Updated on 2024/10/02

Information

 

写真a

 
HOKAMOTO SHINJI
 
Organization
Faculty of Engineering Department of Aeronautics and Astronautics Professor
School of Engineering (Concurrent)
Graduate School of Engineering Department of Aeronautics and Astronautics(Concurrent)
Title
Professor
Contact information
メールアドレス
Profile
Research: Submittion of original research articles to Journals Education: Lecture to students and supervisor of research
External link

Research Areas

  • Frontier Technology (Aerospace Engineering, Marine and Maritime Engineering) / Aerospace engineering

  • Informatics / Mechanics and mechatronics

  • Manufacturing Technology (Mechanical Engineering, Electrical and Electronic Engineering, Chemical Engineering) / Control and system engineering

Degree

  • Kyushu University (Japan), Doctor of Engineering

Research History

  • Kyushu University   

    2010.4 - Present

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  • 佐賀大学:1987年4月〜1996年3月   

Education

  • Kyushu University   School of Engineering   航空工

    - 1984

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    Country:Japan

    researchmap

  • Kyushu University   Faculty of Engineering   Aeronautics

    - 1984

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Research Interests・Research Keywords

  • Research theme: 非ホロノミック制御

    Keyword: 非ホロノミック制御

    Research period: 2024

  • Research theme: 自律システム

    Keyword: 自律システム

    Research period: 2024

  • Research theme: 宇宙探査システム

    Keyword: 宇宙探査システム

    Research period: 2024

  • Research theme: Space System

    Keyword: Space System

    Research period: 2024

  • Research theme: Nonholonomic Control System

    Keyword: Nonholonomic Control System

    Research period: 2024

  • Research theme: Autonomous Control

    Keyword: Autonomous Control

    Research period: 2024

  • Research theme: Development of Autonomous Navigation Systems based on Insect Vision

    Keyword: Vision Guidance System, Optic Flow, Compound Eye System

    Research period: 2012.4

  • Research theme: Control of Nonlinear Systems with Non-holonomic Constraints

    Keyword: Space, Non-holonomic, Tether

    Research period: 2000.1

  • Research theme: Dynamics and Control of Space Robots

    Keyword: Space, Robot, Non-holonomic, Path Planning

    Research period: 2000.1

  • Research theme: Development of Autonomous Systems

    Keyword: Autonomous System, Path Plannning, Leg Locomotion, Vision Guidance System

    Research period: 2000.1

Papers

  • Controllability Analysis of Propellant-Free Satellite Formation Flight Reviewed International journal

    #Mohamed Shouman, @Mai Bando, @Shinji Hokamoto

    Journal of Guidance, Control, and Dynamics   44 ( 12 )   2214 - 2224   2021.12

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    Language:English   Publishing type:Research paper (scientific journal)  

    This paper presents a comprehensive analysis of the controllability for the relative dynamics of satellites using space environment forces. First, the constraints of the space environment forces are illustrated for circular orbits, and the integration of space environment forces for achieving full controllability is considered. Two approaches are used to estimate the controllability of various configurations of space environment forces. The first approach relies on controllability theory for linear continuous and discrete systems, including a derivation of a new linear formulation for solar radiation pressure with lower constraints. The second approach exploits extensive numerical simulations for controllability analyses of nonlinear dynamics models. The linear quadratic regulator is designed for different dynamics models of the space environment forces and implemented numerically for nonlinear dynamics using an anti-windup scheme with bounded control inputs. The numerical simulations demonstrate that the Lorentz forces and the differential atmospheric drag are more effective control forces in the low Earth orbits than the solar radiation pressure.

    DOI: 10.2514/1.G006035

    Other Link: https://doi.org/10.2514/1.G006035

  • Guidelines for practical navigation systems based on wide-field-integration of optic flow Reviewed International journal

    #Naoto Kobayashi, @Mai Bando, @Shinji Hokamoto, Daisuke Kubo

    Asian Journal of Control   2021.10

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    Language:English   Publishing type:Research paper (scientific journal)  

    This paper shows some guidelines to improve the estimation accuracy of a navigation system, which is based on wide-field-integration (WFI) of optic flow. Optic flow is a vector field of relative velocities obtained by photoreceptors in image sensors, and WFI of optic flow enables motion estimation robust by integrating wide range of optic flow. Since the system has several attractive features (small size, light weight, and low computation), it is applicable to an autonomous control system of micro air vehicles. However, due to some restrictions of real systems, WFI of optic flow theory should be applied while considering sensor arrangement for better estimation. In this paper, first an adequate number and adequate optical-axes of image sensors are investigated. Then, a new estimation system combining a gyro sensor with WFI of optic flow is discussed by numerical simulations. Finally, the essential effect for the number of cameras are verified in experiments.

    DOI: 10.1002/asjc.2363

    Repository Public URL: http://hdl.handle.net/2324/4479598

  • Two-Input-Torque for Hopping Exploration Robot to Enhance Reachability under Microgravity Reviewed International journal

    #Yusei Sasaki, #Tomohiro Ishizuka, @Mai Bando, @Shinji Hokamoto

    Transactions of Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan   19 ( 5 )   719 - 725   2021.9

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    Language:English   Publishing type:Research paper (scientific journal)  

    DOI: 10.2322/tastj.19.719

  • Formation Flying Trajectory Design based on Attractive Sets of Tschauner-Hempel Equations Reviewed International journal

    #Motoki Yamane, @Mai Bando, @Shinji Hokamoto

    Journal of Guidance, Control, and Dynamics   43 ( 10 )   1943 - 1951   2020.10

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    Language:English   Publishing type:Research paper (scientific journal)  

    This paper proposes a new method of optimal trajectory design for formation flying along an elliptical orbit. If the system is linear and a quadratic performance index is assumed, the optimal cost is quadratic form of the initial state. Attractive sets of optimal control are defined as level sets of the optimal cost based on linear quadratic regulator theory. They describe a set of all initial states to reach a desired state by a given cost. By solving the optimal control problem for the Tschauner-Hempel equations, the optimal cost is characterized by a time-periodic solution to the Riccati differential equation. This paper defines the attractive set for optimal formation reconfiguration problem and develops the procedures to draw the attractive
    set. A novel method to depict the geometry of the attractive set of optimal control along a periodic orbit is proposed. Several applications to illustrate the theory are also given.

    Repository Public URL: http://hdl.handle.net/2324/4479056

  • Station-keeping and formation flying based on nonlinear output regulation theory Reviewed International journal

    #Yuki Akiyama, @Mai Bando, @Shinji Hokamoto

    Acta Astronautica   153   289 - 296   2018.12

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    Language:English   Publishing type:Research paper (scientific journal)  

    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

  • Explicit form of station-keeping and formation flying controller for libration point orbits Reviewed International journal

    #Yuki Akiyama, @Mai Bando, @Shinji Hokamoto

    Journal of Guidance, Control, and Dynamics   41 ( 6 )   1405 - 1413   2018.7

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    Language:English   Publishing type:Research paper (scientific journal)  

    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

  • Chattering Attenuation Sliding Mode Approach for Nonlinear Systems Reviewed International journal

    #Hamidreza Nemati, @Mai Bando, @Shinji Hokamoto

    Asian Journal of Control   19 ( 4 )   1519 - 1531   2017.7

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    Language:English   Publishing type:Research paper (scientific journal)  

    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

    Repository Public URL: http://hdl.handle.net/2324/4479597

  • Comparison of integrated and nonintegrated wide-field optic flow for vehicle navigation Reviewed International journal

    #Michael A. Shoemaker, @Shinji Hokamoto

    Journal of Guidance, Control, and Dynamics   36 ( 3 )   710 - 720   2013.5

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    Language:English   Publishing type:Research paper (scientific journal)  

    Recent studies of vision-based navigation and guidance for robotic vehicles have been inspired by the biological systems found in flying insects. The wide-field integration of optic flow is one pre-existing method, in which the sensed optic flow is integrated along with sensitivity functions to mimic the action of directionally sensitive cells observed in some insects' visual systems. This study re-examines the wide-field integration method and reformulates the problem from a summation rather than an integral. This reformulation allows the wide-field integration measurement outputs to be directly compared with nonintegrated optic flow measurements. The method using nonintegrated optic flow measurements is shown to have some practical advantages, such as eliminating the need to define input sensitivity functions and having a measurement Jacobian that is easier to derive analytically. Also, the state estimates obtained with the nonintegrated method are proven to have minimum variance compared with those from the wide-field integration method. Numerical simulations of each method are shown for a vehicle maintaining level flight at constant altitude over a flat terrain.

    DOI: 10.2514/1.59084

  • 移動するマニフォールドを用いた平面宇宙ロボットのフィードバック制御 Reviewed

    @外本 伸治, #船迫 俊郎

    日本ロボット学会誌   25 ( 5 )   745 - 751   2007.7

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    Language:Japanese   Publishing type:Research paper (scientific journal)  

    Feedback Control of a Planar Space Robot Using a Moving Manifold

    DOI: 10.7210/jrsj.25.745

  • 非ホロノミック性を利用した剛体衛星の軌道変更に関する研究 Reviewed

    @外本 伸治

    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences   54 ( 634 )   477 - 484   2006.11

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    Language:Japanese   Publishing type:Research paper (scientific journal)  

    A Study on Orbital Transfer of a Rigid Satellite System Using Its Nonholonomic Constraint

    DOI: 10.2322/jjsass.54.477

  • New Equilibria and Dynamic Structures Under Continuous Optimal Feedback Control

    Tsuruta, A; Bando, M; Hokamoto, S; Scheeres, DJ

    JOURNAL OF GUIDANCE CONTROL AND DYNAMICS   47 ( 10 )   2029 - 2040   2024.10   ISSN:0731-5090 eISSN:1533-3884

  • Data-Driven Modeling for Multirotor Autonomous Control

    Shiotsuka T., Bando M., Hokamoto S.

    AIAA SciTech Forum and Exposition, 2024   2024   ISBN:9781624107115

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    Publisher:AIAA SciTech Forum and Exposition, 2024  

    The precise trajectory control of UAVs, including multirotors, is challenging due to uncertainties such as modeling errors, unmodeled aerodynamic forces, and wind disturbances. To address this issue, this paper focuses on real-time modeling of quadrotor motion exploiting recently developed data-driven methods. By constructing a dynamical model in real-time using data collected during flight, it is expected to develop a dynamical model that incorporates uncertainties arising from modeling errors and disturbances. In particular, the data-driven modeling method called Real-Time Update Dynamic Mode Decomposition (RTDMD), an extension of the DMD algorithm with sequential update rules, is employed for the real-time modeling of dynamical models. Identification experiments using experimental data demonstrate that the RTDMD successfully obtained a dynamical model for estimating the quadrotor’s state.

    DOI: 10.2514/6.2024-0568

    Scopus

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

    TAKEUCHI Saki, BANDO Mai, HOKAMOTO Shinji

    Journal of Evolving Space Activities   2 ( 0 )   n/a   2024   eISSN:27581802

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    Language:English   Publisher:International Symposium on Space Technology and Science  

    <p>Spacecraft with movable parts can change their attitude through utilizing non-holonomic features generated by their motion. This can be used as an alternative attitude control method when their equipped attitude control devices no longer generate control torque. No propellant is required in this method, so it has attracted attention as a control method to extend the life of spacecraft. This paper discusses the optimization of the structural configurations to increase the efficiency of the non-holonomic features when attitude control devices are malfunctioned. The optimization problem is difficult due to several reasons: non-holonomic attitude change can be evaluated from numerical integration along trajectories in joint space, spacecraft might have many movable parts as well as structural design parameters, and so on. In this paper, the optimization problem is solved as iterative optimizations in the subspace consisting of the extracted parameters rather than considering all parameters simultaneously. The numerical results show that structural optimization can make the attitude change much more significant.</p>

    DOI: 10.57350/jesa.169

    CiNii Research

  • Discrete-Time Attitude Control for Spacecraft Using Iterative Learning

    HAYASHI Yuta, Mai BANDO, HOKAMOTO Shinji

    Journal of Evolving Space Activities   2 ( 0 )   n/a   2024   eISSN:27581802

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    Language:English   Publisher:International Symposium on Space Technology and Science  

    <p>This study aims at the attitude control problem of spacecraft with periodic disturbances and model uncertainty by using anticipatory Iterative Learning Control (ILC), a combination of feedback control and ILC in a discrete-time system. Using a sampling point a little forward in one previous cycle, the convergence accuracy to the target value is improved step by step by the anticipatory ILC scheme, and its effectiveness against periodic disturbances is verified. In addition, we compare the accuracy to the target value by changing the sampling point selected in one previous cycle.</p>

    DOI: 10.57350/jesa.171

    CiNii Research

  • Mission Strategy to Await Comets by Leveraging Manifolds and Low Thrust Reviewed International journal

    #Soi Yamaguchi, #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 74th International Astronautical Congress   2023.10

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    Language:English   Publishing type:Research paper (scientific journal)  

  • Analysis of Transfer Trajectories in Cislunar Space Using Sequences of Lobe Dynamics Reviewed International journal

    #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 74th International Astronautical Congress   2023.10

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    Language:English   Publishing type:Research paper (scientific journal)  

  • Attitude Control Using Iterative Learning Control Considering Orbital Motion of NRHO Reviewed International journal

    #Yuta Hayashi, #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 74th International Astronautical Congress   2023.10

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    Language:English   Publishing type:Research paper (scientific journal)  

  • Guidance and Control Algorithm for Mars Aerocapture Considering Uncertainties Reviewed International journal

    #Ayumi Chikusa, #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 74th International Astronautical Congress   2023.10

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    Language:English   Publishing type:Research paper (scientific journal)  

  • Optimal Trajectory Design by ADAM under Stochastic Disturbing Acceleration Reviewed International journal

    #Shodai Hirayama, #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 74th International Astronautical Congress   2023.10

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    Language:English   Publishing type:Research paper (scientific journal)  

  • A New Gravitational Wave Observatory Formation Configuration Design and Control Method Reviewed International journal

    #Zhengxu Pan, @Mai Bando, Zhanxia Zhu, @Shinji Hokamoto

    Proceedings of the 2023 SICE Annual Conference   2023.9

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    Language:English   Publishing type:Research paper (scientific journal)  

  • Transfer between Resonances via Lobe Dynamics in the Standard Map Reviewed International journal

    #Naoki Hiraiwa, Isaia Nisoli, Yuzuru Sato, @Mai Bando, @Shinji Hokamoto

    Proceedings of 10th International Congress on Industrial and Applied Mathematics   2023.8

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    Language:English   Publishing type:Research paper (international conference proceedings)  

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

    Hiraiwa, N; Bando, M; Hokamoto, S

    JOURNAL OF GUIDANCE CONTROL AND DYNAMICS   46 ( 8 )   1637 - 1648   2023.8   ISSN:0731-5090 eISSN:1533-3884

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    Publisher:Journal of Guidance, Control, and Dynamics  

    DOI: 10.2514/1.G007151

    Web of Science

    Scopus

  • Design of Chaotic Transfers Based on Lobe Dynamics

    HIRAIWA Naoki, BANDO Mai, HOKAMOTO Shinji

    The 33rd Workshop on JAXA Astrodynamics Symposium and Flight Mechanics   2023.7

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    Language:English   Publisher: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

  • Global analysis of the Circular Restricted Three-Body Problem using Stochastic Noise

    BANDO Mai, HOKAMOTO Shinji

    The 33rd Workshop on JAXA Astrodynamics Symposium and Flight Mechanics   2023.7

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    Language:English   Publisher: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

  • Effect of Joints Structure of Transformable Spacecraft on Attitude Change Utilizing Non-holonomic Constrain

    TAKEUCHI Saki, BANDO Mai, HOKAMOTO Shinji

    The 33rd Workshop on JAXA Astrodynamics Symposium and Flight Mechanics   2023.7

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    Language:English   Publisher: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

  • Equilibria and Dynamical Structures with Quadratic Optimal Control

    TSURUTA Ayano, BANDO Mai, SCHEERES Daniel J, HOKAMOTO Shinji

    The 33rd Workshop on JAXA Astrodynamics Symposium and Flight Mechanics   2023.7

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    Language:English   Publisher: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

  • Optimization of Structural Configurations of Spacecraft for Efficient Attitude Change Utilizing Non-holonomic Features Reviewed International journal

    #Saki Takeuchi, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 34th International Symposium on Space Technology and Science   2023.6

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    Language:English   Publishing type:Research paper (international conference proceedings)  

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

    #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Journal of Journal of Evolving Space Activities   1 ( 0 )   n/a   2023.6   eISSN:27581802

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    Language:English   Publishing type:Research paper (scientific journal)   Publisher:International Symposium on Space Technology and Science  

    <p>This paper proposes an algorithm to systematically search for a good sequence and the number of intermediate orbits in order to design the low-thrust minimum-fuel halo-to-halo transfer. The proposed algorithm applies successive convex optimization for the optimal transfer design, and initial guesses for the optimization are generated by beam search. In the beam search process, intermediate halo orbits that construct the initial guesses are chosen from a family of halo orbits so that they are located between the initial and final halo orbits. By determining the appropriate evaluation index for the intermediate orbit design, the proposed algorithm can collect local optimal solutions with a reasonable computational time. The obtained optimal transfers provide several options for the total △<i>V</i> and time of flight, which helps to find the suitable solution based on mission requirements.</p>

    DOI: 10.57350/jesa.48

    CiNii Research

  • Discrete-Time Attitude Control for Spacecraft Using Iterative Learning Reviewed International journal

    #Yuta Hayashi, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 34th International Symposium on Space Technology and Science   2023.6

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    Language:English   Publishing type:Research paper (international conference proceedings)  

  • Optimal Transfer by Stochastic Gradient Descent Algorithm ADAM Reviewed International journal

    #Shodai Hirayama, #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 34th International Symposium on Space Technology and Science   2023.6

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    Language:English   Publishing type:Research paper (international conference proceedings)  

  • New Equilibria in Quadratic Optimal Control Systems Reviewed International journal

    #Ayano Tsuruta, @Mai Bando, Daniel Scheeres, @Shinji Hokamoto

    Proceedings of the 34th International Symposium on Space Technology and Science   2023.6

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    Language:English   Publishing type:Research paper (international conference proceedings)  

  • Orbital Configuration Control for Space-based Gravitational Wave Observatory in the Three-body Problem Reviewed International journal

    #Zhengxu Pan, Zhanxia Zhu, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 34th International Symposium on Space Technology and Science   2023.6

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    Language:English   Publishing type:Research paper (international conference proceedings)  

  • Data-Driven Guidance and Control for Asteroid Landing Based on Real-Time Dynamic Mode Decomposition Reviewed International journal

    #Taiga Kajikawa, #Tatsuya Shiotsuka, @Mai Bando, @Shinji Hokamoto

    IEEE Access   11   52622 - 52635   2023.5   ISSN:2169-3536

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    Language:English   Publishing type:Research paper (scientific journal)   Publisher:IEEE Access  

    Navigation and control near asteroids are challenging due to high levels of uncertainty, necessitating a high degree of autonomy and safety. To address this challenge, we propose a novel method for leveraging data-driven approaches, which have garnered significant attention in recent years. Traditional data-driven and machine learning techniques have been applied to space exploration problems; however, they often require large amounts of data in advance and are not robust to unknown environments. Hence, they are typically used in auxiliary roles and are not easily adaptable to real-time modeling and control. We propose the use of the theory of dynamic mode decomposition (DMD) and delayed embedding to construct a data-driven real-time guidance and control system for asteroid landings. Our approach employs low-dimensional information obtained from onboard sensors to construct nonlinear dynamics in the vicinity of asteroids. Based on the constructed dynamical model, we propose a guidance control strategy for accurate and reliable spacecraft landing. Our proposed method has the potential to improve guidance and control systems for space exploration by enabling real-time modeling and control with reduced computational cost.

    DOI: 10.1109/ACCESS.2023.3276754

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    Scopus

  • Design of Low Energy Transfer Trajectories from Earth to Europa with Ballistic Capture Reviewed International journal

    #Kanta Ikeda, @Mai Bando, @Shinji Hokamoto

    Journal of Journal of Evolving Space Activities   1 ( 0 )   1 - 10   2023.4   eISSN:27581802

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    Language:English   Publishing type:Research paper (scientific journal)   Publisher:International Symposium on Space Technology and Science  

    <p>This paper aims to construct a method to design low-energy transfer trajectories from Jupiter to Europa, one of the Galilean satellites, via ballistic transfer. The proposed method leverages the periapsis Poincaré map and efficiently finds ballistic transfer trajectories from Jupiter’s sphere of influence (SOI) to Europa. For the evaluation of the proposed method, the interplanetary trajectory from Earth to Jupiter’s SOI is designed by using existing methods, the Tisserand map and multiple gravity assists. By solving the phasing problem that considers the ephemeris of the celestial bodies, this map can find interplanetary trajectories with various transfer times depending on the launch date. It is demonstrated that the periapsis Poincaré map can efficiently find all ballistic transfer trajectories in the region, although it depends on the initial conditions. Furthermore, by applying the clustering method to the obtained ballistic transfer trajectories, we succeeded in finding families of ballistic transfer trajectories existing within the region.</p>

    DOI: 10.57350/jesa.35

    CiNii Research

  • Analysis of Transfer Trajectories in Cislunar Space Using Sequences of Lobe Dynamics

    Hiraiwa N., Bando M., Hokamoto S.

    Proceedings of the International Astronautical Congress, IAC   2023-October   2023   ISSN:00741795

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    Publisher:Proceedings of the International Astronautical Congress, IAC  

    The Gateway will be constructed as a staging point for exploring cislunar space in the Artemis program. For the maintenance of this platform, uncrewed cargo transport is planned by JAXA. To efficiently conduct cargo transport, this study proposes a novel methodology to design low-energy chaotic transfers based on lobe dynamics in the planar circular restricted three-body problem (CR3BP). Lobe dynamics focuses on the " lobe, " the region determined by stable and unstable manifolds of a resonant orbit, and can reveal phase space transport of chaotic trajectories. In general, lobe dynamics of one resonant orbit can transfer a spacecraft only around the tori related to the resonant orbit in concern. The proposed method combines lobe dynamics of various resonant orbits to make a desired transfer. The fuel-optimal transfer path is found based on a graph by introducing some simplification. By adding trajectory correction maneuvers, the robust optimal transfer trajectory is achieved in the CR3BP.

