9月

    記述言語:英語  

    開催地:Kanazawa   国名:日本国  

    In previous research, a controller design procedure via generalized canonical transformations has been proposed to keep the passivity feature of Port-controlled Hamiltonian systems. The procedure has a general form and is applicable to spacecraft's attitude motion described with quaternion parameters. This paper investigates the roles of several design parameters in the generalized canonical transformations. Special attention is placed on the relation between the shape of Lyapunov functions and the convergence speed of the state variables. Furthermore, from the analysis utilizing the linearized form of the Port-controlled Hamiltonian system, the guideline to decide the preferable ratio between two parameters in the design procedure is proposed.

  • Station-keeping and formation flying based on Nonlinear Output Regulation Theory 国際会議

    #Yuki Akiyama,@Mai Bando,@Shinji Hokamoto,

    9th International Workshop on Satellite Constellations and Formation Flying (IWSCFF)  2017年6月 

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    開催年月日: 2017年6月

    記述言語:英語  

    開催地:Boulder   国名:アメリカ合衆国  

  • Optimal Trajectory Design of Formation Flying based on Attractive sets 国際会議

    #Motoki Yamane,@Mai Bando,@Shinji Hokamoto,

    31st International Symposium on Space Technology and Science (ISTS),  2017年6月 

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    開催年月日: 2017年6月

    記述言語:英語   会議種別:口頭発表(一般)  

    開催地:Matsuyama   国名:日本国  

  • Dynamic Locomotion of a Multi-Legged Planetary Exploration Rover with Isotropic Leg Arrangement 国際会議

    #Tomohito Sekiguchi,#Saki Omi,@Mai Bando,@Shinji Hokamoto,

    31st International Symposium on Space Technology and Science (ISTS),  2017年6月 

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    開催年月日: 2017年6月

    記述言語:英語   会議種別:口頭発表(一般)  

    開催地:Matsuyama   国名:日本国  

  • Powered swing-by using tether cutting

    Tsubasa Yamasaki, Mai Bando, Shinji Hokamoto

    67th International Astronautical Congress, IAC 2016  2016年9月 

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    開催年月日: 2016年9月

    記述言語:英語  

    開催地:Guadalajara   国名:メキシコ合衆国  

    The swing-by maneuver is known as a method to change the velocity of a spacecraft by using the gravity force of the celestial body. The powered swing-by has been proposed and researched to enhance the velocity change during the swing-by maneuver, e.g. Prado (1996). The research reports that applying an impulse maneuver at periapsis maximizes the additional effect to the swing-by. However, such impulsive force requires additional propellant. On the other hand, Williams et al. (2003) researched to use a tether cutting maneuver for a planetary capture technique. This current paper studies another way of the powered swing-by using tether cutting, which does not require additional propellant consumption. A Tethered-satellite is composed of a mother satellite, a subsatellite and a tether connecting two satellites. In a swing-by trajectory, a gravity gradient force varies according to the position of the tethered-satellite, and consequently its attitude motion is induced; the tethered-satellite starts to liberate and rotate. Cutting the tether during the tethered-satellites' rotation can add the rotational energy into the orbital energy. In this research, since the gravity gradient effect on orbital motion is small, the orbit can be considered a hyperbolic orbit. Assuming that the tether length is constant, Eq. (1) describes the equation of the attitude motion of a tethered-satellite within the SOI (sphere of influence) of the secondary body. θ = 1/1+ e cos α {2e (θ' + 1) sin α - 3/2 sin 2θ} where e is an orbit eccentricity, α is a true anomaly, θ is an attitude angle and l is tether length. The prime means the derivative with α. The mother satellite and subsatellite can obtain not only the velocity change but the position change by the tether cutting; they are denoted as Δv and Δr, and described in Eqs. (2) and (3), respectively. Δv = -l1(α + θ) [-sin (α + θ) cos (α + θ)] Δr = -l1 [cos (α + θ) sin (α + θ)] where l1 is a distance between the center of gravity of the tethered-satellite and the mother satellite. Since α and θ are functions of time, Δv and Δr are also functions of time. This means that changing the tether cutting point can maximize the velocity change in this proposed powered swing-by maneuver. Furthermore, the optimum cutting point depends on the attitude and angular velocity when the tethered satellite enters the SOI. We propose a systematic design procedure to obtain the desired velocity change by optimizing the cutting point, the initial attitude and the initial angular velocity of the tethered satellites.

  • Periodic orbits design based on the center manifold theory in the circular restricted three-body problem

    Yuki Akiyama, Mai Bando, Shinji Hokamoto

    67th International Astronautical Congress, IAC 2016  2016年9月 

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    開催年月日: 2016年9月

    記述言語:英語  

    開催地:Guadalajara   国名:メキシコ合衆国  

    Invariant manifolds such as stable and unstable manifolds are often used in trajectory designs in the circular restricted three-body problem (CRTBP). Focusing on center manifolds, this paper proposes a simple but powerful trajectory design method for a periodic orbit based on the center manifold theorem. In general, there exist three types of invariant manifolds around equilibrium points: stable, unstable and center manifolds. The trajectories on center manifolds are bounded, whereas those on stable or unstable manifolds exponentially approach or diverge from the libration point as time passes. Hence, periodic orbits can be considered as systems lying on center manifolds. A general system around an equilibrium point is given by (Equation presented) where f, g and h are nonlinear terms and all real-parts of eigenvalues of matrices C, P and Q are zero, negative and positive, respectively. According to the center manifold theorem, in the neighborhood of the equilibrium point, the system (1) can be represented by (Equation presented) The first ordinary differential equation is called reduced order system. The solution to Eq. (2) represents solutions restricted on center manifolds. Based on Eq. (2), we propose a novel method to obtain periodic orbit. It includes two steps. The first step computes approximate solutions for the system shown as Eq. (2) in the CRTBP. This step requires iteration by using a successive approximation method proposed by Suzuki et al., which requires initial values of the reduced order system, ξ ∈ R 4 . Note that since in the first step quasi-periodic orbits are obtained, a further modification of ξ is necessary to obtain pure periodic orbits. The second step corrects ξ to form a periodic orbit. The required variation Δξ are computed by using the state transition matrix. The remarkable feature of the proposed method is that once we fix three components of ξ, the method provides the initial state for a periodic orbit uniquely by successive iteration mentioned above. Note that two of them become zero from symmetries of periodic orbits and the rest can be set arbitrarily. Contrary to the proposed method, conventional methods such as the differential correction method and the Lindstedt-Poincaré method require good initial guesses and complex algebraic manipulations. The proposed method is applicable to any equilibrium point, although as an example the proposed method is applied to the Sun-Earth L 2 point and verified in numerical simulation. In conclusion, we reveal that the proposed method is a very powerful tool and can significantly reduce efforts to obtain periodic orbits.