    Scopus

  • Experimental Research for Improvement of Wide-Field-Integration of Optic Flow Sensor

    Honda Yuki, Bando Mai, Hokamoto Shinji

    Proceedings of the Japan Joint Automatic Control Conference   66 ( 0 )   536 - 540   2023

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    Language:Japanese   Publisher:The Japan Joint Automatic Control Conference  

    DOI: 10.11511/jacc.66.0_536

    CiNii Research

  • Stereo cameras using formation flight of multirotor aircraft

    Kurahashi Seiya, Bando Mai, Hokamoto Shinji

    Proceedings of the Japan Joint Automatic Control Conference   66 ( 0 )   526 - 530   2023

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    Language:Japanese   Publisher:The Japan Joint Automatic Control Conference  

    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   ISSN:1876-1100 ISBN:978-981-19-2634-1 eISSN:1876-1119

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    Publisher: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

  • Optimal Trajectory Design by Adam under Stochastic Disturbing Acceleration

    Hirayama S., Hiraiwa N., Bando M., Hokamoto S.

    Proceedings of the International Astronautical Congress, IAC   2023-October   2023   ISSN:00741795

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    Publisher:Proceedings of the International Astronautical Congress, IAC  

    This paper presents optimization methods that incorporate elements of Adaptive Moment Estimation (Adam) into Sequential Quadratic Programming (SQP) for designing two-impulse transfer trajectories from one halo orbit to another with minimum velocity increment. The optimization problem can be formulated by a cost function that evaluates velocity increments at endpoints. The gradient and Hessian of the problem are calculated using the state transition tensors and then used for the Adam-enhanced SQP implementaion. To validate the effectiveness of this approach, we solve the optimal transfer problem using random initial guesses and stochastic disturbing acceleration. The results from numerical simulations are analyzed with respect to the cost function, transfer time, and orbit stability.

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  • Mission Strategy to Await Comets by Leveraging Manifolds and Low Thrust

    Yamaguchi S., Hiraiwa N., Bando M., Hokamoto S.

    Proceedings of the International Astronautical Congress, IAC   2023-October   2023   ISSN:00741795

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    In recent years, comet exploration missions represented by the Comet Interceptor mission have attracted our attention to unravel the origin of our solar system. Motivated by the Comet Interceptor mission concept, this paper firstly proposes designing standby orbits by leveraging invariant manifold structures in the Sun-Earth CRTBP system. To expand accessible regions, the optimization problem is solved, and the optimal input added to unstable manifolds emanating from periodic and quasi-periodic orbits is obtained. Moreover, the two-point boundary value problem (TPBVP) about the final time of the propagation is solved to make multiple space probes form a constellation by leveraging both single and multiple shooting methods. Designing the trajectories to expand accessible areas by leveraging invariant manifolds and low-thrust engines enables even small spacecraft to observe and explore unknown comets.

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  • Guidance and Control Algorithm for Mars Aerocapture Considering Uncertainties

    Chikusa A., Hiraiwa N., Bando M., Hokamoto S.

    Proceedings of the International Astronautical Congress, IAC   2023-October   2023   ISSN:00741795

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    Aerocapture is the one of the most effective methods for future large-scale exploration because it enable trajectory transformation with less fuel. In this study, optimal aerocapture problem is investigated based on the analysis of aerocapture trajectory. Simulate the aerocapture trajectory with and without uncertainties, and from the results, the optimal control condition for guided control of of aerocapture of developed. Using the optimal aerocaputre problem, this paper proposes the problem involving re-solving to design trajectories that can be more robust to uncertainties.

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  • New design of a tilt-rotor eVTOL for stability in transition mode

    Kitaba Hayate, Bando Mai, Hokamoto Shinji

    Proceedings of the Japan Joint Automatic Control Conference   66 ( 0 )   335 - 342   2023

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    DOI: 10.11511/jacc.66.0_335

    CiNii Research

  • Attitude Control using Iterative Learning Control Considering Orbital Motion of NRHO

    Hayashi Y., Bando M., Hokamoto S.

    Proceedings of the International Astronautical Congress, IAC   2023-October   2023   ISSN:00741795

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    Recently, deep space exploration has advanced particularly with orbital characteristics of NRHO being widely studied. However, studies for spacecraft autonomy have not progressed well. A control law that combines feedback control and Iterative Learning Control(ILC) is applied to the attitude control system of a spacecraft, and furthermore, the control input is realized by a CMG capable of high output, with the aim of improving the attitude tracking control system step by step by increasing the orbital motion.

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  • An Improved YOLO for Tiny Rocks Detection in Spacecraft Autonomous Landing Reviewed International journal

    #Xi Chen, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 2022 Asia-Pacific International Symposium on Aerospace Technology (APISAT2022)   2022.10

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  • Design of Satellites Tours Using Periapsis Poincaré Map in Multibody Dynamics of Jovian System Reviewed International journal

    #Kanta Ikeda, #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 73rd International Astronautical Congress   2022.9

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  • Data-Driven Orbital Control in Perturbed Environment Reviewed International journal

    #Komsun Tamanakijprasart, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 2022 SICE Annual Conference   2022.9

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  • Influence of Overall Layout Design of Compound Multi-Rotor Vehicles on Flight Performance Reviewed International journal

    #Yuke Huang, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 33rd Congress of the International Council of the Aeronautical Sciences   2022.9

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  • Altitude Estimation by Wide-Field-Integration Optic Flow Reviewed International journal

    #Hiromitsu Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 33rd Congress of the International Council of the Aeronautical Sciences   2022.9

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  • Data-Driven Guidance for Asteroid Landing Based on Real-Time Dynamic Mode Decomposition Reviewed International journal

    #Taiga Kajikawa, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 73rd International Astronautical Congress   2022.9

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  • A Data-Driven Nonlinear Optimal Control Using Koopman Operator on Hamiltonian Flow Reviewed International journal

    #Kyoshuke Sato, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 73rd International Astronautical Congress   2022.9

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  • Design of Optimal Low-Thrust Orbit-to-Orbit Transfers via Convex Approach Reviewed International journal

    #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 73rd International Astronautical Congress   2022.9

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  • Formation flying along libration point orbits using chattering attenuation sliding mode control

    Bando, M; Namati, H; Akiyama, Y; Hokamoto, S

    FRONTIERS IN SPACE TECHNOLOGIES   3   2022.7   eISSN:2673-5075

  • Formation Flying Along Libration Point Orbits Using Chattering Attenuation Sliding Mode Control Reviewed International journal

    @Mai Bando, Hamidreza Nemati, Yuki Akiyama, @Shinji Hokamoto

    Frontier in Space Technology   2022.7

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  • Sparse Optimal Trajectory Design in Three-Body Problem

    Kayama, Y; Bando, M; Hokamoto, S

    JOURNAL OF THE ASTRONAUTICAL SCIENCES   69 ( 3 )   829 - 856   2022.6   ISSN:0021-9142 eISSN:2195-0571

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    This paper proposes the sparse optimal control in the circular restricted three-body problem to exploit the dynamical structure of the linearized motion around equilibrium points or periodic orbits. First, optimal transfer problem is formulated for a linearized system where the objective function and constraints are given by convex sets. For a long time transfer problem in the vicinity of periodic orbits, the Floquet-Lyapunov transformation and a normal form are introduced to enable numerical calculations. Then, the proposed method is applied to several transfer problems around an equilibrium point or periodic orbits and a parameter analysis is performed to understand the optimal transfer by changing the maximum thrust acceleration and time of flight. Finally, a new station-keeping strategy is proposed to implement the sparse optimal solution in a nonlinear dynamics.

    DOI: 10.1007/s40295-022-00315-1

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    Scopus

  • Sparse Optimal Trajectory Design in Three-Body Problem Reviewed International journal

    #Yuki Kayama, @Mai Bando, @Shinji Hokamoto

    Journal of the Astronautical Sciences   26   829 - 856   2022.5

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    Other Link: doi.org/10.1007/s40295-022-00315-1

  • Low-Thrust Trajectory Design with Convex Optimization for Libration Point Orbits Reviewed International journal

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

    Journal of Guidance, Control, and Dynamics   45 ( 4 )   623 - 637   2022.4   ISSN:0731-5090 eISSN:1533-3884

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    Language:English   Publishing type:Research paper (scientific journal)   Publisher:Journal of Guidance, Control, and Dynamics  

    In space missions, numerical techniques for minimizing the fuel consumption of spacecraft using low-thrust propulsion are desirable. Among various nonlinear optimization methods, convex optimization has been attracting attention because it allows optimal solutions to emerge robustly and requires short computation times. In particular, trajectory design in the three-body problem near the Lagrange points involves instability and nonlinearity. Hence, this study considers the application of convex optimization to trajectory design with low-thrust propulsion in cislunar space and verifies that this technique performs well, even for sensitive and highly nonlinear dynamics. Specifically, the convex optimization scheme is applied in the transfer from a halo orbit to a near-rectilinear halo orbit where both are periodic as defined in the circular restricted three-body problem. As a further step, the transfer problem is transitioned to an ephemeris model. In addition, extensive investigations of the dependence on various parameters used in convex optimization are conducted, and a trajectory corrections maneuver method is constructed combined with the convex optimization process. This investigation provides valuable insight into the convex optimization technique in the three-body problem and facilitates the estimation of low-thrust trajectory designs for complex space missions.

    DOI: 10.2514/1.G005916

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    Other Link: https://doi.org/10.2514/1.G005916

  • PSO algorithm parameter settings and optimal multi-rotor layout design Reviewed International journal

    #Yuke Huang,#Tatsuya Watanabe, @Mai Bando, @Shinji Hokamoto

    International Journal of Sustainable Aviation   8 ( 2 )   116 - 135   2022.4

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

    #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 33rd International Symposium on Space Technology and Science   2022.3

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

    #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 33rd International Symposium on Space Technology and Science   2022.3

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  • Effects of Rotational Joint Directions of Variable Structure on Non-holonomic Features Reviewed International journal

    #Saki Takeuchi, #Kanta Ikeda, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 33rd International Symposium on Space Technology and Science   2022.3

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  • Design of low energy transfer trajectories from Earth to Europa with ballistic capture Reviewed International journal

    #Kanta Ikeda, #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 33rd International Symposium on Space Technology and Science   2022.3

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

    Sato K., Bando M., Hokamoto S.

    Proceedings of the International Astronautical Congress, IAC   2022-September   2022   ISSN:00741795

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    The fuel minimization problem for a low-thrust spacecraft in a gravity field is formulated as a nonlinear optimal control problem. Euler-Lagrange equation is the necessary condition of a nonlinear optimal control problem and this is the Hamiltonian flow. To find the optimal solution of nonlinear optimal control problem, a two-point boundary value problem for the Euler-Lagrange equation have to be solved. However, since this problem cannot be solved analytically, it is solved numerically, which is generally known to be difficult to find the optimal solution. In this paper, a new method to solve a nonlinear optimal control problem is proposed, which the Koopman Operator theory is applied to Hamiltonian flow. The Koopman Operator is the finite dimensional linear operator in the functional space, so this cannot be calculated. But by using data science, the Koopman Operator of the Hamiltonian flow can be computed approximately. In my method, taking advantage of the linearity of the Koopman Operator, the solution of a nonlinear optimal control problem satisfying the boundary conditions can be easily obtained.

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  • Motion and distance estimation for Unmanned Aerial Vehicle using Wide-Field-Integration of Optic Flow

    Honda Yuki, Bando Mai, Hokamoto Shinji

    Proceedings of the Japan Joint Automatic Control Conference   65 ( 0 )   1450 - 1454   2022

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    Language:Japanese   Publisher:The Japan Joint Automatic Control Conference  

    DOI: 10.11511/jacc.65.0_1450

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  • PSO algorithm parameter settings and optimal multi-rotor layout design

    Huang, YK; Watanabe, T; Bando, M; Hokamoto, S

    INTERNATIONAL JOURNAL OF SUSTAINABLE AVIATION   8 ( 2 )   116 - 135   2022   ISSN:2050-0467 eISSN:2050-0475

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  • INFLUENCE OF OVERALL LAYOUT DESIGN OF COMPOUND MULTIROTOR VEHICLES ON FLIGHT PERFORMANCE

    Huang Y., Bando M., Hokamoto S.

    33rd Congress of the International Council of the Aeronautical Sciences, ICAS 2022   8   5718 - 5731   2022   ISBN:9781713871163

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    In the design of multi-rotor vehicles, it is very important to predesign the overall layout from the perspectives of fluid dynamics, flight dynamics, and control performance. However, there is currently no unified guiding principle. In addition, traditional multi-rotor vehicles are usually not capable of high-speed flight and long endurance. This study discusses a kind of compound multi-rotor vehicle configurations and analyze the influence of the overall layout of multi-rotors on flight performance by utilizing Blade Element Momentum Theory (BEMT) and Particle Swarm Optimization (PSO). First, the flight dynamics model of the compound multi-rotor aircraft is established based on BEMT. Next, by using the PSO algorithm, aiming at the longest cruising distance, some results of proper layouts are shown according to different rotor sizes, positions, wing area, propeller sizes and rotating speeds. Finally, according to the simulation results, the influence of each independent variable on the optimal layout is analyzed. The results show that the method proposed in this paper can be applied as a guideline for the layout design of multi-rotor vehicles, and the compound multi-rotor has better flight performance than the traditional multi-rotor.

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  • Design of Satellites Tours Using Periapsis Poincaré Map in Multibody Dynamics of Jovian System

    Ikeda K., Hiraiwa N., Bando M., Hokamoto S.

    Proceedings of the International Astronautical Congress, IAC   2022-September   2022   ISSN:00741795

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    In trajectory design of satellite tours in multibody dynamical systems such as the Jovian system, it is important to make good use of the gravity of celestial bodies. However, trajectory design is difficult in the Jovian region because the dynamics around this system is highly nonlinear due to the influence of several satellites as well as Jupiter and Sun. This paper proposes a new method for satellites tour design utilizing the Poincaré map which enables us to find the natural or ∆v-assisted satellite tour of the Galilean satellites.

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

    Hiraiwa N., Bando M., Hokamoto S.

    Proceedings of the International Astronautical Congress, IAC   2022-September   2022   ISSN:00741795

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    This paper constructs the framework to design low-thrust minimum-fuel trajectories for a phase-free orbit-to-orbit transfers by leveraging convex optimization and beam search. The proposed method formulates the convex optimization problem involving the departure and arrival phases as optimization parameters; it optimizes the position and velocity of the initial point along the departure orbit and those of the final point along the arrival orbit, as well as the whole transfer trajectory and control inputs. Initial guesses for the optimization problem are generated by choosing intermediate orbits from a family of periodic orbits. Intermediate orbits are located between the departure and arrival orbits to guide a transfer trajectory. The selection of intermediate orbits changes the optimal solution to be obtained. To find the good sequence and number of intermediate orbits, this paper introduces the beam search algorithm to the proposed framework. As an example, the design of low-thrust transfers between halo orbits in the Earth-Moon system is conducted. The obtained results demonstrate that the proposed framework can find the transfer trajectories with lower fuel consumption by adjusting the departure and arrival phases. In conclusion, when the departure and arrival orbits are given, the proposed framework can widely search for the local optimal transfer trajectories between them by utilizing periodic orbits of a certain family.

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

    Kajikawa T., Bando M., Hokamoto S.

    Proceedings of the International Astronautical Congress, IAC   2022-September   2022   ISSN:00741795

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    The dynamics in the vicinity of asteroids is highly uncertain,therefore, guidance and control requires a high degree of autonomy and safety. We propose a method to deal with the uncertainty by applying data-driven methods, which have attracted much attention in recent years. The proposed method enables us to construct the nonlinear dynamics for guidance and control the vicinity of asteroids in real-time using low-dimensional information obtained from on-board sensors, and propose a guidance control strategy for the spacecraft landing based on the obtained accurate dynamics.

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  • 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   ISBN:9781713871163

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    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

  • Semantic Segmentation Technique to Identify Landing Area for Autonomous Spacecraft Reviewed International journal

    #Xin Gao, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 2021 Asia-Pacific International Symposium on Aerospace Technology (APISAT2021)   2021.11

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  • Spacecraft Trajectory Design Using Data-Driven Model Predictive Control Reviewed International journal

    #Yuto Hirose, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 72nd International Astronautical Congress   2021.10

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  • Analysis of Ballistic Escape Based on Lobe Dynamics Reviewed International journal

    #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 72nd International Astronautical Congress   2021.10

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  • Multirotor Vehicles Design Based on Dynamic Manipulability for Underactuated Flying Systems Reviewed International journal

    #Yoshiki Matsumura, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 32nd Congress of the International Council of the Aeronautical Sciences   19 ( 5 )   2021.9

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  • Data-Driven Analysis of Chaotic Orbits in the Circular Restricted Three Body Problem Reviewed International journal

    #Taiki Urashi, @Shinji Hokamoto, @Mai Bando

    Proceedings of the 2021 AAS/AIAA Astrodynamics Specialist Conference   2021.8

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  • Three-Dimensional Attitude Change of Variable Structured Spacecraft by Utilizing Non-holonomic Features International journal

    #Saki Takeuchi, #Kanta Ikeda, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 31st Workshop on JAXA Astrodynamics and Flight Mechanics 2021   2021.8

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

    #Kyosuke Sato, @Shinji Hokamoto, @Mai Bando

    Proceedings of the 2021 AAS/AIAA Astrodynamics Specialist Conference   2021.8

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  • Orbit Maintenance for Quasi-Periodic Orbit in Earth-Moon System Reviewed International journal

    #Yang Zhou, @Mai Bando, @Shinji Hokamoto, Panlong Wu

    Transactions of Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan   19 ( 4 )   562 - 569   2021.7

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    DOI: 10.2322/tastj.19.562

  • Sparse Optimal Control for Nonlinear Trajectory Design in Three-Body Problem Reviewed International journal

    #Yuki Kayama, @Mai Bando, @Shinji Hokamoto

    Transactions of Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan   19 ( 4 )   545 - 552   2021.7

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    DOI: 10.2322/tastj.19.545

  • Optimal Layout Design of Multi-Rotor Vehicle Based on PSO Algorithm Reviewed International journal

    #Yuke Huang, @Mai Bando, @Shinji Hokamoto

    Proceedings of the International Symposium on Aircraft Technology 2021   2021.6

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  • Optimal Layout Design of Multi-Rotor Vehicle Based on PSO Algorithm Reviewed International journal

    #Yuke Huang, @Mai Bando, @Shinji Hokamoto

    Proceedings of the International Symposium on Aircraft Technology 2021   2021.6

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  • Application of Halo Orbit on Extension for Launch Window Limited by Direct Earth-Mars Transfer Reviewed International journal

    #Zhe Xu, @Mai Bando, @Hedeaki Ogawa, @Shinji Hokamoto

    Advances in the Astronautical Sciences   176   55 - 74   2021.2

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  • Obstacle Shape Estimation by Wide-Field-Integration of Optic Flow Reviewed International journal

    #Xiaoxu Feng, @Mai Bando, @Shinji Hokamoto

    Proceedings of the International Symposium on Electric Aviation and Autonomous Systems 2020   93 - 96   2021.1

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  • Three-dimensional Attitude Control of Spacecraft by Three Thrusters Reviewed International journal

    #Yusei Sasaki, #Masato Matsumoto, @Mai Bando, @Shinji Hokamoto

    71st International Astronautical Congress, IAC 2020 Proceedings of the International Astronautical Congress, IAC   2020.10

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    Repository Public URL: http://hdl.handle.net/2324/4479733

  • Trajectory Design to Mars from Earth-Moon System with Three-Dimensional Transit Orbits Reviewed International journal

    #Wataru Noma, #Zhe Xu, @Mai Bando, @Shinji Hokamoto

    71st International Astronautical Congress, IAC 2020 Proceedings of the International Astronautical Congress, IAC   2020.10

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  • Cycler orbit design using low-thrust in the Sun-Earth-Moon system Reviewed International journal

    #Keitaro Miyahara, #Yuki Kayama, @Mai Bando, @Shinji Hokamoto

    71st International Astronautical Congress, IAC 2020 Proceedings of the International Astronautical Congress, IAC   2020.10

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  • Formation Control Using Differential Atmospheric Drag Considering Attitude Constraints Reviewed International journal

    #Takehiro Yasuda, @Mai Bando, @Shinji Hokamoto

    71st International Astronautical Congress, IAC 2020 Proceedings of the International Astronautical Congress, IAC   2020.10

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  • Optimal Landing Problem for a Binary Asteroid System and its Error Sensitivity Reviewed International journal

    #Anviksha Sharma, @Mai Bando, @Shinji Hokamoto, Daniel J. Scheeres

    Proceedings of the SICE Annual Conference 2020   2020.9

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  • Performance Analysis of Low-Gain Feedback for Saturated Differential Drag in a High-precision Orbit Propagator Reviewed International journal

    #Mohamed Shouman, @Mai Bando, @Shinji Hokamoto

    Transactions of the Japan Society for Aeronautical and Space Sciences   63 ( 5 )   243 - 247   2020.9

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    DOI: 10.2322/tjsass.63.243

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

    #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 2020 AAS/AIAA Astrodynamics Specialist Conference   2020.8

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  • Sparse Optimal Control for Nonlinear Trajectory Design in Three-Body Problem Reviewed International journal

    #Yuki Kayama, @Mai Bando, @Shinji Hokamoto

    Transactions of Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan   17 ( 20 )   10 - 17   2020.6

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  • 太陽活動による大気密度の変化を考慮した小型衛星のデオービットに関する考察 Reviewed

    #片山雅之,@外本伸治,@麻生茂,@平山寛

    航空宇宙技術   19   47 - 55   2020.3

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    Language:Japanese   Publishing type:Research paper (scientific journal)  

    DOI: 10.1299/transjsme.15-00550

    Repository Public URL: http://hdl.handle.net/2324/4479600

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

    #Yuki Kayama, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 2020 AIAA SciTech Forum   2020.1

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  • Integrated orbit determination and maintenance in Earth-Moon unstable dynamics environment Reviewed International journal

    #Yang Zhou, @Mai Bando, @Shinji Hokamoto, Panlong Wu

    Acta Astronautica   163   69 - 76   2019.10

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    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

  • Output regulation control for satellite formation flying using differential drag Reviewed International journal

    #Mohamed Shouman, @Mai Bando, @Shinji Hokamoto

    Journal of Guidance, Control, and Dynamics   42 ( 10 )   2220 - 2232   2019.10

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    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

    Repository Public URL: http://hdl.handle.net/2324/4479055

  • Riemannian optimization for spacecraft trajectory design Reviewed International journal

    #Kyosuke Asaki, @Mai Bando, @Shinji Hokamoto

    70th International Astronautical Congress, IAC 2019 Proceedings of the International Astronautical Congress, IAC   2019-October   2019.10

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    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-to-manifold transfers using low-thrust acceleration Reviewed International journal

    #Yuri Hachiya, #Yuki Kayama, @Mai Bando, @Shinji Hokamoto

    70th International Astronautical Congress, IAC 2019 Proceedings of the International Astronautical Congress, IAC   2019-October   2019.10

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    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.

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

    #Yang Zhou, @Mai Bando, @Shinji Hokamoto, Panlong Wu

    70th International Astronautical Congress, IAC 2019 Proceedings of the International Astronautical Congress, IAC   2019-October   2019.10

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    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.

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

    #Yuki Kayama, @Mai Bando, @Shinji Hokamoto

    Proceedings of the SICE Annual Conference 2019   2019.9

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  • Periodic and quasi-periodic orbit design based on the center manifold theory Reviewed International journal

    #Yuki Akiyama, @Mai Bando, @Shinji Hokamoto

    Acta Astronautica   160   672 - 682   2019.7

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    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

  • Design of 3D Transit Orbits and Application to Mission Design International journal

    #Wataru Noma, @Mai Bando, @Shinji Hokamoto

    [第29回アストロダイナミクスシンポジウム講演後刷り集] = The 29th Workshop on JAXA Astrodynamics and Flight Mechanics   2019.7

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    The 29th Workshop on JAXA Astrodynamics and Flight Mechanics 2019 (Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan

  • Performance Analysis of Formation Flying Using Differential Aerodynamic Drag in High Precision Orbit Propagator Reviewed International journal

    #Mohamed Shouman, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 32nd International Symposium on Space Technology and Science   2019.6

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  • Reachability of Hopping Exploration Robot to a Destination Point Under Microgravity Reviewed International journal

    #Yusei Sasaki, #Tomohiro Ishizuka, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 32nd International Symposium on Space Technology and Science   2019.6

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  • Orbit Maintenance for Quasi Periodic Orbits in Earth-Moon System Reviewed International journal

    #Yang Zhou, @Mai Bando, @Shinji Hokamoto, @Penlong Wu

    Proceedings of the 32nd International Symposium on Space Technology and Science   2019.6

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  • Sparse Optimal Control for Nonlinear Trajectory Design in Three-Body Problem Reviewed International journal

    #Yuki Kayama, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 32nd International Symposium on Space Technology and Science   2019.6

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  • Controllability analysis of propellant-free satellite formation flight Reviewed International journal

    #Mohamed Shouman, @Mai Bando, @Shinji Hokamoto

    29th AAS/AIAA Space Flight Mechanics Meeting, 2019 Spaceflight Mechanics 2019   3577 - 3596   2019.1

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    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.

  • Optimal Trajectory Design of Formation Flying based on Attractive Sets Reviewed International journal

    #Motoki Yamane, @Mai Bando, @Shinji Hokamoto

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   17 ( 1 )   96 - 103   2019.1

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    This paper presents a new method of optimal trajectory design for formation flying. Under linearized assumptions and a quadratic performance index, we introduce an attractive set of optimal control based on the linear quadratic regulator theory. The attractive set is defined as a set of all initial states to reach a desired state for a given cost. In particular, we consider attractive sets for two problems: a fixed final-state, fixed final-time problem and an infinite-time problem, and the optimal initial state is found based on the geometry of the attractive set. The optimal trajectories for two problems are evaluated in terms of L1-norm of control input and termination time.

    DOI: 10.2322/tastj.17.96

  • Output regulation control for satellite formation flying using differential drag Reviewed International journal

    #Mohamed Shouman, @Mai Bando, @Shinji Hokamoto

    29th AAS/AIAA Space Flight Mechanics Meeting, 2019 Spaceflight Mechanics 2019   3433 - 3452   2019.1

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    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.

    Repository Public URL: http://hdl.handle.net/2324/4479055

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

    #Yuki Oshima, @Mai Bando, @Shinji Hokamoto

    29th AAS/AIAA Space Flight Mechanics Meeting, 2019 Spaceflight Mechanics 2019   1235 - 1254   2019.1

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    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.

  • Sparse optimal trajectory design in three-body problem Reviewed International journal

    #Yuki Kayama, @Mai Bando, @Shinji Hokamoto

    29th AAS/AIAA Space Flight Mechanics Meeting, 2019 Spaceflight Mechanics 2019   2599 - 2618   2019.1

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    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.

  • 自律飛行体のためのオプティックフローの広域統合法

    #小林 直人, #丸山 慶一郎, @坂東 麻衣, @外本 伸治

    自動制御連合講演会講演論文集   61 ( 0 )   1136 - 1141   2018.11

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    Wide-Field-Integration of optic flow for autonomous vehicles

    DOI: 10.11511/jacc.61.0_1136

  • Optimal trajectory design for safety rendezvous based on sparse modeling Reviewed International journal

    #Satoshi Nagashima, @Mai Bando, @Shinji Hokamoto

    69th International Astronautical Congress: #InvolvingEveryone, IAC 2018 Proceedings of the International Astronautical Congress, IAC   2018-October   2018.10

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    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 Reviewed International journal

    #Yuki Akiyama, @Mai Bando, @Shinji Hokamoto

    69th International Astronautical Congress: #InvolvingEveryone, IAC 2018 Proceedings of the International Astronautical Congress, IAC   2018-October   2018.10

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    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 Reviewed International journal

    #Tomoya Sakamoto, @Mai Bando, @Shinji Hokamoto

    69th International Astronautical Congress: #InvolvingEveryone, IAC 2018 Proceedings of the International Astronautical Congress, IAC   2018-October   2018.10

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    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.

  • Consideration of three-dimensional attitude and position control for a free-floating rigid body using three thrusters Reviewed International journal

    Takashi Matsuno, Yasuhiro Yoshimura, @Shinji Hokamoto

    International Journal of Aerospace Engineering   2018   2018.10

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    The study examines the control algorithm of a three-dimensional attitude and position of a free-floating rigid body with three thruster forces in which the force directions are fixed with respect to the body. This study provides a theory to develop a control method of an underactuated satellite with the minimum thruster number. In the procedure, three switching controllers are used in conjunction with motion planning in the final angular-rate deceleration phase to individually control the six state variables to the target values. The switching controllers have a hierarchical structure by using invariant manifolds as switching surfaces. The state variables in higher class manifolds that include lower class ones are adjusted by repeatedly adding intentional disturbances while the lower class state variables are returned to the original values by using lower class invariant manifolds. This study describes methods to define the invariant manifolds and also the intentional disturbance for achieving the forementioned control strategy. Finally, the motion planning in the angular-rate deceleration phase from a remained single-axis rotation finalizes the six state values of the body to the target values. Numerical simulations verify the proposed method.

    DOI: 10.1155/2018/2825681

  • Optimal Trajectory Design Using Attractive Set on Elliptical Orbit International journal

    #Yuki Kayama, @Mai Bando, @Shinji Hokamoto

    [第28回アストロダイナミクスシンポジウム講演後刷り集] = The 28th Workshop on JAXA Astrodynamics and Flight Mechanics   2018.7

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    The 28th Workshop on JAXA Astrodynamics and Flight Mechanics 2018 (July 30-31, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan

  • Dynamics of a Released Robot on an Asteroid with Small Gravity International journal

    #Yusei Sasaki, @Mai Bando, @Shinji Hokamoto, Fuyuto Terui, Yuichi Tsuda

    [第28回アストロダイナミクスシンポジウム講演後刷り集] = The 28th Workshop on JAXA Astrodynamics and Flight Mechanics   2018.7

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    The 28th Workshop on JAXA Astrodynamics and Flight Mechanics 2018 (July 30-31, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan

  • Controller Performance for Quad-Rotor Vehicles Based on Sliding Mode Control Reviewed International journal

    #Takayoshi Oba, @Mai Bando, @Shinji Hokamoto

    Journal of Robotics and Mechatronics   30 ( 3 )   397 - 405   2018.6

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    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

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

    #Yang Zhou, @Mai Bando, @Shinji Hokamoto, Panlong Wu

    4th IAA Conference on Dynamics and Control of Space Systems, DYCOSS 2018 Dynamics and Control of Space Systems   1827 - 1843   2018.5

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    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.

  • 複眼視覚航法を用いた航空機・宇宙機の運動推定システム Invited Reviewed

    @外本 伸治

    計測と制御 = Journal of the Society of Instrument and Control Engineers   57 ( 4 )   266 - 271   2018.4

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    Motion Estimation for Aerospace Vehicles Based on a Compound Eye System of Flying Insects

    DOI: 10.11499/sicejl.57.266

    Repository Public URL: http://hdl.handle.net/2324/4479732

  • Tether cutting maneuver in swing-by trajectory Reviewed International journal

    #Tsubasa Yamasaki, @Mai Bando, @Shinji Hokamoto

    Acta Astronautica   142   212 - 220   2018.1

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    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

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

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

    56th Annual Conference of the Society of Instrument and Control Engineers of Japan, SICE 2017 2017 56th Annual Conference of the Society of Instrument and Control Engineers of Japan, SICE 2017   2017-November   464 - 469   2017.11

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    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.

    DOI: 10.23919/SICE.2017.8105722

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

    #Motoki Yamane, @Mai Bando, @Shinji Hokamoto

    68th International Astronautical Congress: Unlocking Imagination, Fostering Innovation and Strengthening Security, IAC 2017 68th International Astronautical Congress, IAC 2017 Unlocking Imagination, Fostering Innovation and Strengthening Security   7186 - 7194   2017.9

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    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.

  • Trajectory design to triangular libration points based on resonant orbits Reviewed International journal

    #Nobuki Yamaguchi, @Mai Bando, @Shinji Hokamoto

    68th International Astronautical Congress: Unlocking Imagination, Fostering Innovation and Strengthening Security, IAC 2017 68th International Astronautical Congress, IAC 2017 Unlocking Imagination, Fostering Innovation and Strengthening Security   7507 - 7518   2017.9

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    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.

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

    #Yuki Akiyama, @Mai Bando, @Shinji Hokamoto

    68th International Astronautical Congress: Unlocking Imagination, Fostering Innovation and Strengthening Security, IAC 2017 68th International Astronautical Congress, IAC 2017 Unlocking Imagination, Fostering Innovation and Strengthening Security   750 - 762   2017.9

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    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.

  • Optic flow-based navigation system for planetary rovers Reviewed International journal

    #Naoto Kobayashi, @Mai Bando, @Shinji Hokamoto

    68th International Astronautical Congress: Unlocking Imagination, Fostering Innovation and Strengthening Security, IAC 2017 68th International Astronautical Congress, IAC 2017 Unlocking Imagination, Fostering Innovation and Strengthening Security   2839 - 2847   2017.9

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    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.

  • Improvement of Wide-Field-Integration of Optic Flow Considering Practical Sensor Restrictions Reviewed International journal

    #Naoto Kobayashi, @Mai Bando, @Shinji Hokamoto

    Journal of Mechanical Engineering and Automation   Vol.7 ( No.2 )   53 - 62   2017.5

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    DOI: 10.5923

  • Trajectory design using the center manifold theory in the circular restricted three-body problem Reviewed International journal

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

    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan   Vol. 14   Pd_151 - Pd_158   2016.12

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  • Design of earth-moon cyclers using primer vector theory Reviewed International journal

    #Sho Hayashida, @Mai Bando, @Shinji Hokamoto

    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan   Vol. 14   Pd_159 - Pd_165   2016.12

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  • Experimental Verification of Wide-Field-Integration of Optic Flow for State Estimation Reviewed International journal

    #Naoto Kobayashi, #Masataka Oishi, @Yutaka Kinjo, @Shinji Hokamoto

    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan   Vol. 14   Pd63 - Pd68   2016.11

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  • A Novel Attitude Estimation Method Based on Wide-Field-Integration of Optic Flow for Autonomous Navigation Reviewed International journal

    #Naoto Kobayashi, #Ryusuke Nakata, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 2016 Asia-Pacific International Symposium on Aerospace Technology (APISAT)   Vol. 14   Pd63 - Pd68   2016.10

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  • Periodic Orbits Design based on the Center Manifold Theory in the Circular Restricted Three-Body Problem Reviewed International journal

    #Yuki Akiyama, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 67th International Astronautical Congress   2016.9

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  • Powered Swing-by Using Tether Cutting Reviewed International journal

    #Tsubasa Yamasaki, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 67th International Astronautical Congress   2016.9

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  • LRF Based Autonomous Navigation System Measuring on Moving Rover Reviewed International journal

    #Kai Yun, #Shinya Katoku, @Yutaka Kinjo, @Shinji Hokamoto

    Proceedings of the 13th International Symposium on Artificial Intelligence, Robotics and Automation in Space (i-SAIRAS)   2016.6

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  • Global Trajectory Design for Position and Attitude Control of an Underactuated Satellite Reviewed International journal

    Yasuhiro Yoshimura, Takashi Matsuno, @Shinji Hokamoto

    Transactions of the Japan Society for Aeronautical and Space Sciences   59 ( 3 )   107 - 114   2016.5

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  • On the possibility of using small asteroids for deflecting near-Earth asteroids Reviewed International journal

    #Yuki Akiyama, @Mai Bando, @Shinji Hokamoto

    Advances in Space Research   57 ( 8 )   1820 - 1831   2016.4

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    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

  • 小型探査ローバのためのレーザーレンジファインダーによる環境認識 Reviewed

    #雲 凱, @外本 伸治

    日本機械学会論文集   82 ( 835 )   15 - 00550-15-00550   2016.3

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    Environment recognition through laser-range-finder for small exploration rover

    DOI: 10.1299/transjsme.15-00550

    Repository Public URL: http://hdl.handle.net/2324/4479599

  • Global trajectory design for position and attitude control of an underactuated satellite Reviewed International journal

    #Yasuhiro Yoshimura, #Takashi Matsuno, @Shinji Hokamoto

    Transactions of the Japan Society for Aeronautical and Space Sciences   59 ( 3 )   107 - 114   2016.1

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    Underactuated control offers fault-tolerance for satellite systems, which not only enables the position and attitude control of a satellite with fewer thrusters, but also can reduce the number of thrusters equipped on the satellite even when considering the need for backups. Due to having fewer thrusters, the coupling effect between the translational motion and rotational motion of the satellite cannot be avoided, and the coupled motion must be considered in control procedures. This paper presents a global trajectory design procedure required for the position and attitude control of an underactuated satellite. The satellite has four thrusters with constant thrust magnitudes on one plane of the satellite body. Then, an analytical solution for coupled motion between the rotation and translation of the satellite is obtained using three-step maneuvers of attitude control. The trajectory design based on the analytical solution is shown for the control of translational and rotational motion in three dimensions. Finally, a numerical simulation is performed to verify the effectiveness of the proposed design procedure.

    DOI: 10.2322/tjsass.59.107

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

    @Mai Bando, #Hamidreza Nemati, @Shinji Hokamoto

    Proceedings of the AAS/AIAA Astrodynamics Specialist Conference, ASC 2015   785 - 804   2016.1

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    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.

  • Design of Sliding Mode Controllers for Formation Flying along Unstable Periodic Orbits in CR3BP Reviewed International journal

    #Hamidreza Nemati, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 66th International Astronautical Congress   2015.10

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  • Motion estimation of autonomous spacecraft near asteroid using wide-field-integration of optic flow Reviewed International journal

    #Naoto Kobayashi, #Masataka Oishi, Yutaka Kinjo, Daisuke Kubo, @Shinji Hokamoto

    Proceedings of the 25th International Symposium on Space Flight Dynamics   2015.10

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  • Station-keeping and formation flying for periodic orbit around Lagrangian points by Fourier series Reviewed International journal

    #Yuki Akiyama, @Mai Bando, @Shinji Hokamoto

    Proceedings of the 25th International Symposium on Space Flight Dynamics   2015.10

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  • Satellite Formation-Keeping about Libration Points in the Presence of System Uncertainties Reviewed International journal

    @Mai Bando, #Hamidreza Nemati, @Shinji Hokamoto

    Proceedings of the AAS/AIAA Astrodynamics Specialist Conference   2015.8

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  • Experimental Verification on Enabling Long Distance Travel for Planetary Rover Using Scanning LRF System Reviewed International journal

    #Kai Yun, @Yutaka Kinjo, @Shinji Hokamoto

    Proceedings of the 30th International Symposium on Space Technology and Science   2015.7

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  • 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) Reviewed

    #伊達 直輝, @坂東 麻衣, @外本 伸治

    日本機械学会論文集   81 ( 826 )   2015.6

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  • 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) Reviewed

    #伊達 直輝, @坂東 麻衣, @外本 伸治

    日本機械学会論文集   81 ( 826 )   2015.6

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  • New Chattering Attenuation Sliding Mode Control of a Flexible Spacecraft Reviewed International journal

    #Hamidreza Nemati, @Shinji Hokamoto

    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology   12 ( ists29 )   Pd_71 - Pd_77   2014.10

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

    @Mai Bando, #Naoki Date, @Shinji Hokamoto

    Proceedings of the 65th International Astronautical Congress   2014.9

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

    @Shinji Hokamoto, #Masataka Oishi, #Naoto Kobayashi, @Mai Bando

    Proceedings of the 65th International Astronautical Congress   2014.9

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  • Attitude Angle Estimation of Space Probe through Wide-Field Integration of Optic Flow Reviewed International journal

    #Hirofumi Sakamoto, @Shinji Hokamoto

    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology   12 ( ists29 )   Pd_41 - Pd_46   2014.6

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  • Realistic terrain reconstruction method by using laser-range-finder Reviewed International journal

    #Kai Yun, #Keita Sakurai, @Shinji Hokamoto

    Proceedings of the 14th International Space Conference of Pacific-basin Societies,   2014.5

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  • Relative Position and Attitude Control of a Satellite with Unilateral Inputs Reviewed International journal

    #Yasuhiro Yoshimura, #Shunsuke Tsuge, @Shinji Hokamoto

    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology   12 ( ists29 )   Pd_11 - Pd_17   2014.4

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  • 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ンシップ Reviewed

    @坂東 麻衣, @外本 伸治

    工学教育   62 ( 2 )   2_73 - 2_76   2014.3

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    Circular Restricted Three-body Problem as a Subject of Internship in the Field of Aeronautics and Astronautics

    DOI: 10.4307/jsee.62.2_73

  • Geometric conditions of thrusters for 3D attitude control of a free-floating rigid spacecraft Reviewed International journal

    #Takashi Matsuno, #Yasuhiro Yoshimura, @Shinji Hokamoto

    Mathematics in Engineering, Science and Aerospace   15 ( 1 )   83 - 95   2014.2

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  • Design Procedure of Chattering Attenuation Sliding Mode Attitude Control of a Satellite System Reviewed International journal

    #Hamidreza Nemati, @Shinji Hokamoto

    Advances in the Astronautical Sciences   152   3533 - 3541   2014.1

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  • Robust deflection strategies of Near Earth asteroids under uncertainties Reviewed International journal

    @Mai Bando, #Yuki Akiyama, @Shinji Hokamoto

    Proceedings of the 24th AAS/AIAA Space Flight Mechanics Meeting, 2014   1165 - 1181   2014.1

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    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.

  • Relative Position and Attitude Control of a Satellite with Unilateral Inputs Reviewed International journal

    #Yasuhiro Yoshimura, #Shunsuke Tsuge, @Shinji Hokamoto

    Proceedings of the 29th International Symposium on Space Technology and Science   2013.6

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  • Attitude and position control for under actuated satellite by ON/OFF thrusters Reviewed International journal

    #Takashi Matsuno, #Yasuhiro Yoshimura, @Shinji Hokamoto

    Nihon Kikai Gakkai Ronbunshu, C Hen/Transactions of the Japan Society of Mechanical Engineers, Part C   79 ( 798 )   225 - 235   2013.5

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    This study proposes a new control method for under-actuated planar satellites having body-fixed thrusters that can generate unilateral and constant forces. The proposed method is applicable when the thrusters are not balanced, which means a rotational motion is inevitably induced whenever the thrusters are turned on. By applying the method, the position and attitude of any planar satellite can be controlled to arbitrary target states so long as a controllability condition is satisfied. The control logic is based on a switching control using plural manifolds. First, the satellite is transferred to an initial manifold, and then it moves to another manifold while decreasing its velocity and approaching the target states. The ON/OFF timing of the thrusters to transfer among the manifolds is explicitly specified in this paper. A numerical simulation validates the proposed control logic.

    DOI: 10.1299/kikaic.79.225

  • State Estimation of Planetary Landing Vehicles with Wide-Field Integration of Optic Flow International journal

    #Hirofumi Sakamoto, #Takumi Kanazawa, @Shinji Hokamoto

    Advances in the Astronautical Sciences   Vol. 146   2013.3

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  • ON-OFFスラスター出力による二次元劣駆動衛星の姿勢と位置の制御 Reviewed

    #松野崇, #吉村康広, @外本 伸治

    日本機械学会論文集 (C1編)   225 - 235   2013.2

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    DOI: No.2012-JCR-0553

  • Chattering attenuation sliding mode control of a satellite's attitude Reviewed International journal

    #Hamidreza Nemati, @Shinji Hokamoto

    23rd AAS/AIAA Space Flight Mechanics Meeting, Spaceflight Mechanics 2013 Advances in the Astronautical Sciences   148   1369 - 1376   2013.2

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    This paper develops a new robust nonlinear control algorithm based on the theory of sliding mode to control the attitude of a satellite. The system comprises a satellite with three pairs of thrusters on the satellite's principal axes. Since conventional sliding mode controllers include a discontinuous function, a significant problem called chattering can occur. The main purpose of this paper is to design a new switching function in order to alleviate this drawback. Moreover, for increasing the robustness of the proposed controller, a new slope-varying hyperbolic function is utilized. Simulation results highlight the effectiveness of the proposed method.