  • Nonlinear attractive sets under optimal feedback control in the hill three-body problem

    Mai Bando, Daniel J. Scheeres

    AIAA/AAS Astrodynamics Specialist Conference, 2016  2016年9月 

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    開催年月日: 2016年9月

    記述言語:英語  

    開催地:Long Beach   国名:アメリカ合衆国  

    Trajectory design combining low-thrust and the three-body problem is a challenging area for study. This paper investigates the combination of optimal feedback control with the dynamical structure of the three-body problem. For the nonlinear system, the attractive set of an equilibrium point or a periodic orbit under optimal control is described by the Hamilton-Jacobi-Bellman partial differential equation. We obtain the solution to the Hamilton-Jacobi-Bellman equation by solving the truncation problem successively.

  • Attractive set of optimal feedback control for the hill three-body problem

    Mai Bando, Daniel J. Scheeres

    26th AAS/AIAA Space Flight Mechanics Meeting, 2016  2016年2月 

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    開催年月日: 2016年2月

    記述言語:英語  

    開催地:Napa   国名:アメリカ合衆国  

    This paper investigates the combination of optimal feedback control with the dynamical structure of the three-body problem. The results provide new insights for the design of continuous low-thrust spacecraft trajectories. Specifically, we solve for the attracting set of an equilibrium point under optimal control with quadratic cost. The analysis reveals the relation between the attractive set and original dynamics. In particular, we find that the asymptotic form of the attractive set to an equilibrium point or a fixed point under optimal control is completely defined by its left unstable eigenvectors and a term inversely proportional to its unstable eigenvalue.

  • Design of sliding mode controllers for formation flying along unstable periodic orbits in CR3BP

    Hamidreza Nemati, Mai Bando, Shinji Hokamoto

    66th International Astronautical Congress 2015: Space - The Gateway for Mankind's Future, IAC 2015  2015年 

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    開催年月日: 2015年10月

    記述言語:英語  

    開催地:Jerusalem   国名:イスラエル国  

    This paper studies a control law to stabilize the orbital motion in the vicinity of an unstable equilibrium point and periodic orbits in the circular-restricted three-body problem (CR3BP). Since the libration point orbits especially around collinear points are highly unstable, time-delay in sensor and/or acutor might cause instability. In this paper, we derive a continuous sliding mode controller (Cont. SMC) to achieve robust fuel-efficient periodic motion based upon a new Lyapunov function to smooth the control input. Then, the total velocity change is investigated to reach and maintain a halo orbit in the Sun-Earth CR3BP. Simulation results show that the proposed Cont. SMC has good performance and robustness in the presence of unmodeled time-delay.

  • Satellite formation-keeping about libration points in the presence of system uncertainties

    Mai Bando, Hamidreza Nemati, Shinji Hokamoto

    AAS/AIAA Astrodynamics Specialist Conference, ASC 2015  2016年 

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    開催年月日: 2015年8月

    記述言語:英語  

    開催地:Vail   国名:アメリカ合衆国  

    This paper studies a control law to stabilize the orbital motion in the vicinity of an unstable equilibrium points and periodic orbits in the circular-restricted three-body problem. Utilizing the eigenstructure of the system, the fuel efficient formation flying controller via linear quadratic regulator (LQR) is developed. Then the chattering attenuation sliding mode controller (CASMC) is designed and analyzed for the in-plane motion of the circular circular-restricted three-body problem. Simulation studies are conducted for the Sun-Earth L2 point and a halo orbit around it. The total velocity change required to reach the halo orbit as well as to maintain the halo orbit is calculated. Simulation results show that the chattering attenuation sliding mode controller has good performance and robustness in the presence of unmodeled nonlinearity along the halo orbit with relatively small fuel consumption.

  • Estimation of mean orbital elements with unknown low-thrust acceleration

    Mai Bando, Naoki Date, Shinji Hokamoto

    65th International Astronautical Congress 2014: Our World Needs Space, IAC 2014  2014年 

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    開催年月日: 2014年9月 - 2014年10月

    記述言語:英語  

    開催地:Toronto   国名:カナダ  

    Space Situational Awareness (SSA) has been recognized to be important for the safe space activities including these problems. As low-thrust propulsion technology becomes increasingly popular, SSA for low-thrust spacecraft may become an area of increasing interest. More frequently use of low-thrust propulsion to place satellites in orbit create more opportunities for collisions and radio frequency interference as these spacecraft travel slowly through altitude ranges. The purpose of this paper is to develop a method for estimation of the mean orbital elements for low-thrust spacecraft. To overcome the instability of the estimation problem with low-thrust acceleration, we estimate the mean elements instead of osculating elements. By use of the averaging technique, Hudson and Scheeres (2009) proposed an analytical model of secular variations of orbital elements under thrust acceleration. The resulting averaged equation has a nice property in which only finite number of Fourier coefficients of the thrust acceleration appear because of the orthogonality of the trigonometric function. Based on the nonlinear state equation representation for the extended state variable which include not only orbital elements but also unknown Fourier coefficients, mean orbital elements and thrust history are estimated from observation data of mean orbital elements. Moreover, the mapping from mean to osculating elements is derived which can be replaced by a measurement equation. Proposed method is demonstrated through numerical simulations