  • State estimation of planetary landing vehicles with wide-field integration of optic flow Reviewed International journal

    #Hirofumi Sakamoto, #Takumi Kanazawa, @Shinji Hokamoto

    13th International Space Conference of Pacific-Basin Societies, ISCOPS 2012 Space for Our Future - Advances in the Astronautical Sciences: Proceedings of the 13th International Conference of Pacific-Basin Societies, ISCOPS 2012   146   57 - 69   2013.1

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    In this paper, we apply Wide-Field integration (WFI) of optic flow for the state estimation of a planetary landing vehicle. This study utilizes nonlinear expressions for the Fourier coefficients of the optic flow instead of linearized expressions. By using the nonlinear expressions, it is shown that the vehicle's attitude angles can be estimated as well as its velocity components. First this paper deals with a two-dimensional model and explains how to estimate state variables. Then two three-dimensional models are discussed. Numerical simulation results are shown to evaluate the estimation accuracy.

  • Application of wide-field integration of optic flow to proximity operations and landing for space exploration missions Reviewed International journal

    #Michael A. Shoemaker, @Shinji Hokamoto

    2011 AAS/AIAA Astrodynamics Specialist Conference, ASTRODYNAMICS 2011 ASTRODYNAMICS 2011 - Advances in the Astronautical Sciences Proceedings of the AAS/AIAA Astrodynamics Specialist Conference   23 - 36   2012.12

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    New advances in vision-based navigation for micro air vehicles (MAVs) have been inspired by the biological systems of flying insects and the use of optic flow. These biologically-inspired optical sensor systems for MAVs are computationally efficient and have low mass and low power consumption, which makes them attractive for small spacecraft. This study explores the applicability of the wide-field integration (WFI) of optic flow to a spacecraft operating in close proximity to an asteroid. In contrast with past WFI work, this study uses an asteroid-relative reference trajectory and known a priori environment model such that the optimal sensitivity functions are recalculated onboard the vehicle at each time step. Numerical simulations with computer-generated images of the asteroid surface are used to estimate the vehicle's translational and angular velocities. Although the accuracy of these state estimates are reasonable considering the noise in the optic flow measurements, the onboard recalculation of the sensitivity functions for this time-varying scenario add computational burden which negates the main advantage of the WFI method. Hence, future applications to time-invariant scenarios for small-body missions are also discussed.

  • Relative Attitude and Orbital Control with a Fewer Thrusters for Rendezvous-Docking Reviewed International journal

    #Shunsuke Tsuge, @Shinji Hokamoto

    Proceedings of the Asia-Pacific International Symposium on Aerospace Technology   2012.11

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  • Study on a Reasonable Locomotion of a Multi-Legged Rover Using its Dynamic Motion Reviewed International journal

    #Shinji Nishikori, @Shinji Hokamoto, Takashi Kubota

    Proceedings of the International Symposium on Artificial Intelligence, Robotics and Automation in Space   2012.9

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  • Satellite position and attitude control by on-off thrusters considering mass change Reviewed International journal

    #Yasuhiro Yoshimura, #Takashi Matsuno, @Shinji Hokamoto

    2011 AAS/AIAA Astrodynamics Specialist Conference, ASTRODYNAMICS 2011 ASTRODYNAMICS 2011 - Advances in the Astronautical Sciences Proceedings of the AAS/AIAA Astrodynamics Specialist Conference   142   2953 - 2964   2012.2

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    This paper deals with the two-dimensional position and attitude control of a satellite by on-off thrusters which are fixed to the satellite's body. Since the thrusters generate constant and unilateral forces, the equations of motion form nonholonomic constraint and cannot be integrated. Furthermore, the satellite's mass changes due to the fuel consumption. Utilizing Fresnel integrals and the partial integrals, we derive the approximate analytic solution considering the satellite's mass change to achieve a specified satellite's position and attitude. The accuracy of the proposed approximate technique is verified by applying it to a condition considered in SLIM project of JAXA.

  • Position and attitude control of an underactuated satellite with constant thrust Reviewed International journal

    #Yasuhiro Yoshimura, #Takashi Matsuno, @Shinji Hokamoto

    Proceedings of the AIAA Guidance, Navigation, and Control Conference 2011   2011.12

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    This paper discusses a position and attitude control problem of an underactuated satellite which uses on-off thruster mechanisms for control. Each thrusters has constant orientation relative to the satellite's body, and can generate only unilateral forces. The purpose of this paper is to clarify the control law for simultaneous position and attitude control for this type of satellite configuration. Considering the input constraints, we obtain the analytical solutions of the satellite's translational and rotational motion. Then the control procedure utilizing an invariant manifold is derived. Some numerical simulations are shown to verify the effectiveness of the proposed controller.

  • Three dimensional attitude control of an underactuated satellite with thrusters Reviewed International journal

    #Yasuhiro Yoshimura, #Takashi Matsuno, @Shinji Hokamoto

    International Journal of Automation Technology   5 ( 6 )   892 - 899   2011.11

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    This paper deals with the three-dimensional attitude control of an underactuated satellite equipped with thrusters whose force directions are fixed to the satellite. First, the necessary number of thrusters for the satellite's attitude control is discussed utilizing the Minkowski-Farkas theorem. Then, using the wz parameters for a satellite's attitude expression, this paper proposes a non holonomic attitude controller which is effective for any satellite regardless of its moment of inertia. Numerical simulation demonstrates the effectiveness of the proposed controller. Furthermore, the efficiency of the controller for different thruster positions is also discussed.

    DOI: 10.20965/ijat.2011.p0892

  • 状態フィードバックによる2つのスラスターをもつ衛星の面内位置・姿勢制御 Reviewed

    #松野 崇, #吉村 康広, @外本 伸治

    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences   59 ( 690 )   183 - 189   2011.7

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    Position and Attitude Feedback Controller of a Planar Satellite with Two Thrusters

    DOI: 10.2322/jjsass.59.183

  • 3-D Attitude Control of an Underactuated Satellite with Constant Inputs Reviewed International journal

    #Yasuhiro Yoshimura, #Takashi Matsuno, @Shinji Hokamoto

    Proceedings of the 28th International Symposium on Space Technology and Science   2011.6

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  • Relative Navigation Near Asteroid Using Wide-Field Integration of Optic Flow Reviewed International journal

    #Michael Shoemaker, @Shinji Hokamoto

    Proceedings of the 28th International Symposium on Space Technology and Science   2011.6

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  • Genetic-Algorithm-Based Rendezvous Trajectory Design for Multiple Active Debris Removal Reviewed International journal

    @Shinji Hokamoto, #Junko Murakami

    Proceedings of the 28th International Symposium on Space Technology and Science   2011.6

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  • Kinematic discussion and development of a multi-legged planetary exploration rover with an isotropic leg arrangement Reviewed International journal

    #Shinji Nishikori, @Shinji Hokamoto, Takashi Kubota

    Advanced Robotics   25 ( 6-7 )   789 - 804   2011.4

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    This study deals with a multi-legged planetary rover with a spherically isotropic leg arrangement. The legged rover is a reliable rover system for exploration on rough terrains, because it can continue walking even after overturning. Moreover, the legged rover can also show a rotational motion by utilizing its isotropic shape. This paper discusses the walking performance of two types of rover shapes: one has a six-leg arrangement based on a regular octahedron and the other has an eight-leg arrangement based on a regular hexahedron. The design procedure of the proposed rover is explained, and a test-bed system, which is developed to demonstrate the fundamental motions, is also presented.

    DOI: 10.1163/016918611X563300

  • Approach for Optimal Multi-Rendezvous Trajectory Design for Active Debris Removal International journal

    #Junko Murakami, @Shinji Hokamoto

    Proceedings of the 20th Workshop on JAXA Astrodynamics and Flight Mechanics   2011.3

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  • A Novel Chattering-Free Sliding Mode Controller for Attitude Control of a Microsatellite International journal

    #Hamidreza Nemati, @Shinji Hokamoto

    Proceedings of the 22nd Workshop on JAXA Astrodynamics and Flight Mechanics   249 - 254   2011.3

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  • Position and Attitude Control of a Free-Floating Planar Satellite Controlled by Thrusters Reviewed International journal

    @Shinji Hokamoto, #Masaoki Iwase

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   8 ( 27 )   Pd_1 - Pd_7   2011.1

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    This study deals with the in-plane motion of a free-floating satellite equipped with thrusters whose force directions are fixed to the satellite. The system's governing equations form nonintegrable second-order “nonholonomic” constraints due to the fixed force directions to the satellite. This paper treats a satellite with three thrusters, and at first assumes that the magnitudes of the thrusters can continuously be changed from zero to a specified positive value. Under the assumption, it is shown that the nonholonomic governing equations can be transformed into holonomic ones by a feedback of the rotational angular velocity. Then, this paper shows the procedures to control the satellite's position and attitude precisely. Finally, we restrict the magnitude of the thrusters to be constant, and discuss the control techniques for such systems.

    DOI: 10.2322/tastj.8.Pd_1

  • Position and attitude control of an underactuated satellite with constant thrust Reviewed International journal

    #Yasuhiro Yoshimura, #Takashi Matsuno, @Shinji Hokamoto

    Proceedings of the AIAA Guidance, Navigation, and Control Conference 2011   2011.1

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    This paper discusses a position and attitude control problem of an underactuated satellite which uses on-off thruster mechanisms for control. Each thrusters has constant orientation relative to the satellite's body, and can generate only unilateral forces. The purpose of this paper is to clarify the control law for simultaneous position and attitude control for this type of satellite configuration. Considering the input constraints, we obtain the analytical solutions of the satellite's translational and rotational motion. Then the control procedure utilizing an invariant manifold is derived. Some numerical simulations are shown to verify the effectiveness of the proposed controller.

    DOI: 10.2514/6.2011-6352

  • Evaluation on Efficient Attitude of a Multi-Legged Planetary Exploration Rover with Isotropic Leg Arrangement International journal

    #Shinji Nishikori, @Shinji Hokamoto

    Advances in the Astronautical Sciences   138   2010.12

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  • Position and attitude control of a planar satellite by two constant force thrusters Reviewed International journal

    #Takashi Matsuno, @Shinji Hokamoto

    Proceedings of the AIAA/AAS Astrodynamics Specialist Conference 2010   2010.12

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    This study deals with the in-plane motion of a free-floating planar satellite equipped with two thrusters having constant force magnitude and fixed direction with respect to the satellite. This paper discusses the motion of such a satellite, and proposes a simple trajectory design procedure for controlling both the satellite's position and attitude angle. First, this paper investigates the motion for constant force magnitude. A drift-less rotational maneuver forms an "invariant manifold", which can be used to design a trajectory for the target state. Then, the condition of the input profile for the drift-less motion is discussed. Furthermore, this paper explains an advantage of a rotational maneuver which intentionally generates drift velocity.

    DOI: 10.2514/6.2010-8393

  • Interplanetary trajectory design of solar sail spacecraft utilizing an invariant manifold Reviewed International journal

    #Yutaro Ishida, @Shinji Hokamoto

    Proceedings of the AIAA/AAS Astrodynamics Specialist Conference 2010   2010.12

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    This paper deals with an in-plane trajectory design method for a solar sail spacecraft to rendezvous with a planet. In the interplanetary rendezvous problem, the spacecraft's velocity must coincide with the orbital velocity of the planet when it reaches the planet's orbit. This paper proposes a trajectory design procedure that utilizes an invariant manifold for a specified control profile to reach a target orbit. The proposed strategy allows a rendezvous to a planet in an elliptical orbit by adjusting the launch timing of the sailcraft when it starts from a circular orbit. Numerical simulations demonstrate the validity of the proposed procedure.

    DOI: 10.2514/6.2010-8137

  • Evaluation of efficient attitude of a multi-legged planetary exploration rover with isotropic leg arrangement Reviewed International journal

    #Shinji Nishikori, @Shinji Hokamoto

    12th International Conference of Pacific-Basin Societies, ISCOPS Applications of Space Technology for Humanity - Advances in the Astronautical Sciences Proceedings of the 12th International Conference of Pacific-Basin Societies, ISCOPS   667 - 679   2010.12

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    This study deals with a multi-legged planetary rover with a spherically isotropic leg arrangement. This robot is a reliable system for the exploration on rough terrains, because the rover can continue walking even after overturning. Moreover, this rover can exhibit a rotational motion by utilizing its isotropic shape in addition to quadruped walking motion. This paper discusses two rotational motions; a quasi-static rotational motion and a dynamic rotational motion. This paper investigates reasonable attitudes for the quasi-static rotational motion from the view point of the energy consumption required for traveling. For the dynamic rotational motion, adequate attitudes to resist the shock for kicking and touchdown are discussed.

  • Three Dimensional Attitude Control of an Underactuated Satellite with Thrusters Reviewed International journal

    #Yasuhiro Yoshimura, #Takashi Matsuno, @Shinji Hokamoto

    Proceedings of the 4th Asia International Symposium on Mechatronics   2010.12

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  • Approach for optimal multi-rendezvous trajectory design for active debris removal Reviewed International journal

    #Junko Murakami, @Shinji Hokamoto

    Proceedings of the 61st International Astronautical Congress 2010, IAC 2010   7   6013 - 6018   2010.10

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    This paper proposes a method for designing a rendezvous trajectory for active debris removal using Lambert's problem. For the active debris removal mission, it is preferable to remove multiple target debris in sequence during a single mission with a low required ΔV. The trajectory design process for the removal mission consists of the following three steps: selection of the removal target debris from among many candidates; specification of the rendezvous order for the chosen debris; and design of the rendezvous transfer orbits. Since Lambert's problem has multiple solutions, the design process requires a large number of computations. By limiting the debris removal mission to low-Earth orbit, this paper proposes a procedure to specify a unique solution for Lambert's problem. To demonstrate the feasibility of the proposed procedure, this paper deals with a simple rendezvous for three debris as an example, and applies a genetic algorithm to find a solution having a reasonable ΔV with low calculation cost. Numerical results show that the proposed design procedure can find a reasonable solution for the multiple rendezvous problem.

  • Study on Efficient Attitude of a Multi-Legged Planetary Exploration Rover with Isotropic Leg Arrangement Reviewed International journal

    #Shinji Nishikori, @Shinji Hokamoto, Takashi Kubota

    Proceedings of the the 10th International Symposium on Artificial Intelligence, Robotics and Automation in Space   2010.8

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  • Study on Efficient Walking Attitude of Planetary Exploration Rover with Spherically Isotropic Leg Arrangement International journal

    #Shinji Nishikori, @Shinji Hokamoto, Takashi Kubota

    Proceedings of the 19th Workshop on JAXA Astrodynamics and Flight Mechanics   149 - 154   2010.3

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  • Position and attitude feedback controller of a planar satellite with two thrusters Reviewed International journal

    #Takashi Matsuno, @Shinji Hokamoto

    Proceedings of the ICROS-SICE International Joint Conference 2009   4206 - 4211   2009.12

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    This paper proposes a feedback control method for the in-plane motion of a satellite equipped with two thrusters, whose force directions are fixed to the satellite. The satellite's equations of motion have second-order nonholonomic constraints. This paper utilizes an invariant manifold and develops a feedback controller based on the Lyapunov's second method. The developed controller can control the satellite's state composed of six components for the position and attitude angle by two thruster systems. Furthermore, the controller has robustness for the system's modeling errors. Some simulations results are shown to demonstrate the effectiveness of the developed controller.

  • Trajectory Design of Solar Sail Spacecraft for Interplanetary Rendezvous Missions Reviewed International journal

    @Shinji Hokamoto, #Koji Sachimoto, @Koki Fujita

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN   7 ( 26 )   Pd_37 - Pd_42   2009.8

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    This paper deals with in-plane motion of a solar sail spacecraft to rendezvous with a planet. In the interplanetary rendezvous problem, the spacecraft's velocity must coincide with the orbital velocity of the planet when it reaches the planet's orbit. Thus, the spacecraft's radial and tangential velocities as well as its orbital radius are controlled by one control input, i.e. the spacecraft's pitch angle. In this paper, we propose a trajectory design method which can reduce the amount of computational iterations considerably. This is applied to a rendezvous mission to a planet in a circular orbit and is achieved by utilizing locally optimal control techniques. A hidden problem in the method is pointed out, and a countermeasure is proposed. Then, numerical results of the proposed method are shown and compared with the results obtained by a fully numerical iteration method. Finally, some mathematical properties of a sailcraft's governing equations are discussed in the framework of nonlinear control theory. We show analytically that a solar sail spacecraft can rendezvous with any planet in any elliptical orbit by using only pitch angle control.

    DOI: 10.2322/tstj.7.Pd_37

  • Roll Angular Momentum Enhancement of a Tethered Satellite System for Transfer in Different Orbit Plane Reviewed International journal

    #Masaoki Iwase, @Shinji Hokamoto

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN   7 ( 26 )   Pd_57 - Pd_62   2009.8

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    This paper discusses the in-planar and out-of-planar dynamics of a Tethered Satellite System (TSS), which aims to inject a satellite into a different orbit plane. The orbital transfer is achieved by only varying the tether length in a gravity gradient field. A previous work treating in-plane orbital transfer induces the system's pitch motion, and proposes a control procedure. For a transfer in a different orbit plane, the system's roll motion must be controlled as well as its pitch motion. First, this paper shows the system's governing equations of motion, and compares the features of the roll motion with its pitch motion. Then, a control method is proposed to increase the angular momentum of the roll motion. Finally, the effectiveness of the proposed method is demonstrated by numerical simulations.

    DOI: 10.2322/tstj.7.Pd_57

  • テザーシステムを用いた衛星の軌道変更のためのフィードバック制御 Reviewed

    @外本 伸治, #古賀 笑平

    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences   57 ( 666 )   301 - 307   2009.7

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    Feedback Control for Satellite Orbit Transfer by a Tethered Satellite System

    DOI: 10.2322/jjsass.57.301

  • Position and Attitude Control of a Free-Floating Planar Satellite Controlled by Thrusters Reviewed International journal

    @Shinji Hokamoto, #Masaoki Iwase

    Proceedings of the 27th International Symposium on Space Technology and Science   2009.5

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  • Non-holonomic Analysis and Control of a Thruster Driven Free-Floating Satellite International journal

    @Shinji Hokamoto, #Masaoki Iwase, #Junya Fujii

    Proceedings of the 18th Workshop on JAXA Astrodynamics and Flight Mechanics   189 - 194   2009.3

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  • Position and attitude control of a planar satellite by two thrusters Reviewed International journal

    @Shinji Hokamoto, #Masaoki Iwase

    Proceedings of the AIAA Guidance, Navigation, and Control Conference and Exhibit   2009.1

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    This study deals with the in-plane motion of a free-floating planar satellite equipped with two thrusters whose force directions are fixed with respect to the satellite. The system's governing equations form non-integrable second-order "nonholonomic" constraints due to the fixed force directions within the satellite. First, this paper shows the general expressions of the system's equations of motion, and shows that its translational and rotational motions can not be controlled independently. Next, by assuming an imaginary thruster controlled by a feedback law, we transform the nonholonomic constraints into holonomic ones. This concept is followed by a strategy to achieve a rotational motion without drift for a satellite system with two fixed thrusters. Afterwards, this paper shows a procedure for precise control of the position and attitude of the system. The validity of the proposed method is verified by numerical simulations. Finally, this paper discusses the special case when the magnitude of the thruster force is taken constant.

    DOI: 10.2514/6.2009-6183

  • Kinematic Discussion and Development of a Multi-Legged Planetary Exploration Rover with Isotropic Leg Arrangement Reviewed International journal

    #Shinji Nishikori, @Shinji Hokamoto

    Proceedings of the 3rd Asia International Symposium on Mechatronics   170 - 175   2008.8

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  • テザー長変化によるピッチング運動制御を利用したテザー衛星の軌道変換 Reviewed

    #柴田 成豊, @外本 伸治

    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences   56 ( 654 )   308 - 314   2008.7

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    Orbital Transfer of a Tethered Satellite System Using Pitching Motion Control through Tether Length Variation

    DOI: 10.2322/jjsass.56.308

  • Tether Length Control for Orbital Transfer of Tethered Satellite International journal

    @Shinji Hokamoto, #Naritoyo Shibata

    Proceedings of the 17th Workshop on JAXA Astrodynamics and Flight Mechanics   261 - 266   2008.3

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  • A Consideration on Lander’s Motion Estimation from Range Image Sequence Utilizing LRF International journal

    @Koki Fujita, @Shinji Hokamoto

    Proceedings of the 17th Workshop on JAXA Astrodynamics and Flight Mechanics   194 - 199   2008.3

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  • 非ホロノミック拘束に着目した剛体衛星軌道のフィードバック制御 Reviewed

    @藤田 浩輝, @外本 伸治

    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences   56 ( 648 )   1 - 7   2008.1

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    Feedback Control of Orbital Parameters for a Rigid Satellite under Nonholonomic Constraint

    DOI: 10.2322/jjsass.56.1

  • Control Laws for Orbital Parameters of Rigid Satellite System Considering Nonholonomic Constraint Reviewed International journal

    @Koki Fujita, @Shinji Hokamoto

    Proceedings of the Guidance, Navigation, and Control Conference   2007.8

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  • Control laws for orbital parameters of rigid satellite system considering nonholonomic constraint Reviewed International journal

    @Koki Fujita, @Shinji Hokamoto

    Proceedings of the AIAA Guidance, Navigation, and Control Conference 2007   5073 - 5085   2007.8

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    This study deals with orbital control of a rigid coplanar dumbbell-type satellite system. While most of the previous work for orbital transfer aim at changing just one parameter of the orbital elements, by applying a nonlinear method, this study proposes two control laws to change an orbit into a prescribed one defined by its orbital elements: semi-major axis (equivalent to semilatus rectum), eccentricity and argument of pericenter. First controller is developed from a two-step approach combining a solution for a chained formed system and numerical modification based on motion planning. Another is a feedback controller, which can compensate model uncertainty or disturbance. These two controllers can be combined to a complementary control technique. The effectiveness of the proposed control laws are demonstrated through a series of numerical simulations.

    DOI: 10.2514/6.2007-6849

  • Position and Attitude Control of a Planar Satellite by Two Thrusters Reviewed International journal

    @Shinji Hokamoto, #Masaoki Iwase

    Proceedings of the Guidance, Navigation, and Control Conference   2007.8

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  • Considerations on a feedback control system for a space robot reorientation Reviewed International journal

    @Shinji Hokamoto, #Toshirou Funasako

    Proceedings of the AIAA/AAS Astrodynamics Specialist Conference, 2006   1205 - 1213   2006.8

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    This study deals with feedback control of reorientation of a planar space robot. Mukherjee and Kamon propose to define 'a radially isometric orientation' and successfully establish a smooth time invariant control system. However the proposed controller suffers from slow rate of convergence for a desired configuration being placed on or near a zero-holonomy curve. They also propose two modified controllers for such configurations, but stability problem for the modified controllers remains future work and a criterion for choosing the original or modified controller is not discussed for general configurations. This paper proposes to adopt a 'moving desired configuration' for convergence to any desired configuration. The moving desired configuration is designed to move to a 'real' desired configuration with the system states close to an invariant manifold. The paper describes how to define the invariant manifold and how to move the moving desired point to the real one.

    DOI: 10.2514/6.2006-6519

  • Orbital control of a tethered satellite system using tether-length variations Reviewed International journal

    @Shinji Hokamoto, #Kazuo Setoyama

    Proceedings of the 56th International Astronautical Congress 2005   5   3105 - 3111   2005.10

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    This study deals with orbital transfer of a tethered satellite system into a specified orbit (defined in the equatorial plane as a set of semilatus rectum, eccentricity, and augment of pericenter,) by using tether-length variations. While in the 55th IAC conference the tethered satellite system was assumed as a rigid dumbbell type satellite, the tethered satellite system dealt in this paper is not rigid, and the system has only one control input: tether-length variation. By comparing the nature of the systems to that of rigid satellite systems, this paper points out that the timing of changing the tether length on its orbital motion is a key of orbital transfer. And controllability of the system is discussed numerically by examining the distribution of the control effect.

  • Orbital control of satellite systems using nonholonomic control theory Reviewed International journal

    @Shinji Hokamoto

    Proceedings of the AAS/AIAA Astrodynamics Conference 2005   1533 - 1544   2005.8

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    This study deals with orbital control of a rigid dumbbell-type satellite system. While most of the previous works for orbital transfer aim at changing just one parameter of the orbital element or the orbital energy, in this study the system is transferred by using its inner force into a prescribed orbit defined as a set of orbital elements: semilatus rectum, eccentricity, and argument of pericenter. By applying nonlinear control theories, it is shown that the satellite system is controllable except its pericenter and its apocenter in the elliptic orbit. Then, this paper transforms the nonlinear governing equations into a canonical system, called 'a chained system', and demonstrates that a specified orbit is accomplished by appropriately shaped time histories of control inputs.

  • マニフォールドを利用した宇宙ロボットの制御に関する検討 Reviewed

    @外本 伸治, #松野 崇

    日本ロボット学会誌   23 ( 5 )   594 - 601   2005.7

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    Considerations for Control of Planar Space Robot using Manifolds

    DOI: 10.7210/jrsj.23.594

  • Considerations on control for a tethered satellite system through angular momentum conservation Reviewed International journal

    @Shinji Hokamoto

    Proceedings of the 55th International Astronautical Congress 2004   2   751 - 756   2004.10

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    This study deals with orbital transfer of a tethered satellite system (TSS) on orbit. Dynamics of TSS is restricted to the angular momentum conservation law of the system around a planet. This constraint is not integrable (, that is called "nonholonomic constraint"), and the final state of TSS depends on a time history of the input. While previous works for orbital transfer mainly investigated dynamics of the system for specified time profiles of the tether-length, this study aims to make tether extension profiles to achieve some specified orbit. This paper, as a preliminary study, gives a brief overview of the previous works and investigates the fundamental property of the constraint based on the angular momentum conservation. Integrability and accessibility /controllability are analyzed and also numerically verified. For simplicity, TSS is modeled to a dumbbell-type satellite in this study.

  • An Autonomous Path Planning of a Rover Utilizing Multi-Image Shape from Shading Reviewed International journal

    @Koki Fujita, @Shinji Hokamoto

    Proceedings of the AIAA/AAS Astrodynamics Specialist Conference   2002.8

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    An Autonomous Path Planning of a Rover Utilizing Multi-Image Shape from Shading

  • A consideration on dynamic constraint of planar manipulators with free-joints Reviewed International journal

    @Shinji Hokamoto, #Yoshinari Kawahara

    Proceedings of the AIAA Guidance, Navigation, and Control Conference and Exhibit 2002   2002.8

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    It is known that the manipulators with free-joints are typical mechanical systems dominated by second-order nonholonomic constraints. This paper points out that only the second-order nonholonomic constraint at the first free-joint of the manipulator is integrable to first-order constraint, and that the integrated constraint has linear form of generalized velocities. This constraint implies that a planar manipulator whose first joint is replaced to a free-joint driven by a reaction wheel can be controlled using the same control strategy as that used for the original manipulator. Integrability of the resulting first-order constraint is also discussed for different planar manipulators with free-joints, and the usefulness of the first-order nonholo-nomic constraint is demonstrated numerically in a path-planning problem for a manipulator with two free-joints.

  • Dynamical Interaction of a Tethered Space Robot Reviewed International journal

    #Naoki Imamura, @Shinji Hokamoto

    Proceedings of the 23rd International Symposium on Space Technology and Science   2002.5

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    Dynamical Interaction of a Tethered Space Robot

  • An autonomous path planning of a rover utilizing multi-image shape from shading Reviewed International journal

    @Koki Fujita, @Shinji Hokamoto

    Proceedings of the AIAA/AAS Astrodynamics Specialist Conference and Exhibit 2002   2002.1

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    For planetary exploration, path planning for a rover is one of the important missions. This paper deals with Shape from Shading (SfS) scheme for estimation of planet terrain. As a reliable reflectance model of a surface, the Hapke model is formed in the world of remote sensing. This paper proposes to utilize the Hapke model in the SfS algorithm for multiple camera images. Since the Hapke model has singularity when the gradient vector of a surface element is coincident with a certain direction, the model is modified not to show the singularity. As a result, the SfS algorithm is applicable to multiple camera images and valid regardless of the degree of albedo of the surface. Applying the proposed SfS algorithm for multiple images, an autonomous path planning based on Dynamic Programming is shown. The effectiveness of the proposed scheme is investigated in numerical simulations, and some discussion about the results is presented.

  • Dynamics and Control of a Tethered Space Robot with Tension Reviewed International journal

    @Shinji Hokamoto, #Naoki Imamura, V. J. Modi

    Advances in the Astronautical Sciences   109   1587 - 1595   2001.7

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    Dynamics and Control of a Tethered Space Robot with Tension

  • Dynamic Behavior of a Multi-Legged Planetary Rover of Isotropic Shape Reviewed International journal

    @Shinji Hokamoto, #Manabu Ochi

    Proceedings of the 6th International Symposium on Artificial Intelligence, Robotics and Automation in Space   2001.6

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    Dynamic Behavior of a Multi-Legged Planetary Rover of Isotropic Shape

  • Fundamental Abilities of Multi-Legged Rover with Isotropic Shape Reviewed International journal

    @Shinji Hokamoto, #Manabu Ochi

    Proceedings of the 22nd International Symposium on Space Technology and Science   1627 - 1632   2000.5

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    Fundamental Abilities of Multi-Legged Rover with Isotropic Shape

  • コントロールモーメントジャイロによるトルクユニットマニピュレータの制御 Reviewed

    @外本伸治

    日本機械学会論文集(C編)   64 ( 627 )   4292 - 4298   1998.11

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    Torque-Unit-Manipulator Driven by Control Moment Gyros

  • コントロールモーメントジャイロによるトルクユニットマニピュレータの制御 Reviewed International journal

    @外本 伸治

    Nippon Kikai Gakkai Ronbunshu, C Hen/Transactions of the Japan Society of Mechanical Engineers, Part C   64 ( 627 )   4292 - 4298   1998.11

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    Torque-Unit-Manipulator Driven by Control Moment Gyros

  • Path Planning for a Space Robot Using Surface Integral Map International journal

    @Shinji Hokamoto, #Hajime Ohno

    Proceedings of the AIAA/AAS Astrodynamics Conference   432 - 437   1998.8

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    Path Planning for a Space Robot Using Surface Integral Map

  • Formulation and Control of a Flexible Space-Based Robot with Slewing-Deployable Links Reviewed International journal

    @Shinji Hokamoto, Masamitsu Kuwahara, Vinod Modi, Arun Misra

    Acta Astronautica   42 ( 9 )   519 - 531   1998.5

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    Formulation and Control of a Flexible Space-Based Robot with Slewing-Deployable Links

    DOI: 10.1016/S0094-5765(98)00040-X

  • Formulation and control of space-based flexible robots with slewing-deployable links Reviewed International journal

    @Shinji Hokamoto, Masamitsu Kuwahara, Vinod Modi, Arun Misra

    Acta Astronautica   42 ( 9 )   519 - 531   1998.1

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    The present study deals with a space-based variable geometry mobile manipulator with an arbitrary number of modules, each with two flexible links: one of them free to slew (revolute joint); and the other deployable (prismatic joint). The versatile manipulator has several attractive features: favorable obstacle avoidance, absence of singular configurations, reduced inertia coupling, relatively simpler inverse kinematics as well as governing equations of motion, to mention a few. To begin with, derivation of the governing equations of motion, using the Lagrangian procedure, is explained. As can be expected, the recursive equations are highly nonlinear, nonautonomous and coupled. This is followed by the development of a numerical algorithm leading to the solution for the inverse kinematics. Finally, some typical simulation results for trajectory control of the end-effector using the resolved acceleration approach are presented. They clearly emphasize importance of the control strategy based on the flexible manipulator model.

    DOI: 10.1016/S0094-5765(98)00040-X

  • Torque Unit Manipulator Driven by Control Moment Gyros Reviewed

    @Shinji Hokamoto

    Nihon Kikai Gakkai Ronbunshu, C Hen/Transactions of the Japan Society of Mechanical Engineers, Part C   64 ( 627 )   4292 - 4298   1998.1

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    This paper deals with a space manipulator which is called Torque-Unit-Manipulator (TUM) : TUM separates its actuator called torque unit from its joints; i.e., torque unit is placed on an arbitrary place on a link, and each rotational joint is a free joint. The TUM proposed in the previous work, however, is driven by reaction wheels, and thus it has a problem to be solved : the angular velocity of the reaction wheel may saturate when external force disturbs the posture of the TUM repeatedly. The reason is that the reaction wheels accumulate angular momentum during the maneuver because of non-holonomic constraint for the free joints. Therefore, TUM driven by Control Moment Gyros (CMGs) is proposed in this paper. For the proposed TUM, an asymptotically stable controller can be designed through Lyapunov's approach, and besides the gimbal angular velocity of the CMG returns to zero after each maneuver. The dynamics of the proposed TUM is computed in numerical simulation, and the effectiveness of the designed controller is shown.

    DOI: 10.1299/kikaic.64.4292

  • Torque unit manipulator driven by control moment gyros Reviewed International journal

    @Shinji Hokamoto

    Advances in the Astronautical Sciences   96   865 - 876   1997.12

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    This paper deals with a space manipulator which is called Torque-Unit-Manipulator (TUM): TUM separates its actuator called torque unit from its joint: i.e., torque unit is placed on an arbitrary place on a link, and each rotational joint is a free joint. The TUM proposed in the previous work, however, is driven by reaction wheels, and thus it has a problem to be solved: the angular velocity of the reaction wheel may saturate when repeated external force disturbs the posture of the TUM. The reason is that the reaction wheels accumulate angular momentum during the maneuver because of non-holonomic constraint for the free joints. Therefore, TUM driven by Control Moment Gyros (CMGs) is proposed in this paper. For the proposed TUM, an asymptotically stable controller can be designed through Lyapunov's approach, and besides this the gimbal angular velocity of the CMG returns to zero after each maneuver. The dynamics of the proposed TUM is computed in numerical simulation, and the effectiveness of the designed controller is shown.

  • Torque Unit Manipulator Driven by Control Moment Gyro Reviewed International journal

    @Shinji Hokamoto

    Proceedings of the Seventh International Space Conference of Pacific-basin Societies   1997.7

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  • Control of a Flexible Space-Based Robot with Slewing-Deployable Links Reviewed International journal

    @Shinji Hokamoto, Masamitsu Kuwahara, Vinod Modi, Arun Misra

    Proceedings of the AIAA/AAS Astrodynamics Specialist Conference   1996.7

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  • 直動リンクをもつ柔軟宇宙ロボットの運動方程式とダイナミクス Reviewed

    @外本伸治,Vinod MODI

    日本機械学会論文集(C編)   62 ( 596 )   1495 - 1502   1996.4

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  • 直動リンクをもつ柔軟宇宙ロボットの運動方程式とダイナミクス Reviewed

    @外本 伸治, Vinod J. Modi

    Nippon Kikai Gakkai Ronbunshu, C Hen/Transactions of the Japan Society of Mechanical Engineers, Part C   62 ( 596 )   1495 - 1502   1996.4

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    Formulation and Dynamics of Flexible Space Robots with Deployable Links

  • Dynamics and Control of Space Robots with Deployable Manipulators Reviewed International journal

    @Shinji Hokamoto, Vinod Modi, Arun Misra

    Advances in the Astronautical Sciences   90   1996.1

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  • Formulation and dynamics of flexible space robots with deployable links Reviewed

    @Shinji Hokamoto, Vinod J. Modi

    Nippon Kikai Gakkai Ronbunshu, C Hen/Transactions of the Japan Society of Mechanical Engineers, Part C   62 ( 596 )   1495 - 1502   1996.1

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    This paper deals with a manipulator interconnected by an arbitrary number of modules, each with a flexible slewing link and a flexible deployable link. This manipulator has several inherent advantages compared to a manipulator connected by rotational joints. The two main ones are that integration of modules leads to a variable geometry manipulator with favorable obstacle avoidance and redundancy characteristics, and that there are no singular positions as in the revolute type manipulator. The equations of motion of the manipulator are derived from Lagrange's equations for the quasicoordinates using the elastic deformation modes orthogonal to the translational displacements. The total amount of calculation for the control torque is proportional to the number of links. Finally, to verify the validity of the derived equation and the computer program, the conservation of energy in a few dynamics problems is checked numerically.

    DOI: 10.1299/kikaic.62.1495

  • Nonlinear Dynamics and Control of a Flexible Space-Based Robot with Slewing-Deployable Links Reviewed International journal

    @Shinji Hokamoto, Vinod Modi

    Proceeding of the International Symposium on Microsystems, Intelligent Materials and Robots   1995.9

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  • Dynamics and Control of Mobile Flexible Manipulators with Slewing and Deployable Reviewed International journal

    @Shinji Hokamoto, Vinod Modi, Arun Misra

    Proceedings of the AAS/AIAA Astrodynamics Specialist Conference   1995.8

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  • LAC/HAC System with a Variable Feedback Gain for Flexible Space Structures Reviewed International journal

    @Shinji Hokamoto, @Norihiro Goto

    JSME International Journal   37 ( 3 )   431 - 435   1994.9

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  • Lac/Hac System with a Variable Feedback Gain for Flexible Space Structures Reviewed International journal

    @Shinji Hokamoto, @Norihiro Goto

    jsme international journal. ser. c, dynamics, control, robotics, design and manufacturing   37 ( 3 )   431 - 435   1994.2

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    This paper proposes a new control technique, based on the low authority control/ high authority control (LAC/HAC) concept, to suppress the vibration of flexible space structures. The control system designed by the new control technique has a mechanism to adjust the HAC feedback gain between zero and one in such a manner as to enhance the effectiveness of control and to obtain global stability even when the magnitude of the LAC gain is not suitable. The paper first describes the theoretical mechanism of the new control technique and proposes a numerical method for determining the HAC feedback gain based on a neural network system. Then it shows the characteristic features of the new technique by computer simulation examples. The computer simulation shows that the new technique is quite effective in suppressing the spillover effects, and quite feasible for implementation.

    DOI: 10.1299/jsmec1993.37.431

  • Robust Attitude Control Systems for Flexible Space Structures Invited Reviewed International journal

    @Shinji Hokamoto, Hiroshi Yamamoto

    Proceedings of the Asia-Pacific Vibration Conference   1349 - 1354   1993.11

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  • Proposal of a vibration control technique for a flexible structure Reviewed International journal

    @Shinji Hokamoto, @Norihiro Goto

    Proceedings of the 41st Japan Congress on Applied Mechanics _ NCTAM-41   41   15 - 20   1992.12

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    In this paper a new control technique based on the LAC/HAC concept is proposed to suppress the vibration of flexible space structures. The new technique employs the mechanism to turn on or off the HAC part of the LAC/HAC system in such a manner as to suppress the spillover effects as quickly as possible. The control system designed by the new technique has global stability and is more effective than a pure LAC system, even when an ordinary LAC/HAC system results in failure because of spillover instability. To show the characteristics features of the new technique and how to implement the system, computer simulation examples are given. Finally, the technique is applied to the transversal vibration control of a cantilever beam to show its effectiveness and practicality.

  • A Proposal of a Vibration Control Technique for a Flexible Structure Invited Reviewed International journal

    @Shinji Hokamoto, @Norihiro Goto

    Theoretical and Applied Mechanics   41   15 - 20   1992.10

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  • Modified LAC/HAC Technique for a Flexible Space Structure Reviewed International journal

    @Shinji Hokamoto, @Norihiro Goto

    Proceedings of the 18th International Symposium on Space Technology and Sciences   961 - 966   1992.5

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  • A New Control Technique Based on the LAC/HAC Concept for Flexible Structures Reviewed International journal

    @Shinji Hokamoto, @Norihiro Goto

    Transactions of the Japan Society for Aeronautical and Space Sciences   34 ( 106 )   240 - 249   1992.2

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  • New control technique based on the LAC/HAC concept for flexible structures Reviewed International journal

    @Shinji Hokamoto, @Norihiro Goto

    Transactions of the Japan Society for Aeronautical and Space Sciences   34 ( 106 )   240 - 249   1992.2

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    In this paper a new control technique based on the LAC/HAC concept is proposed to suppress the vibration of flexible space structures. The new technique employs the mechanism to turn on or off the HAC part of the LAC/HAC system in such a manner as to suppress the spillover effects as quickly as possible. The control system designed by the new technique has global stability and is more effective than a pure LAC system, even when an ordinary LAC/HAC system results in failure because of spillover instability. To show the characteristic features of the new technique and how to implement the system, computer simulation examples are given. Finally, the technique is applied to the transversal vibration control of a cantilever beam to show its effectiveness and practicality.

  • LAC/HAC概念に基づく柔軟構造物の新制御法 Invited Reviewed

    @外本伸治,@後藤昇弘

    日本航空宇宙学会誌   39 ( 455 )   686 - 693   1991.12

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  • LAC/HAC概念に基づく柔軟構造物の新制御法 Reviewed

    @外本 伸治, @後藤 昇弘

    日本航空宇宙学会誌   39 ( 455 )   686 - 693   1991.12

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    A New Control Technique Based on the LAC/HAC Concept for Flexible Structures.

    DOI: 10.2322/jjsass1969.39.686

  • Time Sharing LAC/HAC Technique for a Flexible Structure Reviewed International journal

    @Shinji Hokamoto, @Norihiro Goto

    Proceedings of the Second U.S./Japan Conference on Adaptive Structures   280 - 296   1991.11

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  • モーダルフィルタを備える柔軟宇宙構造物のスピルオーバ不安定に関する一考察 Reviewed

    @外本伸治,@後藤昇弘

    システム制御情報学会論文誌   3 ( 12 )   414 - 421   1990.12

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  • モーダルフィルタを備える柔軟宇宙構造物のスピルオーバ不安定に関する一考察 Reviewed

    @外本 伸治, @後藤 昇弘

    システム制御情報学会論文誌   3 ( 12 )   414 - 421   1990.12

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    Modal instability due to spillover is investigated for a flexible vibration control system that employs a modal filter as a state estimator. First the characteristic equation of the system equipped with actuators, sensors and a modal filter is derived in a determinantal form. Then it is shown that the characteristic equation can be expanded. By applying the perturbation technique to the expanded characteristic equation, a criterion is obtained to predict whether a residual mode become stable or unstable. Using the criterion, it is mathematically proved that the control system equipped with one actuator and one sensor always has unstable modes if they are non-colocated.

    DOI: 10.5687/iscie.3.414

  • Spillover instability of a flexible structure equipped with a modal filter Reviewed

    @Shinji Hokamoto, @Norihiro Goto

    Memoirs of the Kyushu University, Faculty of Engineering   50 ( 4 )   363 - 376   1990.12

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    Modal instability due to spillover is investigated of a flexible vibration control system that employs a modal filter as the state estimator. First the characteristic equation of the closed-loop system containing actuators, sensors and a modal filter is derived in a determinantal form. Then it is shown that the characteristic equation can be expanded in a mathematically tractable form. By applying the perturbation technique to the expanded characteristic equation, a criterion is obtained that determines whether or not a residual mode is destabilized. Finally it is proved through the use of the criterion that the control system equipped with one actuator and one sensor always has unstable modes if they are non-colocated.

  • 柔軟構造物制御系の特性方程式と安定化条件について Reviewed

    @外本伸治,@後藤昇弘

    システム制御情報学会論文誌   2 ( 10 )   343 - 349   1989.10

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  • 柔軟構造物制御系の特性方程式と安定化条件について Reviewed

    @外本 伸治, @後藤 昇弘

    システム制御情報学会論文誌   2 ( 10 )   343 - 349   1989.10

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    Precise attitude and shape control of flexible spacecraft requires active control of flexural vibrations. This paper first derives a general closed loop characteristic equation of a flexural vibration control system equipped with arbitrary numbers of non-point actuators and sensors whose regions of actions and observations are expressed by weight functions. Then, the characteristic equation in a determinantal form is expanded in a mathematically tractable form in which each coefficient is a product of an actuator-dependent determinant, a sensor-dependent determinant and a compensator-dependent determinant. By applying the perturbation technique to the expanded characteristic equation, it is shown that a modal stabilizing condition can be obtained for a rate and position feedback control system. Finally, a numerical example is given to illustrate the usage of the condition.

    DOI: 10.5687/iscie.2.343

  • Root Locus Method for Active Control of Flexible Systems Reviewed International journal

    @Norihiro Goto, @Shinji Hokamoto

    Transactions of the Japan Society for Aeronautical and Space Sciences   30 ( 89 )   150 - 161   1987.11

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  • ROOT LOCUS METHOD FOR ACTIVE CONTROL OF FLEXIBLE SYSTEMS. Reviewed International journal

    @Norihiro Goto, @Shinji Hokamoto

    Transactions of the Japan Society for Aeronautical and Space Sciences   30 ( 89 )   150 - 161   1987.11

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    Precise attitude and shape control of flexible spacecraft requires active control of flexural vibrations. This paper is concerned with the root locus method applied to active vibration control systems for a certain class of flexible bodies. A general characteristic equation is derived for a feedback system to control flexural vibrations with arbitrary numbers of sensors and actuators. Then it is shown, for the first time, that the characteristic equation in determinantal form may be reduced to a mathematically tractable form. It is also shown that under the condition of colocation of sensors and actuators the characteristic equation assumes a form in which the significance of this condition can be readily appreciated. Finally, the paper presents a numerical study to illustrate a practical procedure applying the root locus method to flexural vibration control systems.