  • Wide-field-integration of optic flow for realistic estimation system for space probes

    Shinji Hokamoto, Masataka Oishi, Naoto Kobayashi, Mai Bando

    65th International Astronautical Congress 2014: Our World Needs Space, IAC 2014  2014年 

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    開催年月日: 2014年9月 - 2014年10月

    記述言語:英語  

    開催地:Toronto   国名:カナダ  

    This study discusses the condition of Wide-Field-Integration (WFI) of optic flow to make it as a realistic guidance and navigation system for space probes. WFI of optic flow is a bio-inspired navigation system mimicking visual processing system of flying insects using their compound eyes. However, in a real system, photoreceptors on a spherical surface used in WFI of optic flow are replaced by pixels on flat image surfaces of cameras, and the camera's field of view is limited. This paper examines the effect of the realistic restrictions for WFI of optic flows on the estimation performance in numerical simulations. The estimation accuracy is evaluated for several parameters: the field of view and the resolution of a camera, which is used instead of photoreceptors. Effects of space probe motion and sensor noises are also evaluated. It is shown that a camera with a wider field of view shows better accuracy, when the total number of pixels (or photoreceptors) is same.

  • Optimal selection of impulse times for formation flying

    Mai Bando, Akira Ichikawa

    2nd International Academy of Astronautics Conference on Dynamics and Control of Space Systems, DyCoSS 2014  2015年 

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    開催年月日: 2014年3月

    記述言語:英語  

    開催地:Rome   国名:イタリア共和国  

    In this paper, leader-follower formation flying problems based on the periodic orbits of the Hill-Clohessy-Wiltshire equations and Tschauner-Hempel equations are considered. the control input is assumed to be impulsive. For a given final relative orbit, the admissible controls are feedback controls such that the follower tracks the final orbit asymptotically. The main performance index is the ΔV which is proportional to the fuel consumption. The number of impulses is fixed, but the impulse time is arbitrary and varied. The optimal location of impulse times is sought numerically. Simulation results for a reconfiguration problem are given.

  • Robust deflection strategies of Near Earth asteroids under uncertainties

    Mai Bando, Yuki Akiyama, Shinji Hokamoto

    24th AAS/AIAA Space Flight Mechanics Meeting, 2014  2014年 

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    開催年月日: 2014年1月

    記述言語:英語  

    開催地:Mexico   国名:アメリカ合衆国  

    In this paper, an approach to optimize deflection mission of Near Earth asteroids under uncertainty is proposed based on control theoretical framework. By using the nonlinear mapping from initial deviation to the final deviation, the performance index J which is expressed as a function of the distance of the Earth in the Earth's closest approach time is minimized for the worst case initial condition. We also formulate the robust orbital transfer problem of kinetic impactor spacecraft where the initial state estimation error exists.

  • Active formation along a circular orbit by pulse control

    Mai Bando, Akira Ichikawa

    2013 52nd Annual Conference of the Society of Instrument and Control Engineers of Japan, SICE 2013  2013年 

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    開催年月日: 2013年9月

    記述言語:英語  

    開催地:Nagoya   国名:日本国  

    The relative motion of a follower satellite with respect to the leader in a given circular orbit is described by autonomous nonlinear differential equations. The linearized equations around the null solution are known as Hill- Clohessy-Wiltshire (HCW) equations. In this paper, active formation flying for the HCW system with pulse (impulse) control input is considered, where the desired relative orbit of the follower is generated by an exosystem. This allows for flexibility of the shape and period of the reference orbit. The output regulation theory for discrete linear system is employed. To show the effectiveness of this approach, numerical examples are given.

  • Proposal of buckling-type-driving-unit for rover on small gravity asteroid

    K. Osuka, H. Mochiyama, K. Tadakuma, Mai Bando, K. Ohgata

    2013 52nd Annual Conference of the Society of Instrument and Control Engineers of Japan, SICE 2013  2013年 

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    開催年月日: 2013年9月

    記述言語:英語  

    開催地:Nagoya   国名:日本国  

    In this note, we propose a new driving unit for a rover on small gravity asteroid MINERVA-II. MINERVA-II will be carried by Hayabusa-2 which will be carried by H-IIA rocket launched in 2014. In designing the rover, the most difficult point is lack of information of the target asteroid. To overcome this diffilulty, we propose a kind of passive type driving system. Concretely, we try to apply buckling phenomenon and use spring. As the result, very simple driving unit for unknown field will be developed.

  • Formation flying along an elliptic orbit by pulse control

    Mai Bando, Akira Ichikawa

    2013 AAS/AIAA Astrodynamics Specialist Conference, Astrodynamics 2013  2014年 

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    開催年月日: 2013年8月

    記述言語:英語  

    開催地:Hilton Head Island, SC   国名:アメリカ合衆国  

    The linearized equations of relative motion of a follower satellite with respect to the leader in a given elliptic orbit are described by Tschauner-Hempel (TH) equations. In this paper, formation flying for the TH system with pulse control input is considered. First, the reconfiguration problem where the desired relative orbit of the follower is natural periodic orbit. Next, the active formation problem where the desired relative orbit is generated by an exosystem is considered. This allows for flexibility of the shape and period of the reference orbit. To realize such a formation flying, the output regulation theory for linear periodic systems is employed. To achieve asymptotic tracking, stabilizing feedback controls are designed by the periodic solution of discrete-time Riccati equation of the linear quadratic regulator (LQR) theory.

  • Trajectory design of destiny mission

    Mai Bando, Masaki Nakamiya, Yasuhiro Kawakatsu, Chikako Hirose, Takayuki Yamamoto

    13th International Space Conference of Pacific-Basin Societies, ISCOPS 2012  2013年4月 

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    開催年月日: 2012年5月

    記述言語:英語  

    開催地:Kyoto   国名:日本国  

    The trajectory design of the interplanetary mission "Demonstration and Experiment of Space Technology for INterplanetary voYage, DESTINY" is discussed. The trajectory optimization of low-thrust spacecraft pose a difficult design challenge. Moreover, DESTINY mission requires many constraints for the orbital design. In advance of optimizing the whole transfer mission, we investigated the basic theory to design which can take into account such constraints.

  • On the optimality of plug-in optimal control systems

    Takao Fujii, Koichi Osuka, Mai Bando

    2012 International MultiConference of Engineers and Computer Scientists, IMECS 2012  2012年 

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    開催年月日: 2012年3月

    記述言語:英語  

    開催地:Kowloon  

    We consider a plug-in control system via a concept of Implicit and Explicit Controls as the two stage controllers. We first show two conditions under which the plug-in control system can be optimized by a suitable design of explicit control in the 2nd stage, when an implicit control is given in the 1st stage. We then show another condition under which the resultant optimal cost can be minimized by a suitable design of the Is' stage implicit control, which is characterized as a feedback control that allocates all the closed-loop poles onto the imaginary axis. These two results clarify the system theoretic meaning of the implicit control from the viewpoint of inverse optimal control problem.

  • On optimality and integrity of plug-in optimal control

    Koichi Osuka, Takao Fujii, Mai Bando

    50th Annual Conference on Society of Instrument and Control Engineers, SICE 2011  2011年 

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    開催年月日: 2011年9月

    記述言語:英語  

    開催地:Tokyo   国名:日本国  

    In this note, we consider a plug-in control system via a concept of Implicit Control and Explicit Control. We show that the plug-in control system can be optimized by a certain plug-in control law. And also we show that a property of integrity can be embedded in the optimal plug-in control system.

  • Orbital maintenance for observation mission of peanut-shaped asteroid

    Mai Bando, Koichi Osuka, Takao Fujii, Hiroshi Yamakawa

    50th Annual Conference on Society of Instrument and Control Engineers, SICE 2011  2011年 

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    開催年月日: 2011年9月

    記述言語:英語  

    開催地:Tokyo   国名:日本国  

    In this paper, we consider the motion control of spacecraft in the vicinity of the peanut-shaped asteroid. The implicit control concept is studied and orbital maintenance strategy to observe the peanut-shaped asteroid where the model of the gravity field is difficult to obtain is proposed. The implicit control law is characterized in terms of inverse problem of optimal control.

  • Formation flying along a circular orbit with control constraints

    Mai Bando, Akira Ichikawa

    2011 AAS/AIAA Astrodynamics Specialist Conference, ASTRODYNAMICS 2011  2012年 

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    開催年月日: 2011年7月 - 2011年8月

    記述言語:英語  

    開催地:Girdwood, AK   国名:アメリカ合衆国  

    In this paper, leader-follower formation flying problems based on the periodic orbits of the Hill-Clohessy-Wiltshire equations are considered. For a given final relative orbit, the admissible controls are feedback controls such that the follower tracks the final orbit asymptotically. The main performance index is the L1-norm of the control input which is proportional to the fuel consumption. The L-norm, which gives the magnitude of the input, is an additional performance index under the thruster level limitation. Feedback controls are designed via two algebraic Riccati equations with parameters, and their L1- and L- norms are given as functions of the parameters. Suboptimal controls are designed by choosing appropriate parameters. Simulation results for a reconfiguration problem are given to demonstrate the effectiveness of the design method.

  • Application of global solution of Hamilton-Jacobi equations to optimal low-thrust multiple rendezvous problem

    Mai Bando, Hiroshi Yamakawa

    61st International Astronautical Congress 2010, IAC 2010  2010年 

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    開催年月日: 2010年9月 - 2010年10月

    記述言語:英語  

    開催地:Prague   国名:チェコ共和国  

    This paper presents a procedure to design multiple rendezvous missions. We propose a new low-thrust trajectory optimization method to find the optimal trajectory in analytical form. The resulting control law is a feedback control, so that it is effective in overcoming sensitivities to small variations in initial orbit and thrust profile. This study determines the optimal approach to find an effective control law to sequential transfer problem. For comparison, optimal sequence using impulsive and continuous thrust method are investigated. Our approaches are illustrated through the trajectory design of the multiple flyby mission and resulting fuel costs are compared.

  • Atitude dynamics of a pendulum-shaped charged satellite

    Hiroshi Yamakawa, S. Hachiyama, Mai Bando

    61st International Astronautical Congress 2010, IAC 2010  2010年 

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    開催年月日: 2010年9月 - 2010年10月

    記述言語:英語  

    開催地:Prague   国名:チェコ共和国  

    Orbiting artificial satellites naturally tend to accumulate electrostatic charge which may in some circumstances cause malfunctions in measuring instruments and other devices on the satellite body and ultimately lead to difficulties in satellite operation. In this paper, we investigate the possibility of the use of the Lorentz force, which acts on charged satellite when it is moving through the magnetic field, as a means of satellite attitude control. We first analyze the stability of the motion and then propose novel attitude control method using the Lorentz force.

  • Active formation along an eccentric orbit

    Mai Bando, Akira Ichikawa

    18th IFAC Symposium on Automatic Control in Aerospace, ACA 2010  2010年1月 

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    開催年月日: 2010年9月

    記述言語:英語  

    開催地:Nara   国名:日本国  

    In this paper, a formation problem of a spacecraft with a leader in an elliptic orbit is considered, where the follower is required to track asymptotically a given periodic relative orbit. The linearized equations of relative motion along an eccentric orbit are known as Tschauner-Hempel equations. The Tschauner-Hempel equations are transformed into simpler ones by the change of variables. For the transformed system, the active formation problem is formulated, and feedback controllers are designed by the regulator equations associated with the Hill-Clohessy-Wiltshire equations. Feedback controllers are also designed using a DRE associated with the TH equations, and the Li-norms of designed controllers are compared.