  • Trajectory Design in Irregular Gravitational Fields Based on Center Manifold Theory Reviewed International journal

    #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    Journal of Guidance, Control, and Dynamics   1900

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Presentations

  • The Minimum Necessary Number of Thrusters for Three-Dimensional Satellite Attitude Control International conference

    Yasuhiro Yoshimura, Shinji Hokamoto

    The 4th KAIST-Kyushu Univ. Symposium on Aerospace Engineering  2009.12 

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    Event date: 2009.12

    Country:Korea, Republic of  

  • A New Type of a Multi-Legged Planetary Exploration Rover International conference

    Shinji Hokamoto, Shinji Nishikori

    The 4th KAIST-Kyushu Univ. Symposium on Aerospace Engineering  2009.12 

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    Event date: 2009.12

    Country:Korea, Republic of  

  • Position and Attitude Feedback Controller of a Planar Satellite with Two Thrusters International conference

    Takashi Matsuno, Shinji Hokamoto

    ICROS-SICE International Joint Conference 2009  2009.8 

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    Event date: 2009.8

    Country:Japan  

  • Position and Attitude Control of a Planar Satellite by Two Thrusters International conference

    Shinji Hokamoto, Masaoki Iwase

    Guidance, Navigation, and Control Conference  2009.8 

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    Event date: 2009.8

    Country:United States  

  • Position and Attitude Control of a Free-Floating Planar Satellite Controlled by Thrusters International conference

    Shinji Hokamoto, Masaoki Iwase

    27th International Symposium on Space Technology and Science  2009.7 

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    Event date: 2009.7 - 2009.9

    Country:Japan  

  • スラスター駆動の浮遊衛星に対する少ない入力数による非ホロノミック制御

    岩瀬正興,外本伸治

    第52回宇宙科学技術連合講演会  2008.11 

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    Event date: 2008.11

    Country:Japan  

  • Kinematic Discussion and Development of a Multi-Legged Planetary Exploration Rover with Isotropic Leg Arrangement International conference

    Shinji Nishikori, Shinji Hokamoto

    Asia International Symposium on Mechatronics 2008  2008.8 

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    Event date: 2008.8

    Presentation type:Oral presentation (general)  

    Venue:Hokkaido   Country:Japan  

  • カメラおよび距離画像を用いた,着陸機運動・特徴点位置同時推定

    藤田浩輝,外本伸治

    機械学会年次大会2008  2008.8 

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    Event date: 2008.8

    Country:Japan  

  • Kinematic Discussion and Development of a Multi-Legged Planetary Exploration Rover with Isotropic Leg Arrangement International conference

    Shinji Nishikori, Shinji Hokamoto

    Asia International Symposium on Mechatronics 2008  2008.8 

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    Event date: 2008.8

    Venue:Hokkaido   Country:Japan  

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  • Input Profile for Satellite Orbit Transfer by Tether Mechanism Part II: Feedback Control for State Variables International conference

    Shinji Hokamoto, Shohei Koga

    37th Committee on Space Research  2008.7 

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    Event date: 2008.7

    Venue:Montreal   Country:Canada  

  • Non-holonomic Analysis and Control of a Thruster Driven Free-Floating Satellite

    Shinji Hokamoto, Masaoki Iwase, Junya Fujii

    18th Workshop on JAXA Astrodynamics and Flight Mechanics  2008.7 

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    Event date: 2008.7

    Country:Japan  

  • Input Profile for Satellite Orbit Transfer by Tether Mechanism Part I: Tether Length Profile Using Feed-Forward Procedure International conference

    Shinji Hokamoto, Naritoyo Shibata

    37th Committee on Space Research  2008.7 

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    Event date: 2008.7

    Presentation type:Oral presentation (general)  

    Venue:Montreal   Country:Canada  

  • Input Profile for Satellite Orbit Transfer by Tether Mechanism Part I: Tether Length Profile Using Feed-Forward Procedure International conference

    Shinji Hokamoto, Naritoyo Shibata

    37th Committee on Space Research  2008.7 

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    Event date: 2008.7

    Venue:Montreal   Country:Canada  

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  • Input Profile for Satellite Orbit Transfer by Tether Mechanism Part II: Feedback Control for State Variables International conference

    Shinji Hokamoto, Shohei Koga

    37th Committee on Space Research  2008.7 

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    Event date: 2008.7

    Venue:Montreal   Country:Canada  

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  • Trajectory Design of Solar Sail Spacecraft for Interplanetary Rendezvous Missions International conference

    Shinji Hokamoto, Koji Sachimoto, Koki Fujita

    26th International Symposium on Space Technology and Science  2008.6 

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    Event date: 2008.6

    Presentation type:Oral presentation (general)  

    Venue:Hamamatsu   Country:Japan  

  • Out-of-Plane Orbital Transfer for Tethered Satellite Systems International conference

    Masaoki Iwase, Shinji Hokamoto

    26th International Symposium on Space Technology and Science  2008.6 

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    Event date: 2008.6

    Presentation type:Oral presentation (general)  

    Venue:Hamamatsu   Country:Japan  

  • Out-of-Plane Orbital Transfer for Tethered Satellite Systems International conference

    Masaoki Iwase, Shinji Hokamoto

    26th International Symposium on Space Technology and Science  2008.6 

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    Event date: 2008.6

    Venue:Hamamatsu   Country:Japan  

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  • Trajectory Design of Solar Sail Spacecraft for Interplanetary Rendezvous Missions International conference

    Shinji Hokamoto, Koji Sachimoto, Koki Fujita

    26th International Symposium on Space Technology and Science  2008.6 

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    Event date: 2008.6

    Venue:Hamamatsu   Country:Japan  

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  • 回転カメラによるステレオ画像を用いた自己位置同定

    藤井淳也,藤田浩輝,外本伸治

    第25回誘導制御シンポジウム  2008.5 

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    Event date: 2008.5 - 2009.5

    Presentation type:Oral presentation (general)  

    Country:Japan  

  • 三次元等方脚配置をもつ脚式探査ローバの運動学的考察と開発

    錦織慎治,松原学,外本伸治

    第25回誘導制御シンポジウム  2008.5 

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    Event date: 2008.5 - 2009.5

    Presentation type:Oral presentation (general)  

    Country:Japan  

  • 摂動論を用いた低推力宇宙機軌道の解析解の導出

    伊達 直輝, 坂東 麻衣, 外本 伸治

    第58回宇宙科学技術連合講演会  2014.11 

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    Country:Japan  

  • 惑星探査ローバにおけるレーザレンジファインダーによる環境認識の効果の検証

    雲 凱, 金城 寛, 外本 伸治

    日本航空宇宙学会西部支部講演会  2014.11 

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    Country:Japan  

  • 吸着機構を持つ4 脚壁面歩行ロボットの開発

    山崎 翼, 金城 寛, 外本 伸治

    ロボティクス・メカトロニクス講演会  2015.5 

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    Country:Japan  

  • スライディングモード制御によるクアッドコプターの姿勢および高度制御

    中田 隆介, 金城 寛, 外本 伸治

    ロボティクス・メカトロニクス講演会  2015.5 

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    Language:Japanese  

    Country:Japan  

  • Experimental verification on enabling long distance travel for planetary rover using scanning LRF system International conference

    Kai Yun, Yutaka Kinjo, Shinji Hokamoto

    30th International Symposium on Space Technology and Science  2015.7 

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    Country:Japan  

  • Experimental verification of wide-field-integration of optic flow for state estimation International conference

    Naoto Kobayashi, Masataka Oishi, Yutaka Kinjo, Shinji Hokamoto

    30th International Symposium on Space Technology and Science  2015.7 

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    Country:Japan  

  • Design of earth-moon cyclers using primer vector theory International conference

    Sho Hayashida, Mai Bando, Shinji Hokamoto

    30th International Symposium on Space Technology and Science  2015.7 

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    Country:Japan  

  • Trajectory design using the center manifold theory in the circular restricted three-body problem International conference

    Yuki Akiyama, Mai Bando, Hamidreza Nemati, Shinji Hokamoto

    30th International Symposium on Space Technology and Science  2015.7 

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    Country:Japan  

  • Satellite Formation-Keeping about Libration Points in the Presence of System Uncertainties International conference

    Mai Bando, Hamidreza Nemati, Shinji Hokamoto

    Astrodynamics Specialist Conference 2015  2015.8 

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    Country:United States  

  • スライディングモード制御によるハロー軌道の安定化について

    Hamidreza Nemati, 坂東麻衣, 外本伸治

    第59回宇宙科学技術連合講演会  2015.10 

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    Country:Japan  

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

    Hamidreza Nemati, Mai Bando, Shinji Hokamoto

    66th International Astronautical Congress  2015.10 

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    Language:English  

    Country:Israel  

  • Station-keeping and formation flying for periodic orbit around Lagrangian points by Fourier series International conference

    Yuki Akiyama, Mai Bando, Shinji Hokamoto

    25th International Symposium on Space Flight Dynamics  2015.10 

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    Country:Germany  

  • Motion estimation of autonomous spacecraft near asteroid using wide-field-integration of optic flow International conference

    Naoto Kobayashi, Masataka Oishi, Yutaka Kinjo, Daisuke Kubo, Shinji Hokamoto

    25th International Symposium on Space Flight Dynamics  2015.10 

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    Country:Germany  

  • Gravity-Assisted Maneuvers with Tether International conference

    Tsubasa Yamasaki, Mai Bando, Shinji Hokamoto

    7th Kyushu University-KAIST Symposium on Aerospace Engineering  2015.12 

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    Country:Japan  

  • Environment recognition and the travel distance estimation by the moving exploration rover equipped with a Laser-Range-Finder (LRF) International conference

    Kai Yun, Yutaka Kinjo, Shinji Hokamoto

    7th Kyushu University-KAIST Symposium on Aerospace Engineering  2015.12 

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    Country:Japan  

  • テザーの切断を利用したスイングバイの解析

    山崎翼, 坂東 麻衣, 外本伸治

    計測自動制御学会制御部門 第3回マルチシンポジウム  2016.3 

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    Country:Japan  

  • オプティックフローによる小型自律航空機の高度および状態推定

    中田隆介, 小林直人, 金城寛, 外本伸治

    計測自動制御学会制御部門 第3回マルチシンポジウム  2016.3 

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    Country:Japan  

  • スライディングモード制御を用いたクアッドコプターの自律飛行に関する研究

    大場隆祥, 小林直人, 中田隆介, 金城寛, 外本伸治

    ロボティクス・メカトロニクス講演会2016  2016.6 

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    Language:Japanese  

    Country:Japan  

  • LRF Based Autonomous Navigation System Measuring on Moving Rover International conference

    Kai Yun, Shinya Katoku, Yutaka Kinjo, Shinji Hokamoto

    The International Symposium on Artificial Intelligence, Robotics and Automation in Space (i-SAIRAS 2016)  2016.6 

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    Language:English  

    Country:China  

  • 3次元劣駆動浮遊衛星のスラスターによる姿勢・位置の制御手法の検討

    松野崇, 吉村康広, 外本 伸治

    第60回宇宙科学技術連合講演会  2016.9 

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    Country:Japan  

  • レーザレンジファインダーを搭載した移動中の探査ローバーによる移動距離推定

    加徳晋也, 雲凱, 佐々木秀邦, 金城寛, 外本 伸治

    第60回宇宙科学技術連合講演会  2016.9 

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    Country:Japan  

  • Flow Functionを用いた円制限三体問題における周期軌道の安定性解析

    山口誠樹, 秋山祐貴, Mai Bando, 外本 伸治

    第60回宇宙科学技術連合講演会  2016.9 

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    Country:Japan  

  • 出力レギュレーションを用いた三体問題の軌道維持

    秋山祐貴, Mai Bando, 外本 伸治

    第60回宇宙科学技術連合講演会  2016.9 

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    Country:Japan  

  • Powered Swing-by Using Tether Cutting International conference

    Tsubasa Yamasaki, Mai Bando, Shinji Hokamoto

    67th International Astronautical Congress  2016.9 

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    Country:Mexico  

  • Periodic Orbits Design based on the Center Manifold Theory in the Circular Restricted Three-Body Problem International conference

    Yuki Akiyama, Mai Bando, Shinji Hokamoto

    67th International Astronautical Congress  2016.9 

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    Language:English  

    Country:Mexico  

  • A Novel Attitude Estimation Method Based on Wide-Field-Integration of Optic Flow for Autonomous Navigation International conference

    Naoto Kobayashi, Ryusuke Nakata, Mai Bando, Shinji Hokamoto

    2016 Asia-Pacific International Symposium on Aerospace Technology  2016.10 

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    Country:Japan  

  • Altitude and motion estimation for small UAVs by using optic flow International conference

    Ryusuke Nakata, Naoto Kobayashi, Mai Bando, Shinji Hokamoto

    8th KAIST-Kyushu University Symposium on Aerospace Engineering  2016.10 

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    Country:Korea, Republic of  

  • Attractive setを用いたフォーメーションフライトの最適軌道設計

    山根基暉, Mai Bando, 外本 伸治

    日本航空宇宙学会西部支部講演会(2016)  2016.11 

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    Country:Japan  

  • 回転と移動機能を持つカメラシステムによる環境認識に関する研究

    王瀚培, 小林直人, Mai Bando, 外本 伸治

    日本航空宇宙学会西部支部講演会(2016)  2016.11 

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    Country:Japan  

  • 入力を付加した力学系における人工的な不変多様体

    秋山祐貴, Mai Bando, 外本 伸治

    第4回 制御部門マルチシンポジウム  2017.3 

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    Country:Japan  

  • 異なる境界条件に対する最適フォーメーションフライト軌道

    山根基暉, Mai Bando, 秋山祐貴, 外本 伸治

    第4回 制御部門マルチシンポジウム  2017.3 

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    Country:Japan  

  • ポート・ハミルトン系を用いた宇宙機の位置・姿勢制御則構築について

    坂本知也, Mai Bando, 外本 伸治

    第4回 制御部門マルチシンポジウム  2017.3 

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    Country:Japan  

  • 最小エネルギー制御を利用した三体問題における低推力軌道移行

    大島侑記, 秋山祐貴, Mai Bando, 外本 伸治

    第4回 制御部門マルチシンポジウム  2017.3 

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    Country:Japan  

  • Altitude and Motion Estimation for Autonomous Vehicles through Wide-Field-Integration of Optic Flow International conference

    #Ryusuke Nakata, #Naoto Kobayashi, @Mai Bando, @Shinji Hokamoto

    31st International Symposium on Space Technology and Science  2017.5 

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    Country:Japan  

  • Dynamic Locomotion of a Multi-Legged Planetary Exploration Rover with Isotropic Leg Arrangement International conference

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

    31st International Symposium on Space Technology and Science  2017.5 

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    Country:Japan  

  • Optimal Trajectory Design of Formation Flying based on Attractive Sets International conference

    #Motoki Yamane, @Mai Bando, @Shinji Hokamoto

    31st International Symposium on Space Technology and Science  2017.5 

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    Country:Japan  

  • Station-keeping and formation flying based on Nonlinear Output Regulation theory International conference

    #Yuki Akiyama, @Mai Bando, @Shinji Hokamoto

    9th International Workshop on Satellite Constellation and Formation Flying  2017.6 

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    Country:United States  

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

    #Yuki Akiyama, @Mai Bando, @Shinji Hokamoto

    68th International Astronautical Congress  2017.9 

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    Language:English  

    Country:Australia  

  • Optic flow-based environment recognition system for planetary rovers International conference

    #Naoto Kobayashi, #Ryusuke Nakata, @Mai Bando, @Shinji Hokamoto

    68th International Astronautical Congress  2017.9 

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    Country:Australia  

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

    #Motoki Yamane, @Mai Bando, @Shinji Hokamoto

    68th International Astronautical Congress  2017.9 

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    Language:English  

    Country:Australia  

  • Trajectory design to triangular libration points based on resonant orbits International conference

    #Nobuki Yamaguchi, @Mai Bando, @Shinji Hokamoto

    68th International Astronautical Congress  2017.9 

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    Country:Australia  

  • Considerations on Design Parameters for Attitude Control of Spacecraft Using Port-Controlled Hamiltonian Systems International conference

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

    SICE Annual Conference 2017  2017.10 

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    Country:Japan  

  • Autonomous Flight of Under-Actuated Quad-Rotor Vehicle based on Sliding Mode Control International conference

    #Takayoshi Oba, #Naoto Kobayashi, @Mai Bando, @Shinji Hokamoto

    2017 Asia-Pacific International Symposium on Aerospace Technology  2017.10 

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    Language:English  

    Country:Korea, Republic of  

  • 円制限三体問題における最小エネルギー制御

    #大島侑記, @Mai Bando, @外本 伸治

    第61回 宇宙科学技術連合講演会  2017.10 

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    Country:Japan  

  • スパース性を伴うL1最適制御による軌道設計

    #永島 聡, @坂東 麻衣, @外本 伸治

    第61回 宇宙科学技術連合講演会  2017.10 

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  • LRFによる移動中の惑星探査ローバの移動距離推定

    #佐々木秀邦,@金城寛, @坂東 麻衣, @外本 伸治

    第61回 宇宙科学技術連合講演会  2017.10 

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    Country:Japan  

  • Wide-Field Integration of Optic Flowを用いた運動推定における画像センサ位置の影響

    #丸山慶一郎,#小林直人,@坂東 麻衣, @外本 伸治

    日本航空宇宙学会西部支部講演会(2017)  2017.11 

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    Country:Japan  

  • Space Debris Chain Collision Analysis Based on Network Theory

    #冨田健人,@坂東 麻衣, @外本 伸治

    第5回 制御部門マルチシンポジウム  2018.3 

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    Language:Japanese  

    Country:Japan  

  • Influence of unstable dynamics on orbit determination with X-ray pulsar navigation International conference

    #Yang Zhou, @Mai Bando, @Shinji Hokamoto, @Panlong Wu

    The 4th IAA Conference on Dynamics and Control of Space Systems  2018.5 

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    Country:China  

  • 3 次元等方多脚形状を有する探査ローバーの運動解析

    #関口智仁,@近江佐紀,@外本伸治

    ロボティクス・メカトロニクス講演会2018  2018.6 

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    Country:Japan  

  • 微小重力天体に投下される探査ローバーの挙動解析

    #佐々木祐成,@坂東麻衣,@外本伸治,@照井冬人,@津田雄一

    アストロダイナミクス・シンポジウム  2018.7 

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  • 微小重力天体に投下される探査ローバーの最終位置予測

    #佐々木祐成,@坂東麻衣,@外本伸治,@照井冬人,@津田雄一

    アストロダイナミクス・シンポジウム  2018.7 

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  • 楕円軌道上におけるAttractive Setを用いた最適軌道設計に関する研究

    #香山裕樹,@坂東麻衣,@外本伸治

    アストロダイナミクス・シンポジウム  2018.7 

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    Country:Japan  

  • LQ Optimal Artificial Potential Functions for Satellite Swarm Guidance International conference

    #Kyosuke Asaki, @Mai Bando, @Shinji Hokamoto

    SICE Annual Conference 2018  2018.9 

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    Country:Japan  

  • Extended State Space Approach for Trajectory Design in Elliptic Restricted Three-Body Problem International conference

    @Yuki Akiyama, @Mai Bando, @Shinji Hokamoto

    69th International Astronautical Congress  2018.9 

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    Language:English  

    Country:Germany  

  • Optimal Trajectory Design for Safety Rendezvous based on Sparse Modeling International conference

    #Satoshi Nagashima, @Mai Bando, @Shinji Hokamoto

    69th International Astronautical Congress  2018.9 

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    Country:Germany  

  • Optimal Control of Spacecraft Attitude Motion using Port-Hamiltonian Systems International conference

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

    69th International Astronautical Congress  2018.9 

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    Country:Germany  

  • ホットジュピターにおけるスリングショットモデル適用妥当性の検証

    #紀藤准弥,@坂東麻衣,@外本伸治

    2018年日本惑星科学会秋季講演会  2018.10 

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  • 最適制御理論的見地からのポート・ハミルトン系による宇宙機の位置姿勢制御

    #坂本知也,@坂東麻衣, @外本伸治

    第62回 宇宙科学技術連合講演会  2018.10 

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  • 微小重力下における跳躍探査ロボットの挙動に関する研究

    #佐々木祐成,@坂東麻衣, @外本伸治

    第62回 宇宙科学技術連合講演会  2018.10 

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  • リーマン多様体上の最適化を用いた軌道最適化の直接解法

    #浅木恭介,@坂東麻衣, @外本伸治

    第62回 宇宙科学技術連合講演会  2018.10 

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  • 月から月への軌道遷移における消費エネルギーの体系化

    #香山裕樹,@坂東麻衣, @外本伸治

    第62回 宇宙科学技術連合講演会  2018.10 

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  • スパース性に着目したHalo 軌道間遷移の最適化

    #香山裕樹,@坂東麻衣, @外本伸治

    第62回 宇宙科学技術連合講演会  2018.10 

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  • 不変多様体の包含関係を利用した周期軌道間の低エネルギー輸送軌道

    #蜂谷友理,@坂東麻衣, @外本伸治

    日本航空宇宙学会西部支部講演会 (2018)  2018.11 

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  • 火星探査用回転翼機の機体形状と制御性能の検討

    #松村吉起,@坂東麻衣, @外本伸治

    日本航空宇宙学会西部支部講演会 (2018)  2018.11 

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  • A Solution of Hamilton-Jacobi-Bellman Equation for Spacecraft Tracking system using Generalized Canonical Transformation International conference

    #Tomoya Sakamoto, @Mai Bando, @Shinji Hokamoto

    The 10th KAIST-Kyushu University Symposium on Aerospace Engineering  2018.12 

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  • Sparse Optimal Trajectory Design in Three-Body Problem International conference

    #Yuki Kayama, @Mai Bando, @Shinji Hokamoto

    The 29th Space Flight Mechanics  2019.1 

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  • Trajectory Design in the Circular Restricted Three-Body Problem Using Artificial Invariant Manifolds International conference