  • Gravity-coulomb force combined three-body problem

    Hiroshi Yamakawa, Mai Bando

    18th IFAC Symposium on Automatic Control in Aerospace, ACA 2010  2010年1月 

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    開催年月日: 2010年9月

    記述言語:英語  

    開催地:Nara   国名:日本国  

    The aim of this paper is to investigate the dynamics of a restricted three-body problem governed by two types of forces: gravity force and Coulomb force. The electrostatic charging and hence the Coulomb force is introduced in order to change the relative position by positive control of the charge amount without using fuel expenditure.

  • Low-thrust trajectory optimization using second-order generating functions

    Mai Bando, Hiroshi Yamakawa

    SICE Annual Conference 2010, SICE 2010  2010年 

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    開催年月日: 2010年8月

    記述言語:英語  

    開催地:Taipei   国名:台湾  

    The optimal control problem of a spacecraft using continuous thrust where the terminal state and time interval are explicitly given is considered. We consider a new robust controller to the spacecraft rendezvous problem. Optimal rendezvous problem using continuous low-thrust is treated as optimal control problem and H control. Using the property that both problems can be treated as two-point boundary value problem (TPVBP) of Hamiltonian system, we formulate the linear quadratic control with worst case disturbance rejection and worst case initial condition related by generating functions. Numerical simulations are given to illustrate the theory.

  • Spacecraft relative dynamics under the influence of geomagnetic lorentz force

    Hiroshi Yamakawa, Mai Bando, Katsuyuki Yano, Shu Tsujii

    AIAA/AAS Astrodynamics Specialist Conference 2010  2010年12月 

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    開催年月日: 2010年8月

    記述言語:英語  

    開催地:Toronto, ON   国名:カナダ  

    The motion of a charged satellite subjected to the Earth's magnetic field is considered. Lorentz force, which acts on charged particle when it is moving through the magnetic field, provides a new concepts of propellant-less electromagnetic propulsion. We derive a dynamical model of a charged spacecraft including the effect of Lorentz force in the vicinity of circular and elliptic orbit and consider its application to formation flight. Based on Hill-Clohessy-Wiltshire equations and Tschauner-Hempel equations, analytical approximations for the relative motion in Earth orbit are obtained. The analysis based on linearized equations in the equatorial case show that the stability of the periodic solutions. Numerical simulations revealed that the periodic solutions which are useful for the formation are obtained for both circular and elliptic reference orbits.The control strategy for the propellantless rendezvous and reconfiguration are developed.

  • Formation flying along a circular orbit with pulse control

    Mai Bando, Akira Ichikawa

    AIAA/AAS Astrodynamics Specialist Conference 2010  2010年 

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    開催年月日: 2010年8月

    記述言語:英語  

    開催地:Toronto, ON   国名:カナダ  

    This paper is concerned with formation flying along a circular orbit. The control input is of pulse type and the performance index is the total velocity change required for formation acquisition. For the in-plane motion, optimal three-pulse strategies which use control acceleration only in the flight direction are given under the condition that the difference of orbit size is relatively larger than that of drift velocity. If the inputs are restricted to the radial direction, only formation reconfiguration is possible and optimal two-pulse strategies are given. For the out-of-plane motion, the existence of optimal single pulse strategies is shown. Formation flying with feedback control is also considered. For the in-plane motion, suboptimal feedback controllers are designed with the help of null controllability with vanishing energy of the Hill-Clohessy-Wiltshire equations. Feedback controls restricted to flight direction are also designed, and the total velocity changes are compared with those of full control. Simulation results for a formation reconfiguration problem are given both for optimal open loop strategies and feedback controls.

  • Near-Earth asteroid survey mission concept using solar sailing technology

    Mai Bando, Hiroshi Yamakawa

    12th International Conference of Pacific-Basin Societies, ISCOPS  2010年 

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    開催年月日: 2010年7月

    記述言語:英語  

    開催地:Montreal, QC   国名:カナダ  

    The purpose of this paper is to investigate the possibility of asteroid survey mission enabled by advanced solar sailing technology. The study is focused not on the solar sail spacecraft itself but on its orbital dynamics to realize the missions. A novel NEA flyby survey mission with a light-weight solar sail spacecraft to increase the accessibility to NEAs located in the vicinity of the Earth's orbit is proposed. Numerical study suggests that our approach increase the opportunities in proximity to NEAs which have eccentric and inclined orbits.

  • Solution to lambert's problem using generalized canonical transformations

    Mai Bando, Hiroshi Yamakawa

    AAS/AIAA Space Flight Mechanics Meeting  2010年 

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    開催年月日: 2010年2月

    記述言語:英語  

    開催地:San Diego, CA   国名:アメリカ合衆国  

    In this paper, we consider the canonical transformations and its applications appearing in astrodynamic problems. First we address stabilization of relative motion via generalized canonical transformation and passivity-based control. Then we propose a method to solve Lambert's problem based on the Hamilton-Jacobi-Bellman (HJB) equation in optimal control theory. Using the generalized canonical transformation, we transform the performance index to positive- definite one and then solve the optimal control problem. We also apply our method to obtain solution to two-point boundary-value problem by the generating function. As an application of the generating functions approach, we consider the problem of multiple flyby mission with impulsive thrust.

  • Satellite formation with restricted control interval

    A. Ichikawa, Mai Bando

    2009 7th Asian Control Conference, ASCC 2009  2009年 

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    開催年月日: 2009年8月

    記述言語:英語  

    開催地:Hong Kong   国名:中華人民共和国  

    In this paper, a formation problem of a satellite with a leader in an eccentric orbit is considered, where the transition to a periodic relative orbit is required, and the control input is restricted to a subinterval of the period of the leader's orbit. As preliminaries, the same problem in the special case of the circular orbit is considered, and feedback controls based on a differential Riccati equation with a periodic control matrix are designed. The performance index is the L1-norm of the feedback control, and suboptimal controls are obtained by virtue of the null controllability with vanishing energy of the controlled system. Then the original problem is transformed into a special form by the change of variables, and using the structure of the resulting system, feedback controls are designed based on those of the circular problem.

  • From elliptic restricted three-body problem to Tschauner-Hempel equations A control strategy based on circular problems

    Mai Bando, Akira Ichikawa

    AAS/AIAA Astrodynamics Specialist Conference  2010年 

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    開催年月日: 2009年8月

    記述言語:英語  

    開催地:Pittsburgh, PA   国名:アメリカ合衆国  

    This paper considers halo orbit control for the Earth-moon elliptic restricted threebody problem. Expressing equations of motion with true anomaly, Lagrangian points are defined and a halo orbit control problem at the L 2 point is discussed. By the change of control variables, constant feedback controllers are designed which maintain a halo orbit of the circular restricted problem. Considering equations of motion relative to the moon, and letting the mass of the moon go to zero, the equations of relative motion along an eccentric orbit are derived. Then formation and reconfiguration problems are formulated, and feedback controllers, based on the Hill-Clohessy-Wiltshire systems, are designed from the point of view of L1-norm minimization.

  • A new optimal orbit control for two-point boundary-value problem using generating functions

    Mai Bando, Hiroshi Yamakawa

    19th AAS/AIAA Space Flight Mechanics Meeting  2009年 

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    開催年月日: 2009年2月

    記述言語:英語  

    開催地:Savannah, GA   国名:アメリカ合衆国  

    The optimal control problem of a spacecraft using impulsive and continuous thrust where the terminal state and time interval are explicitly given is considered. Using a recently developed technique based on Hamilton-Jacobi theory, we develop a method to approximate the solution of the Hamilton-Jacobi equation which can solve the two-point boundary-value problem. The proposed method is based on the successive approximation and Galerkin spectral method with Chebyshev polynomials. This approach is expected to derive the analytical solution of the optimal control problem in the large domain. Numerical simulation is given to illustrate the theory.

  • Adaptive output regulation of nonlinear systems described by multiple linear models

    Mai Bando, Akira Ichikawa

    9th IFAC Workshop "Adaptation and Learning in Control and Signal Processing", ALCOSP'2007  2007年12月 

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    開催年月日: 2007年8月

    記述言語:英語  

    開催地:Saint Petersburg   国名:ロシア連邦  

    In this paper the output regulation problem for nonlinear systems described by multiple linear models with unknown parameters is considered. Based on the Lyapunov stability theory, an adaptive controller which stabilize the system is derived. Then sufficient conditions for the output regulation problem with full information to be solvable are established. Simulation results are given to illustrate the theory.

  • Adaptive output regulation for linear systems

    Mai Bando, Akira Ichikawa

    2006 SICE-ICASE International Joint Conference  2006年 

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    開催年月日: 2006年10月

    記述言語:英語  

    開催地:Busan   国名:大韓民国  

    In this paper, the output regulation problem for linear time-invariant systems with unknown parameters is considered. Based on Lyapunov stability theorem, an adaptive controller which achieves regulation is derived. Then, sufficient conditions for the existence of a controller that solves the output regulation problem with state feedback are established and simulation result are given.

  • A study on designing control system by modular learning

    Mai Bando, Hiroaki Nakanishi, Koichi Inoue

    SICE Annual Conference 2004  2004年 

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    開催年月日: 2004年8月

    記述言語:英語  

    開催地:Sapporo   国名:日本国  

    A control system, which consists of several cooperative modules whose combination and structures change dynamically according to the state and environment, is discussed in this paper. We propose a method to design a control system by modular learning. Numerical simulations and flight experiment of an autonomous aero-robot demonstrate the effectiveness of the proposed method.

▼全件表示

所属学協会

  • 計測自動制御学会

  • 日本航空宇宙学会

  • 米国航空宇宙学会

委員歴

  • 計測自動制御学会   理事   国内

    2024年4月 - 2026年3月   

  • 日本学術会議   連携会員   国内

    2023年10月 - 2029年9月   

  • 日本航空宇宙学会   理事   国内

    2023年4月 - 2024年3月   

  • 日本航空宇宙学会   理事   国内

    2022年4月 - 2023年3月   

  • 日本航空宇宙学会   代議員   国内

    2022年4月 - 2023年3月   

  • International Astronautical Federation’s (IAF) Astrodynamics Symposium Committee   Committee Member   国際

    2021年10月 - 2026年10月   

  • 日本航空宇宙学会西部支部   幹事   国内

    2017年4月 - 2018年3月   

  • 日本航空宇宙学会   代議員   国内

    2017年4月 - 2018年3月   

  • 日本航空宇宙学会西部支部   庶務幹事   国内

    2016年4月 - 2017年3月   

▼全件表示

学術貢献活動

  • プログラム小委員会委員 国際学術貢献

    The 34th International Symposium on Space Technology and Science (ISTS)  ( Kurume Japan ) 2023年6月

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    種別:大会・シンポジウム等 

  • 学術論文等の審査

    役割:査読

    2023年

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    種別:査読等 

    外国語雑誌 査読論文数:6

    国際会議録 査読論文数:4

  • 日本航空宇宙学会

    2022年4月 - 2024年3月

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    種別:学会・研究会等 

  • プログラム小委員会委員 国際学術貢献

    The 33rd International Symposium on Space Technology and Science (ISTS)  ( Japan ) 2022年2月 - 2022年3月

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    種別:大会・シンポジウム等 

  • 学術論文等の審査

    役割:査読

    2022年

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    種別:査読等 

    外国語雑誌 査読論文数:7

    国際会議録 査読論文数:12

  • 学術論文等の審査

    役割:査読

    2021年

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    種別:査読等 

    外国語雑誌 査読論文数:9

    国際会議録 査読論文数:2

  • 学術論文等の審査

    役割:査読

    2020年

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    種別:査読等 

    外国語雑誌 査読論文数:10

    国際会議録 査読論文数:12

  • 不明 国際学術貢献

    三体問題の力学系と軌道設計に関する研究会  ( Japan ) 2019年10月

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    種別:大会・シンポジウム等 

    参加者数:20

  • プログラム小委員会委員 国際学術貢献

    The 32nd International Symposium on Space Technology and Science (ISTS)  ( 福井 ) 2019年6月