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

    The 29th Space Flight Mechanics  2019.1 

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  • Output Regulation Control for Satellite Formation Flying Using Differential Drag International conference

    #Mohamed Shouman, @Mai Bando, @Shinji Hokamoto

    The 29th Space Flight Mechanics  2019.1 

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  • LQR制御による太陽-地球-月系の低エネルギー軌道遷移

    #蜂谷友理,#大島侑記,@坂東麻衣, @外本伸治

    第6回 制御部門マルチシンポジウム  2019.3 

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  • Orbit Maintenance for Quasi Periodic Orbits in Earth-Moon System International conference

    #Yang Zhou, @Mai Bando, @Shinji Hokamoto, @Penlong Wu

    32nd International Symposium on Space Technology and Science  2019.6 

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    Country:Japan  

  • Performance Analysis of Formation Flying Using Differential Aerodynamic Drag in High Precision Orbit Propagator International conference

    #Mohamed Shouman, @Mai Bando, @Shinji Hokamoto

    32nd International Symposium on Space Technology and Science  2019.6 

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  • Sparse Optimal Control for Nonlinear Trajectory Design in Three-Body Problem International conference

    #Yuki Kayama, @Mai Bando, @Shinji Hokamoto

    32nd International Symposium on Space Technology and Science  2019.6 

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    Country:Japan  

  • Reachability of Hopping Exploration Robot to a Destination Point Under Microgravity International conference

    #Yusei Sasaki, #Tomohiro Ishizuka, @Mai Bando, @Shinji Hokamoto

    32nd International Symposium on Space Technology and Science  2019.6 

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

    #Yuki Kayama, @Mai Bando, @Shinji Hokamoto

    SICE Annual Conference 2019  2019.9 

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  • Manifold-to-Manifold Transfers Using Low-Thrust Acceleration International conference

    @Yuri Hachiya, #Yuki Kayama, @Mai Bando, @Shinji Hokamoto

    70th International Astronautical Congress  2019.9 

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  • Riemannian Optimization for Spacecraft Trajectory Design International conference

    #Kyosuke Asaki, @Mai Bando, @Shinji Hokamoto

    70th International Astronautical Congress  2019.9 

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  • 電動エアタクシーにおけるVTOL時の姿勢安定性に関する研究

    #渡部達也,@坂東麻衣, @外本伸治

    第57回飛行機シンポジウム  2019.10 

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  • 劣駆動性に基づく宇宙機の姿勢制御系のロバスト化に関する研究

    #佐々木祐成,@坂東麻衣, @外本伸治

    第63回宇宙科学技術連合講演会  2019.11 

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  • 火星探査用回転翼機の機体形式が可操作度に及ぼす影響

    #松村吉起,@坂東麻衣, @外本伸治

    第63回宇宙科学技術連合講演会  2019.11 

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  • 姿勢の制約を考慮した大気抵抗によるフォーメーション制御

    #安田武弘,#Mohamed Shouman,@坂東麻衣, @外本伸治

    第63回宇宙科学技術連合講演会  2019.11 

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  • 3次元トランジット軌道の設計とミッション

    #野間航,@坂東麻衣, @外本伸治

    第63回宇宙科学技術連合講演会  2019.11 

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  • 太陽―地球―月系における低推力を用いた連続月スイングバイ軌道設計

    #宮原圭太郎,#香山裕樹,@坂東麻衣, @外本伸治

    第63回宇宙科学技術連合講演会  2019.11 

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  • Unmanned Aerial Vehicle Obstacle Detection Using Wide-Field Integration of Optic Flow International conference

    #Xiaoxu Feng, @Mai Bando, @Shinji Hokamoto

    The 11th KAIST-Kyushu University Symposium on Aerospace Engineering  2019.12 

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

    #Yuki Kayama, @Mai Bando, @Shinji Hokamoto

    2020 AIAA SciTech Forum  2020.1 

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  • 強化学習を用いた3次元観測ドローンネットワークの構築

    #毎熊良太,@坂東麻衣,@外本伸治

    アストロダイナミクス・シンポジウム  2020.7 

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    Venue:online   Country:Japan  

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

    #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    2020 AAS/AIAA Astrodynamics Specialist Conference  2020.8 

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  • Optimal Landing Problem for a Binary Asteroid System and its Error Sensitivity International conference

    #Anviksha Sharma, @Mai Bando, @Shinji Hokamoto, Daniel J. Scheeres

    SICE Annual Conference 2020  2020.9 

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    Venue:online   Country:Thailand  

  • Obstacle Shape Estimation by Wide-Field-Integration of Optic Flow International conference

    #Xiaoxu Feng, @Mai Bando, @Shinji Hokamoto

    International Symposium on Electric Aviation and Autonomous Systems 2020  2020.9 

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    Venue:online   Country:Ukraine  

  • 3 基のスラスタによる宇宙機の角速度と姿勢の制御

    #佐々木祐成,@坂東麻衣, @外本伸治

    第64回宇宙科学技術連合講演会  2020.10 

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  • 動的モード分解を用いた多体力学系の非線形力学現象の解析

    #中村俊介,@坂東麻衣, @外本伸治

    第64回宇宙科学技術連合講演会  2020.10 

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  • 中心多様体理論に基づく連星小惑星Didymosにおける軌道設計

    #平岩尚樹,@坂東麻衣, @外本伸治

    第64回宇宙科学技術連合講演会  2020.10 

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  • クープマン固有関数を用いた宇宙機の非線形力学系の解析と制御

    #廣瀬悠斗,@坂東麻衣, @外本伸治

    第64回宇宙科学技術連合講演会  2020.10 

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    Venue:online   Country:Japan  

  • Trajectory Design to Mars from Earth-Moon System with Three-Dimensional Transit Orbits International conference

    #Wataru Noma, @Mai Bando, @Shinji Hokamoto

    71st International Astronautical Congress  2020.10 

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  • Formation Control Using Differential Atmospheric Drag Considering Attitude Constraints International conference

    #Takehiro Yasuda, @Mai Bando, @Shinji Hokamoto

    71st International Astronautical Congress  2020.10 

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  • Cycler orbit design using low-thrust in the Sun-Earth-Moon system International conference

    #Keitaro Miyahara, @Mai Bando, @Shinji Hokamoto

    71st International Astronautical Congress  2020.10 

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  • Three-dimensional Attitude Control of Spacecraft by Three Thrusters International conference

    #Yusei Sasaki, #Masato Matsumoto, @Mai Bando, @Shinji Hokamoto

    71st International Astronautical Congress  2020.10 

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  • Optimization of Earth-Mars Transfer Using Three-dimensional Transit Orbits

    #許哲,@坂東麻衣, @外本伸治

    第64回宇宙科学技術連合講演会  2020.10 

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    Venue:online   Country:Japan  

  • 劣駆動性を考慮した宇宙機におけるスラスタ配置の検討

    #松本真慧,@坂東麻衣, @外本伸治

    日本航空宇宙学会西部支部講演会 (2020)  2020.11 

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  • PSOと翼素運動量理論に基づくローター最適レイアウト設計

    #黄雨可,#渡部達也,@坂東麻衣, @外本伸治

    日本航空宇宙学会西部支部講演会 (2020)  2020.11 

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  • 強化学習を用いた3次元観測ドローンネットワークの構築

    #毎熊良太,@坂東麻衣,@外本伸治

    第8回 制御部門マルチシンポジウム  2021.3 

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  • 平衡点周辺における非線形最適制御

    #佐藤杏輔,@坂東麻衣,@外本伸治

    第31回アストロダイナミクス・シンポジウム  2021.7 

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  • HAVOKによる地球-月三体問題のカオス軌道の解析

    #浦志太勢,@坂東麻衣,@外本伸治

    第31回アストロダイナミクス・シンポジウム  2021.7 

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  • 非ホロノミック性を利用した可変構造宇宙機の3次元姿勢変化

    #竹内咲希,@坂東麻衣,@外本伸治

    第31回アストロダイナミクス・シンポジウム  2021.7 

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  • Optimal Layout Design of Multi-Rotor Vehicle Based on PSO Algorithm International conference

    #Yuke Huang, @Mai Bando, @Shinji Hokamoto

    International Symposium on Aircraft Technology 2021  2021.6 

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    Venue:online   Country:Turkey  

  • Data-Driven Analysis of Chaotic Orbits in the Circular Restricted Three Body Problem International conference

    #Taiki Urashi, @Shinji Hokamoto, @Mai Bando

    2021 AAS/AIAA Astrodynamics Specialist Conference  2021.8 

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

    #Kyosuke Sato, @Shinji Hokamoto, @Mai Bando

    2021 AAS/AIAA Astrodynamics Specialist Conference  2021.8 

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    Venue:online   Country:United States  

  • Multirotor Vehicles Design Based on Dynamic Manipulability for Underactuated Flying Systems International conference

    #Yoshiki Matsumura, @Mai Bando, @Shinji Hokamoto

    32nd Congress of the International Council of the Aeronautical Sciences  2021.9 

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    Venue:online   Country:China  

  • Analysis of Ballistic Escape Based on Lobe Dynamics International conference

    #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    72nd International Astronautical Congress  2021.10 

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    Country:United Arab Emirates  

  • Spacecraft Trajectory Design Using Data-Driven Model Predictive Control International conference

    #Yuto Hirose, @Mai Bando, @Shinji Hokamoto

    72nd International Astronautical Congress  2021.10 

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    Country:United Arab Emirates  

  • Semantic Segmentation Technique to Identify Landing Area for Autonomous Spacecraft International conference

    #Xin Gao, @Mai Bando, @Shinji Hokamoto

    Asia-Pacific International Symposium on Aerospace Technology (APISAT 2021)  2021.11 

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  • カメラを用いたマルチコプターの編隊飛行について

    外本賢暉,岡田伸廣,@外本伸治

    第40回計測自動制御学会九州支部学術講演会  2021.11 

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  • 力学系の遅延埋め込みを用いた小惑星着陸制御

    #梶川大河,@坂東麻衣, @外本伸治

    第65回宇宙科学技術連合講演会  2021.11 

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  • 近点ポアンカレマップを用いたEuropaへの低エネルギー遷移軌道の設計

    #池田幹太,#平岩尚樹,@坂東麻衣, @外本伸治

    第65回宇宙科学技術連合講演会  2021.11 

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  • 複眼視覚航法に基づく小型UAVの自律システムについて

    #平岩央光,@坂東麻衣, @外本伸治

    第64回自動制御連合講演会  2021.11 

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  • 並進運動性能 に基づいた ヘキサローターのローター設置角の最適化

    #島村祐,@坂東麻衣, @外本伸治

    第59回飛行機シンポジウム  2021.11 

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  • 強化学習を用いた3次元観測ドローンネットワークの構築

    #毎熊良太,@坂東麻衣, @外本伸治

    第34回自律分散システム・シンポジウム  2022.1 

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  • 摂動を考慮したデブリへの接近ストラテジーに関する考察

    #竹﨑碧,@坂東麻衣, @外本伸治

    第9回制御部門マルチシンポジウム  2022.3 

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  • クープマン作用素による宇宙機のデータ駆動力学系のモデル予測制御

    #廣瀬悠斗,#佐藤杏輔,@坂東麻衣, @外本伸治

    第9回制御部門マルチシンポジウム  2022.3 

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  • Design of low energy transfer trajectories from Earth to Europa with ballistic capture International conference

    #Kanta Ikeda, #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    The 33rd International Symposium on Space Technology and Science  2022.3 

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

    #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    The 33rd International Symposium on Space Technology and Science  2022.3 

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    Language:English  

    Venue:online   Country:Japan  

  • Effects of Rotational Joint Directions of Variable Structure on Non-holonomic Features International conference

    #Saki Takeuchi, #Kanta Ikeda, @Mai Bando, @Shinji Hokamoto

    The 33rd International Symposium on Space Technology and Science  2022.3 

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    Language:English  

    Venue:online   Country:Japan  

  • Lobe Dynamics によるカオス的遷移軌道の解析

    #平岩尚樹, @坂東麻衣,@外本伸治

    第32回アストロダイナミクス・シンポジウム  2022.7 

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    Language:Japanese  

    Venue:online   Country:Japan  

  • 3次元運動による非ホロノミック性を利用した宇宙機の姿勢変化

    #竹内咲希,#池田幹太, @坂東麻衣,@外本伸治

    第32回アストロダイナミクス・シンポジウム  2022.7 

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    Language:Japanese  

    Venue:online   Country:Japan  

  • Data-Driven Orbital Control in Perturbed Environment International conference

    #Komsun Tamanakijprasart, @Mai Bando, @Shinji Hokamoto

    The 2022 SICE Annual Conference  2022.9 

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    Language:English  

    Venue:Kumamoto   Country:Japan  

  • Influence of Overall Layout Design of Compound Multi-Rotor Vehicles on Flight Performance International conference

    #Yuke Huang, @Mai Bando, @Shinji Hokamoto

    The 33rd Congress of the International Council of the Aeronautical Sciences  2022.9 

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    Language:English  

    Venue:Stockholm   Country:Sweden  

  • Altitude Estimation by Wide-Field-Integration Optic Flow International conference

    #Hiromitsu Hiraiwa, @Mai Bando, @Shinji Hokamoto

    The 33rd Congress of the International Council of the Aeronautical Sciences  2022.9 

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    Language:English  

    Venue:Stockholm   Country:Sweden  

  • Data-Driven Guidance for Asteroid Landing Based on Real-Time Dynamic Mode Decomposition International conference

    #Taiga Kajikawa, @Mai Bando, @Shinji Hokamoto

    The 73rd International Astronautical Congress  2022.9 

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    Language:English  

    Country:France  

  • A Data-Driven Nonlinear Optimal Control Using Koopman Operator on Hamiltonian Flow International conference

    #Kyoshuke Sato, @Mai Bando, @Shinji Hokamoto

    The 73rd International Astronautical Congress  2022.9 

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    Language:English  

    Country:France  

  • Design of Optimal Low-Thrust Orbit-to-Orbit Transfers via Convex Approach International conference

    #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    The 73rd International Astronautical Congress  2022.9 

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    Language:English  

    Country:France  

  • Design of Satellites Tours Using Periapsis Poincaré Map in Multibody Dynamics of Jovian System International conference

    #Kanta Ikeda, #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    The 73rd International Astronautical Congress  2022.9 

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    Language:English  

    Country:France  

  • An Improved YOLO for Tiny Rocks Detection in Spacecraft Autonomous Landing International conference

    #Xi Chen, @Mai Bando, @Shinji Hokamoto

    Asia-Pacific International Symposium on Aerospace Technology (APISAT 2022)  2022.10 

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    Language:English  

    Venue:online   Country:Japan  

  • 大気抵抗力の差を用いた非協力物体へのランデブー

    安田武弘,@坂東麻衣, @外本伸治

    第66回宇宙科学技術連合講演会  2022.11 

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    Language:Japanese  

    Venue:熊本   Country:Japan  

  • ハミルトン系のフローのクープマン作用素に基づく非線型最適制御

    #佐藤杏輔,@坂東麻衣, @外本伸治

    第66回宇宙科学技術連合講演会  2022.11 

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    Venue:熊本   Country:Japan  

  • 凸最適化による軌道間の低推力最適遷移軌道の設計

    #平岩尚樹,@坂東麻衣, @外本伸治

    第66回宇宙科学技術連合講演会  2022.11 

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    Venue:熊本   Country:Japan  

  • 地球-月三体問題の周期軌道における姿勢運動の解析

    #林勇太,@坂東麻衣, @外本伸治

    第66回宇宙科学技術連合講演会  2022.11 

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    Venue:熊本   Country:Japan  

  • データ駆動型解析による地球-月三体問題におけるカオス軌道の解析

    #浦志太勢, @坂東麻衣, @吉村康広, @花田俊也, @陳泓儒, @外本伸治

    第66回宇宙科学技術連合講演会  2022.11 

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    Venue:熊本   Country:Japan  

  • リアルタイム動的モード分解に基づく小惑星着陸を目的としたデータ駆動型誘導制御

    #梶川大河,@坂東麻衣, @外本伸治

    第66回宇宙科学技術連合講演会  2022.11 

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    Venue:熊本   Country:Japan  

  • 木星の多体力学系におけるポアンカレマップを用いた衛星ツアー軌道の設計

    #池田幹太,@坂東麻衣, @外本伸治

    第66回宇宙科学技術連合講演会  2022.11 

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    Venue:熊本   Country:Japan  

  • 確率的勾配降下法Adamを用いた軌道最適化

    #平山翔大,#平岩尚樹,@坂東麻衣, @外本伸治

    第66回宇宙科学技術連合講演会  2022.11 

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    Venue:熊本   Country:Japan  

  • 超小型衛星によるインターセプト式を利用した彗星遷移軌道の設計

    #山口宗生,#平岩尚樹,@坂東麻衣, @外本伸治

    第66回宇宙科学技術連合講演会  2022.11 

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    Venue:熊本   Country:Japan  

  • 外乱を考慮した火星エアロキャプチャの誘導制御系の検討

    #千種あゆ美,#平岩尚樹,@坂東麻衣, @外本伸治

    第66回宇宙科学技術連合講演会  2022.11 

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    Venue:熊本   Country:Japan  

  • 新しいチルトローター機のローター数と配置に関する研究

    #宮部司嵯,@坂東麻衣, @外本伸治

    日本航空宇宙学会西部支部講演会(2022)  2022.11 

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    Venue:online   Country:Japan  

  • 太陽-地球-月系四体問題を利用した彗星観測ミッションとその実現性に関する検討

    #山口宗生,#平岩尚樹,@坂東麻衣, @外本伸治

    日本航空宇宙学会西部支部講演会(2022)  2022.11 

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    Venue:online   Country:Japan  

  • 複眼視覚航法を用いた小型無人航空機の運動・距離推定

    #本田悠樹,@坂東麻衣, @外本伸治

    第65回自動制御連合講演会  2022.11 

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    Venue:宇都宮   Country:Japan  

  • ジャイロ効果と反トルクがマルチローター機の姿勢変更に及ぼす影響

    #石田匠,#倉橋征椰,@坂東麻衣, @外本伸治

    第41回計測自動制御学会九州支部学術講演会  2022.12 

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    Venue:北九州   Country:Japan  

  • マルチローターの実験データによるデータ駆動型状態推定

    #塩塚竜也,#梶川大河,@坂東麻衣, @長崎秀司, @外本伸治

    第10回 計測自動制御学会制御部門マルチシンポジウム  2023.3 

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    Venue:草津   Country:Japan  

  • Bio-inspired Autonomous Flying System Based on Wide-Field-Integration of Optic Flow Invited International conference

    @Shinji Hokamoto

    AeroResCon&MechResCon2023  2023.3 

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    Venue:Fiano Romano, Rome   Country:Italy  

  • Discrete-Time Attitude Control for Spacecraft Using Iterative Learning International conference

    #Yuta Hayashi, @Mai Bando, @Shinji Hokamoto

    The 34th Congress of the International Council of the Aeronautical Sciences  2023.6 

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    Venue:Kurume   Country:Japan  

  • Optimal Transfer by Stochastic Gradient Descent Algorithm ADAM International conference

    #Shodai Hirayama, #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    The 34th Congress of the International Council of the Aeronautical Sciences  2023.6 

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    Venue:Kurume   Country:Japan  

  • New Equilibria in Quadratic Optimal Control Systems International conference

    #Ayano Tsuruta, @Mai Bando, Daniel Scheeres, @Shinji Hokamoto

    The 34th Congress of the International Council of the Aeronautical Sciences  2023.6 

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    Venue:Kurume   Country:Japan  

  • Orbital Configuration Control for Space-based Gravitational Wave Observatory in the Three-body Problem International conference

    #Zhengxu Pan, Zhanxia Zhu, @Mai Bando, @Shinji Hokamoto

    The 34th Congress of the International Council of the Aeronautical Sciences  2023.6 

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    Venue:Kurume   Country:Japan  

  • Optimization of Structural Configurations of Spacecraft for Efficient Attitude Change Utilizing Non-holonomic Features International conference

    #Saki Takeuchi, @Mai Bando, @Shinji Hokamoto

    The 34th Congress of the International Council of the Aeronautical Sciences  2023.6 

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    Venue:Kurume   Country:Japan  

  • 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,@Daniel Scheeres, @外本伸治

    第33回アストロダイナミクス・シンポジウム  2023.7 

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    Venue:相模原市   Country:Japan  

  • 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  2023.7 

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    Venue:相模原市   Country:Japan  

  • 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  2023.7 

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    Venue:相模原市   Country:Japan  

  • The Role of Stable Manifolds in Optimal Control under Stochastic Noise International conference

    @Mai Bando, #Shohei Morimitsu, #Takuro Nishimura, @Shinji Hokamoto

    The 10th International Congress on Industrial and Applied Mathematics  2023.8 

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    Venue:Tokyo   Country:Japan  

  • A New Gravitational Wave Observatory Formation Configuration Design and Control Method International conference

    #Zhengxu Pan, @Mai Bando, Zhanxia Zhu, @Shinji Hokamoto

    The 2023 SICE Annual Conference  2023.9 

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    Venue:Mie   Country:Japan  

  • Analysis of Transfer Trajectories in Cislunar Space Using Sequences of Lobe Dynamics International conference

    #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    The 74th International Astronautical Congress  2023.10 

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    Language:English  

    Country:Azerbaijan  

  • Attitude Control Using Iterative Learning Control Considering Orbital Motion of NRHO International conference

    #Yuta Hayashi, #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    The 74th International Astronautical Congress  2023.10 

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    Language:English  

    Country:Azerbaijan  

  • Guidance and Control Algorithm for Mars Aerocapture Considering Uncertainties International conference

    #Ayumi Chikusa, #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    The 74th International Astronautical Congress  2023.10 

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    Language:English  

    Country:Azerbaijan  

  • Optimal Trajectory Design by ADAM under Stochastic Disturbing Acceleration International conference

    #Shodai Hirayama, #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    The 74th International Astronautical Congress  2023.10 

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    Country:Azerbaijan  

  • Mission Strategy to Await Comets by Leveraging Manifolds and Low Thrust International conference

    #Soi Yamaguchi, #Naoki Hiraiwa, @Mai Bando, @Shinji Hokamoto

    The 74th International Astronautical Congress  2023.10 

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    Language:English  

    Country:Azerbaijan  

  • 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

    第66回自動制御連合講演会  2023.10 

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    Venue:仙台   Country:Japan  

  • 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

    第66回自動制御連合講演会  2023.10 

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    Venue:仙台   Country:Japan  