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    種別:大会・シンポジウム等 

  • 学術論文等の審査

    役割:査読

    2019年

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    種別:査読等 

    外国語雑誌 査読論文数:4

    国際会議録 査読論文数:10

  • 学術論文等の審査

    役割:査読

    2018年

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    種別:査読等 

    外国語雑誌 査読論文数:6

    日本語雑誌 査読論文数:2

  • Organization Commitee 国際学術貢献

    The 9th Kyushu Univ-KAIST Symposium on Aerospace Engineering  ( Japan ) 2017年12月

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    種別:大会・シンポジウム等 

    参加者数:60

▼全件表示

共同研究・競争的資金等の研究課題

  • 非線形力学系の縮約表現に基づく制御理論の探求

    研究課題/領域番号:22H03663  2022年 - 2026年

    日本学術振興会  科学研究費助成事業  基盤研究(B)

      詳細を見る

    担当区分:研究代表者  資金種別:科研費

  • データ駆動型サイエンスによる宇宙機軌道力学におけるカオス現象の解明

    研究課題/領域番号:21K18781  2021年 - 2023年

    日本学術振興会  科学研究費助成事業  挑戦的研究(萌芽)

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    担当区分:研究代表者  資金種別:科研費

  • 宇宙ミッション創出へ向けたデータ駆動型サイエンスと軌道工学の融合

    2021年 - 2023年

    JST 創発的研究支援事業

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    担当区分:研究代表者  資金種別:受託研究

  • 昆虫複眼システムに基づく完全自律型ドローンの開発と3次元観測ネットワークの構築

    研究課題/領域番号:20H02354  2020年4月 - 2024年3月

    科学研究費助成事業  基盤研究(B)

    外本 伸治, 坂東 麻衣

      詳細を見る

    資金種別:科研費

    本研究では、昆虫の複眼システムを模倣した工学システムについての研究を発展させ、障害物が存在する空間においてもドローンが自在に飛行できる完全自律型の航法誘導システムを開発する。これは、ドローンに搭載された画像センサから、ドローンの飛行状態、周囲にある障害物までの距離、障害物の形状を高速に推定するシステムである。さらに、自律飛行するドローンを空中プラットフォームとして捉え、複数の自律ドローンを用いて、これまでにない能動的3次元観測ネットワークを構築する。

    CiNii Research

  • 多体力学系の構造を用いた低推力宇宙機による惑星間ハイウェイ

    研究課題/領域番号:18K04560  2018年 - 2020年

    日本学術振興会  科学研究費助成事業  基盤研究(C)

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    担当区分:研究代表者  資金種別:科研費

  • 多体力学系の軌道設計への制御理論的アプローチ

    2015年

    九州大学基金 若手教職員の長期海外派遣支援

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    担当区分:研究代表者  資金種別:学内資金・基金等

  • 強い非線形性を伴う環境下における宇宙機の超精密制御

    2014年

    工学研究院若手研究者育成研究助成

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    担当区分:研究代表者  資金種別:学内資金・基金等

  • 地上観測による人工衛星の軌道運動の動態推定技術

    2013年10月 - 2014年3月

    共同研究

      詳細を見る

    担当区分:研究代表者  資金種別:その他産学連携による資金

  • 宇宙機軌道設計のための多体力学系の制御理論的解析

    研究課題/領域番号:25870513  2013年 - 2016年

    科学研究費助成事業  若手研究(B)

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    担当区分:研究代表者  資金種別:科研費

  • 地上観測による人工衛星の軌道運動の動態推定技術

    2012年7月 - 2012年10月

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    担当区分:研究代表者  資金種別:その他産学連携による資金

  • 母関数を用いた宇宙機の非線形軌道最適化問題の効率解法

    研究課題/領域番号:21760650  2009年 - 2010年

    科学研究費助成事業  若手研究(B)

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    担当区分:研究代表者  資金種別:科研費

  • 環境適応型自律ロボットのシステム構成原理

    研究課題/領域番号:06J02848  2006年 - 2007年

    日本学術振興会  科学研究費助成事業  特別研究員奨励費

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    担当区分:研究代表者  資金種別:科研費

▼全件表示

担当授業科目

  • (IUPE)Systems Control ⅡB

    2023年6月 - 2023年8月   夏学期

  • 飛行制御論B

    2023年6月 - 2023年8月   夏学期

  • 数学創発モデリング

    2023年4月 - 2024年3月   通年

  • 数学共創モデリング

    2023年4月 - 2024年3月   通年

  • 力学基礎

    2023年4月 - 2023年9月   前期

  • 誘導制御特論Ⅱ

    2023年4月 - 2023年9月   前期

  • Advanced Guidance and Control Ⅱ

    2023年4月 - 2023年9月   前期

  • (IUPE)Systems Control ⅡA

    2023年4月 - 2023年6月   春学期

  • 飛行制御論A

    2023年4月 - 2023年6月   春学期

  • 航空宇宙工学A

    2022年6月 - 2022年8月   夏学期

  • 飛行制御論B

    2022年6月 - 2022年8月   夏学期

  • (IUPE)Systems Control ⅡB

    2022年6月 - 2022年8月   夏学期

  • 数学共創モデリング

    2022年4月 - 2023年3月   通年

  • 力学基礎

    2022年4月 - 2022年9月   前期

  • 航空宇宙工学実験

    2022年4月 - 2022年9月   前期

  • 誘導制御特論 II

    2022年4月 - 2022年9月   前期

  • (IUPE)Systems Control ⅡA

    2022年4月 - 2022年6月   春学期

  • 飛行制御論A

    2022年4月 - 2022年6月   春学期

  • 飛行制御論B

    2021年6月 - 2021年8月   夏学期

  • (IUPE)Systems Control ⅡB

    2021年6月 - 2021年8月   夏学期

  • 航空宇宙工学実験

    2021年4月 - 2021年9月   前期

  • 数学共創概論Ⅰ

    2021年4月 - 2021年9月   前期

  • 力学基礎

    2021年4月 - 2021年9月   前期

  • 数学共創概論Ⅰ

    2021年4月 - 2021年9月   前期

  • 力学基礎

    2021年4月 - 2021年9月   前期

  • 誘導制御特論Ⅱ

    2021年4月 - 2021年9月   前期

  • 飛行制御論A

    2021年4月 - 2021年6月   春学期

  • (IUPE)Systems Control ⅡA

    2021年4月 - 2021年6月   春学期

  • 航空宇宙工学実験

    2020年4月 - 2021年3月   通年

  • (IUPE) Systems Control Ⅱ

    2020年4月 - 2020年9月   前期

  • 飛行制御論

    2020年4月 - 2020年9月   前期

  • 飛行制御論A

    2020年4月 - 2020年6月   春学期

  • 飛行制御論A

    2020年4月 - 2020年6月   春学期

  • 誘導制御特論 Ⅱ

    2019年4月 - 2019年9月   前期

  • 飛行制御論

    2019年4月 - 2019年9月   前期

  • (IUPE) Systems Control Ⅱ

    2019年4月 - 2019年6月   春学期

  • 航空宇宙工学実験

    2018年4月 - 2019年3月   通年

  • 基幹物理学ⅠA演習

    2018年4月 - 2018年9月   前期

  • 飛行制御論

    2018年4月 - 2018年9月   前期

  • 基幹物理学ⅠA

    2018年4月 - 2018年9月   前期

  • Systems Control Ⅱ

    2018年4月 - 2018年6月   春学期

  • 航空宇宙工学実験

    2017年4月 - 2018年3月   通年

  • 誘導制御講究

    2017年4月 - 2018年3月   通年

  • 誘導制御特論II

    2017年4月 - 2017年9月   前期

  • 飛行制御論

    2017年4月 - 2017年9月   前期

  • 飛行制御特論Ⅱ

    2017年4月 - 2017年9月   前期

  • 基幹物理学ⅠA

    2017年4月 - 2017年9月   前期

  • 基幹物理学ⅠA演習

    2017年4月 - 2017年9月   前期

  • 基幹物理学IA

    2016年4月 - 2016年9月   前期

  • 基幹物理学IA演習

    2016年4月 - 2016年9月   前期

  • 航空宇宙工学実験

    2015年4月 - 2016年3月   通年

  • 航空宇宙工学実験

    2014年4月 - 2015年3月   通年

  • 航空宇宙工学実験

    2013年4月 - 2014年3月   通年

▼全件表示

FD参加状況

  • 2020年4月   役割:参加   名称:e-learningでの成績評価

    主催組織:部局

  • 2018年3月   役割:参加   名称:M2B(みつば)学習支援システム講習会

    主催組織:全学

  • 2013年9月   役割:参加   名称:科学研究費補助金獲得のためのFD

    主催組織:学科

  • 2013年1月   役割:参加   名称:ハラスメント防止に関する研修会

    主催組織:部局

他大学・他機関等の客員・兼任・非常勤講師等

  • 2019年  宇宙航空研究開発機構 宇宙科学研究所  区分:客員教員  国内外の区分:国内 

  • 2018年  放送大学福岡学習センター  国内外の区分:国内 

社会貢献活動

  • 高校生のための市民講座「創造する未来と科学の可能性」

    福岡市科学館  福岡市科学館  2022年6月

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    対象:社会人・一般, 学術団体, 企業, 市民団体, 行政機関

    種別:講演会

  • 放送大学 面接授業「宇宙ミッションと軌道力学」

    放送大学  放送大学福岡学習センター  2018年11月

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    対象:社会人・一般, 学術団体, 企業, 市民団体, 行政機関

    種別:セミナー・ワークショップ

  • 小わく星のはなし

    香椎東小学校  2015年2月

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    対象:幼稚園以下, 小学生, 中学生, 高校生

  • 小惑星衝突回避と軌道工学

    兵庫県立明石北高等学校  2012年8月

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    対象:幼稚園以下, 小学生, 中学生, 高校生

    種別:セミナー・ワークショップ

  • 小惑星探査機『はやぶさ』帰還カプセル特別公開

    京都大学,京都府教育委員会  2011年2月

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    対象:社会人・一般, 学術団体, 企業, 市民団体, 行政機関

    種別:その他

    小惑星探査機「はやぶさ」帰還カプセル特別公開企画検討委員会に参加.説明員に対する事前講習を行った.

  • 小わく星のおはなし

    福知山市立川合小学校(京都府)  2011年1月

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    対象:幼稚園以下, 小学生, 中学生, 高校生

  • 小わく星のおはなし

    綾部市立西八田小学校  2011年1月

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    対象:幼稚園以下, 小学生, 中学生, 高校生

  • 小わく星のおはなし

    木津川市立高の原小学校  2010年7月

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    対象:幼稚園以下, 小学生, 中学生, 高校生

▼全件表示

メディア報道

  • 宇宙の魅力語る 京大助教、綾部・西八田小で授業 新聞・雑誌

    京都新聞  2011年1月

     詳細を見る

    宇宙の魅力語る 京大助教、綾部・西八田小で授業

海外渡航歴

  • 2015年4月 - 2016年4月

    滞在国名1:アメリカ合衆国   滞在機関名1:University of Colorado at Boulder

学内運営に関わる各種委員・役職等

  • 2017年4月 - 2018年3月   その他 広報委員会委員

  • 2016年4月 - 2017年3月   その他 広報委員会委員

  • 2016年4月 - 2017年3月   全学 嚶鳴編集専門委員会

  • 全学 国際卓越研究大学に係る国際ワーキンググループ