  • eVTOL機の遷移モード安定化に向けた機構提案及び特性解析

    #北波颯,@坂東麻衣, @外本伸治

    第66回自動制御連合講演会  2023.10 

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    Venue:仙台   Country:Japan  

  • 不確定性を含む火星エアロキャプチャの誘導制御系の構築

    #千種あゆ美,#平岩尚樹,@坂東麻衣, @外本伸治

    第67回宇宙科学技術連合講演会  2023.10 

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    Venue:富山   Country:Japan  

  • 不変多様体を利用した低推力彗星待機軌道の設計

    #山口宗生,#平岩尚樹,@坂東麻衣, @外本伸治

    第67回宇宙科学技術連合講演会  2023.10 

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    Venue:富山   Country:Japan  

  • 反復学習制御による軌道情報を必要としないハロー軌道上の宇宙機の姿勢安定化

    #林勇太,@坂東麻衣, @外本伸治

    第67回宇宙科学技術連合講演会  2023.10 

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    Venue:富山   Country:Japan  

  • ノイズを考慮した円制限三体問題の初期値と制御コストの関係

    #森光翔平,@坂東麻衣, @外本伸治

    第67回宇宙科学技術連合講演会  2023.10 

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    Venue:富山   Country:Japan  

  • ボロノイ図を使った衛星群の被覆制御

    @安田武弘,@坂東麻衣, @外本伸治

    第67回宇宙科学技術連合講演会  2023.10 

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    Venue:富山   Country:Japan  

  • 複眼視覚航法を用いた運動推定における障害物の影響の低減

    #岡林竜一郎,@坂東麻衣, @外本伸治

    日本航空宇宙学会西部支部講演会(2023)  2023.12 

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    Venue:長崎   Country:Japan  

  • Data-Driven Modeling for Multirotor Autonomous Control International conference

    #Tatsuya Shiotsuka, @Mai Bando, @Shinji Hokamoto

    2024 AIAA SciTech Forum  2024.1 

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    Language:English  

    Country:United States  

  • ベイズ最適化を用いたデータ駆動解析の最適化

    #加藤颯太,@坂東麻衣, @外本伸治

    第11回 計測自動制御学会制御部門マルチシンポジウム  2024.3 

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    Venue:広島   Country:Japan  

  • 近点ポアンカレマップと有限時間リアプノフ指数を用いた脱出軌道の解析

    #佐野嵩弥, @Pan Shanshan,@坂東麻衣, @外本伸治

    第11回 計測自動制御学会制御部門マルチシンポジウム  2024.3 

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    Venue:広島   Country:Japan  

  • ラグランジュ点における中心多様体の近似計算

    坂東 麻衣, 秋山 祐貴, Hamidreza Nemati, 外本 伸治

    第58回宇宙科学技術連合講演会  2014.11 

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    Country:Japan  

  • 複数画像によるSFSアルゴリズムを用いた地形推定法

    藤田浩輝,外本伸治

    ロボティクス・メカトロニクス講演会2004  2004.6 

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    Venue:名古屋   Country:Japan  

  • 角運動量保存を利用したテザー衛星の軌道変更

    高橋周平,外本伸治

    ロボティクス・メカトロニクス講演会2004  2004.6 

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    Venue:名古屋   Country:Japan  

  • 多様体への収束を利用した宇宙ロボットの姿勢制御についての一考察

    松野崇,外本伸治

    ロボティクス・メカトロニクス講演会2004  2004.6 

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    Venue:名古屋   Country:Japan  

  • Considerations on Control for a Tethered Satellite System through Angular Momentum Conservation International conference

    Shinji Hokamoto

    55th International Astronautical Congress  2004.10 

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    Presentation type:Oral presentation (general)  

    Venue:Vancouver   Country:Canada  

  • 非ホロノミック性を利用したテザー衛星の軌道変更に関する研究

    外本伸治

    第48回宇宙科学技術連合講演会  2004.10 

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    Venue:福井   Country:Japan  

  • 多様体を用いた3次元猫ひねりロボットの状態フィードバック制御に関する研究

    松野崇,外本伸治

    ロボティクス・メカトロニクス講演会2005  2005.5 

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    Venue:神戸   Country:Japan  

  • Consideration on Attitude Control of a Space Robot Using Manifolds

    Shinji Hokamoto

    アストロダイナミクスシンポジウム  2005.7 

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    Presentation type:Oral presentation (general)  

    Venue:神奈川   Country:Japan  

  • Orbital Control of Satellite System Using Nonholonomic Control Theory International conference

    Shinji Hokamoto

    Astrodynamics Specialist Conference  2005.8 

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    Presentation type:Oral presentation (general)  

    Venue:Lake Tahoe   Country:United States  

  • Orbital Control of a Tethered Satellite System Using Tether-Length Variations International conference

    Shinji Hokamoto

    56th International Astronautical Congress  2005.10 

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    Presentation type:Oral presentation (general)  

    Venue:Fukuoka   Country:Japan  

  • マニフォールドを利用した宇宙ロボットの姿勢制御に関する研究

    船迫俊郎,外本伸治

    ロボティクス・メカトロニクス講演会2006  2006.5 

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    Venue:東京   Country:Japan  

  • Considerations on Orbital Control of a Rigid Satellite System under Nonholonomic Constraint International conference

    Koki Fujita, Shinji Hokamoto

    25th International Symposium on Space Technology and Science  2006.6 

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    Presentation type:Oral presentation (general)  

    Venue:Kanazawa   Country:Japan  

  • Conceptual Study on a Legged Planetary Rover of Isotropic Shape International conference

    Shinji Hokamoto, Shinji Nishikori, Takashi Kubota

    the 16th Workshop on JAXA Astrodynamics and Flight Mechanics  2006.7 

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    Venue:Sagamihara   Country:Japan  

  • Reorientation of a Space Robot Using a Virtual Desired Configuration International conference

    Shinji Hokamoto, Toshirou Funasako

    16th Workshop on JAXA Astrodynamics and Flight Mechanics  2006.7 

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    Venue:Sagamihara, Kanagawa   Country:Japan  

  • Considerations on a Feedback Control System for a Space Robot Reorientation International conference

    Shinji Hokamoto, Toshirou Funasako

    AIAA/AAS Astrodynamics Specialist Conference  2006.8 

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    Venue:Keystone, Colorado   Country:United States  

  • 人工衛星の内力を利用した軌道変更法について

    古賀笑平,外本伸治

    日本機械学会2006年次大会  2006.9 

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    Country:Japan  

  • 三次元等方脚配置を有する脚式惑星探査ローバーに関する研究

    錦織慎治,外本伸治

    日本航空宇宙学会西部支部講演会  2006.10 

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    Country:Japan  

  • マニフォールドを利用した宇宙ロボットの姿勢制御に関する研究

    船迫俊郎,外本伸治

    計測自動制御学会九州支部学術講演会  2006.12 

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    Country:Japan  

  • 三次元的回転歩行可能な月・惑星探査ローバの概念研究

    錦織慎治,外本伸治,久保田孝

    2007.5 

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    Venue:秋田   Country:Japan  

  • Tether Length Control for Orbital Transfer of Tethered Satellite International conference

    Shinji Hokamoto, Naritoyo Shibata

    the 17th Workshop on JAXA Astrodynamics and Flight Mechanics  2007.7 

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    Venue:Sagamihara   Country:Japan  

  • A Consideration on Lander’s Motion Estimation from Range Image Sequence Utilizing LRF International conference

    Koki Fujita, Shinji Hokamoto

    the 17th Workshop on JAXA Astrodynamics and Flight Mechanics  2007.7 

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    Venue:Sagamihara   Country:Japan  

  • ピッチ運動制御を用いたテザー衛星の軌道変換に関する研究

    外本伸治,柴田成豊,古賀笑平

    機械学会年次大会2007  2007.7 

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    Presentation type:Oral presentation (general)  

    Venue:大阪   Country:Japan  

  • Control Laws for Orbital Parameters of Rigid Satellite System Considering Nonholonomic Constraint International conference

    Koki Fujita, Shinji Hokamoto

    Guidance, Navigation, and Control Conference  2007.8 

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    Venue:Hilton Head, South Carolina   Country:United States  

  • ソーラーセイルを用いた惑星ランデブー軌道の設計手法に関する研究

    幸本宏治,外本伸治

    日本航空宇宙学会西部支部講演会2007  2007.11 

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    Venue:熊本   Country:Japan  

  • 月面探査ローバーにおける自律的なスタック回避に関する研究

    久保川潤一,松原学,外本伸治

    日本航空宇宙学会西部支部講演会2007  2007.11 

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    Venue:熊本   Country:Japan  

  • テザー衛星の軌道変更問題に対するフィードバック制御の検討

    古賀笑平,外本伸治

    第50回自動制御連合講演会  2007.11 

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    Venue:横浜   Country:Japan  

  • Feedback Control for Orbital Transfer of Tethered Satellite System International conference

    Masaoki Iwase, Shohei Koga, Shinji Hokamoto

    The Eighth Japan/Korea Joint Workshop on Aeronautics and Astronautics  2007.12 

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    Country:Japan  

  • 吸着脚をもつ壁面移動ロボットの開発

    外本伸治,石田雄太郎,森満大輔,松原学

    機械学会九州支部第61期総会・講演会  2008.3 

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    Country:Japan  

  • 三次元等方脚配置を有する惑星探査ローバの歩行姿勢の検討

    錦織慎治,外本伸治,久保田孝

    ROBOMEC2009  2009.5 

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    Country:Japan  

  • 吸着脚をもつ壁面移動ロボットの姿勢に関する検討

    石田雄太郎,松原学,外本伸治

    ROBOMEC2009  2009.5 

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    Country:Japan  

  • Effective Attitude of a Multi-Legged Planetary Exploration Rover with Isotopic Leg Arrangement

    Shinji Nishikori, Shinji Hokamoto, Takashi Kubota

    19th Workshop on JAXA Astrodynamics and Flight Mechanics  2009.7 

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    Country:Japan  

  • 2入力による衛星の3軸姿勢制御

    吉村康広,外本伸治

    第53回宇宙科学技術連合講演会  2009.9 

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    Country:Japan  

  • 回転カメラを用いた惑星探査ローバの環境認識に関する研究

    金澤拓海,松原学,外本伸治

    ロボティクス・メカトロニクス講演会2010  2010.6 

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    Country:Japan  

  • 吸着脚を持つ四足歩行ロボットの壁面歩行に関する実験的研究

    北田啓一郎,松原学,外本伸治

    ロボティクス・メカトロニクス講演会2010  2010.6 

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    Country:Japan  

  • Approach for Optimal Multi-Rendezvous Trajectory Design for Active Debris Removal

    村上純子,外本伸治

    アストロダイナミクスシンポジウム  2010.7 

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    Country:Japan  

  • Evaluation on Efficient Attitude of a Multi-Legged Planetary Exploration Rover with Isotropic Leg Arrangement International conference

    Shinji Nishikori, Shinji Hokamoto

    12th International Space Conference of Pacific-basin Societies  2010.7 

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    Country:Canada  

  • Interplanetary Trajectory Design of Solar Sail Spacecraft Utilizing an Invariant Manifold International conference

    Yutaro Ishida, Shinji Hokamoto

    AIAA/AAS Astrodynamics Specialist Conference  2010.8 

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    Country:United States  

  • Position and Attitude Control of a Planar Satellite by Two Constant Force Thrusters International conference

    Takashi Matsuno, Shinji Hokamoto

    AIAA/AAS Astrodynamics Specialist Conference  2010.8 

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    Country:United States  

  • Study on Efficient Attitude of a Multi-Legged Planetary Exploration Rover with Isotropic Leg Arrangement International conference

    Shinji Nishikori, Shinji Hokamoto, Takashi Kubota

    The 10th International Symposium on Artificial Intelligence, Robotics and Automation in Space  2010.8 

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    Country:Japan  

  • Approach for Optimal Multi-Rendezvous Trajectory Design for Active Debris Removal International conference

    Junko Murakami, Shinji Hokamoto

    The 61st International Astronautical Congress  2010.10 

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    Country:Czech Republic  

  • SLIMランダーの転倒可能性に関する検討

    外本伸治

    第54回宇宙科学技術連合講演会  2010.11 

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    Presentation type:Oral presentation (general)  

    Country:Japan  

  • Three Dimensional Attitude Control of an Underactuated Satellite with Thrusters International conference

    Yasuhiro Yoshimura, Takashi Matsuno, Shinji Hokamoto

    The 4th Asia International Symposium on Mechatronics  2010.12 

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    Country:Singapore  

  • 遺伝的アルゴリズムを用いた複数個ターゲットへのランデブー軌道計画

    村上純子,外本伸治

    第19回スペース・エンジニアリング・コンファレンス  2011.1 

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    Country:Japan  

  • オプティカルフローの広域統合法による探査機の状態推定

    金澤拓海,マイケル・シューメーカー,外本伸治

    第28回誘導制御シンポジウム  2011.1 

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  • 三次元等方脚配置型ローバの動的な回転運動

    錦織慎治,外本伸治,久保田孝

    第12回「運動と振動の制御」シンポジウム  2011.6 

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    Country:Japan  

  • 3-D Attitude Control of an Underactuated Satellite with Constant Inputs

    Yasuhiro Yoshimura, Takashi Matsuno, Shinji Hokamoto

    28th International Symposium on Space Technology and Science  2011.6 

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    Country:Japan  

  • Genetic-Algorithm-Based Rendezvous Trajectory Design for Multiple Active Debris Removal International conference

    Shinji Hokamoto, Junko Murakami

    28th International Symposium on Space Technology and Science  2011.6 

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    Presentation type:Oral presentation (general)  

    Country:Japan  

  • Relative Navigation Near Asteroid Using Wide-Field Integration of Optic Flow

    Michael A. Shoemaker, Shinji Hokamoto

    28th International Symposium on Space Technology and Science  2011.6 

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    Country:Japan  

  • Satellite Position and Attitude Control by On-Off Thrusters Considering Mass Change

    Yasuhiro Yoshimura, Takashi Matsuno, Shinji Hokamoto

    Astrodynamics Specialist Conference  2011.8 

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    Country:United States  

  • Application of Wide-Field Integration of Optic Flow to Proximity Operations and Landing for Space Exploration Missions

    Michael A. Shoemaker, Shinji Hokamoto

    Astrodynamics Specialist Conference  2011.8 

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    Country:United States  

  • Position and Attitude Control of an Underactuated Satellite with Constant Thrust

    Yasuhiro Yoshimura, Takashi Matsuno, Shinji Hokamoto

    AIAA Guidance, Navigation and Control Conference  2011.8 

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    Country:United States  

  • 並進・回転カメラによる探査ローバの環境認識に関する研究

    坂本博史,金澤拓海,外本伸治

    日本機械学会 2011年度年次大会  2011.9 

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  • 少数スラスタによる人工衛星のフライアラウンド軌道への投入

    柘植俊佑,外本伸治

    日本航空宇宙学会西部支部講演会  2011.11 

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  • オプティカルフローの広域統合法による惑星着陸探査機の状態推定

    金澤拓海,マイケル・シューメーカー,外本伸治

    第54回自動制御連合講演会  2011.11 

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    Country:Japan  

  • SLIMの機体ピッチ角による着地後の挙動制御に関する検討

    中田孝幸,錦織慎治,外本伸治

    第55回宇宙科学技術連合講演会  2011.11 

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    Country:Japan  

  • 方向が機体に固定された3本のスラスターによる人工衛星の姿勢制御

    松野崇,吉村康広,外本伸治

    第55回宇宙科学技術連合講演会  2011.11 

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    Country:Japan  

  • Fly-Around Orbit Design with Thrusters Fixed to Satellite

    Shunsuke Tsuge, Shinji Hokamoto

    5th Kyushu Univ. –KAIST Symposium on Aerospace Engineering  2011.11 

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    Country:Japan  

  • Sliding Mode Control of Satellite Formation Flying

    Hamidreza Nemati, Shinji Hokamoto

    5th Kyushu Univ. –KAIST Symposium on Aerospace Engineering  2011.11 

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    Country:Japan  

  • 姿勢角変化に伴うSLIM着陸時の挙動解析

    中田孝幸, 錦織慎治, 外本 伸治

    第12回宇宙科学シンポジウム  2012.1 

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    Language:Japanese  

    Country:Japan  

  • SLIMの機体ピッチ角による着陸後の挙動制御に関する検討

    中田孝幸, 錦織慎治, 外本 伸治

    第2回小型科学衛星シンポジウム  2012.3 

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    Language:Japanese  

    Country:Japan  

  • オプティカルフローの広域統合法による宇宙着陸探査機の自律制御

    坂本博史, 金澤拓海, 外本 伸治

    ロボティクス・メカトロニクス講演会  2012.5 

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    Country:Japan  

  • 並進・回転カメラによる探査ローバの環境認識に関する研究

    桜井景太, 坂本博史, 外本 伸治

    ロボティクス・メカトロニクス講演会  2012.5 

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    Language:Japanese  

    Country:Japan  

  • エアベアリングを用いた3 次元姿勢制御試験装置の開発

    吉村康広, 松隈洋平, 柘植俊佑, 外本 伸治

    ロボティクス・メカトロニクス講演会  2012.5 

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    Language:Japanese  

    Country:Japan  

  • A Novel Chattering-Free Sliding Mode Controller for Attitude Control of a Microsatellite

    Hamidreza Nemati, Shinji Hokamoto

    Astrodynamics Symposium  2012.7 

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    Country:Japan  

  • Wide Field Integration of Optic Flow for Space Exploration Missions International conference

    Shinji Hokamoto, Michael Shoemaker, Takumi Kanazawa, Hirofumi Sakamoto

    The Sixth KAIST-Kyushu University Joint Workshop  2012.9 

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    Country:Korea, Republic of  

  • Attitude Control of an Underactuated Satellite with Constant Torques International conference

    Yasuhiro Yoshimura, Shinji Hokamoto

    The Sixth KAIST-Kyushu University Joint Workshop  2012.9 

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    Country:Korea, Republic of  

  • A Novel Chattering-Free Sliding Mode Controller for Satellite’s Attitude Motion International conference

    Hamidreza Nemati, Shinji Hokamoto

    The Sixth KAIST-Kyushu University Joint Workshop  2012.9 

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    Country:Korea, Republic of  

  • Relative Attitude and Orbital Control with a Fewer Thrusters for Rendezvous-Docking International conference

    Shunsuke Tsuge, Shinji Hokamoto

    The Sixth KAIST-Kyushu University Joint Workshop  2012.9 

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    Country:Korea, Republic of  

  • Attitude Angle Estimation of Space Probe with Wide-Field Integration of Optic Flow International conference

    Hirofumi Sakamoto, Shinji Hokamoto

    The Sixth KAIST-Kyushu University Joint Workshop  2012.9 

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    Country:Korea, Republic of  

  • 詳細モデルを用いたSLIMの着陸時の挙動に関する検討

    中田孝幸, 錦織慎治, 外本 伸治

    第56回宇宙科学技術連合講演会  2012.11 

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    Country:Japan  

  • 3次元等方脚配置型ローバの天体表面移動性能に関する検討

    錦織慎治, 外本 伸治, 久保田孝

    第56回宇宙科学技術連合講演会  2012.11 

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    Country:Japan  

  • SLIM着陸時のピッチ角制御と挙動解析

    中田孝幸, 錦織慎治, 外本 伸治

    第13回宇宙科学シンポジウム  2013.1 

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    Country:Japan  

  • スライディングモード制御によるモデル化誤差を含む宇宙機の姿勢制御

    上野宙輝, 外本 伸治

    第21回スペース・エンジニアリング・コンファレンス  2013.1 

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    Country:Japan  

  • SLIM着陸時のピッチ角制御と挙動解析

    中田孝幸, 錦織慎治, 外本 伸治

    第3回小型科学衛星シンポジウム  2012.3 

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    Country:Japan  

  • State Estimation of Planetary Landing Vehicles with Wide-Field Integration of Optic Flow

    Hirofumi Sakamoto, Takumi Kanazawa, Shinji Hokamoto

    The 13th International Space Conference of Pacific-basin Societies  2012.5 

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    Country:Japan  

  • Study on a Reasonable Locomotion of a Multi-Legged Rover Using its Dynamic Motion International conference

    Shinji Nishikori, Shinji Hokamoto

    International Symposium on Artificial Intelligence, Robotics and Automation in Space  2012.9 

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    Language:English  

    Country:Italy  

  • Relative Attitude and Orbital Control with a Fewer Thrusters for Rendezvous-Docking

    Shunsuke Tsuge, Shinji Hokamoto

    Asia-Pacific International Symposium on Aerospace Technology  2012.11 

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    Country:Korea, Republic of  

  • Chattering Attenuation Sliding Mode Control of a Satellite’s Attitude

    Hamidreza Nemati, Shinji Hokamoto

    The 23rd AAS/AIAA Space Flight Mechanics Meeting  2013.2 

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    Country:United States  

  • Optimal Formation Reconfiguration of Satellites with Attitude Constraints Using Thrusters International conference

    Yasuhiro Yoshimura, Shinji Hokamoto

    5th International Conference on Spacecraft Formation Flying Missions and Technologies  2013.5 

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    Language:English  

    Country:Germany  

  • Attitude Angle Estimation of Space Probe through Wide-Field Integration of Optic Flow International conference

    Hirofumi Sakamoto, Shinji Hokamoto

    29th International Symposium on Space Technology and Science  2013.6 

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    Country:Japan  

  • New Chattering Attenuation Sliding Mode Control of a Flexible Spacecraft International conference

    Hamidreza Nemati, Shinji Hokamoto

    29th International Symposium on Space Technology and Science  2013.6 

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    Country:Japan  

  • Relative Position and Attitude Control of a Satellite with Unilateral Inputs International conference

    Yasuhiro Yoshimura, Shunsuke Tsuge, Shinji Hokamoto

    29th International Symposium on Space Technology and Science  2013.6 

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    Country:Japan  

  • Design Procedure of Chattering Attenuation Sliding Mode Attitude Control of a Satellite System

    Hamidreza Nemati, Shinji Hokamoto

    The 24th AAS/AIAA Space Flight Mechanics Meeting  2014.1 

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    Country:United States  

  • クアッドコプターの位置・姿勢運動に対するロバスト制御

    松藤弘樹, 大石宜卓, 金城寛, 外本伸治

    ロボティクス・メカトロニクス講演会2013  2013.5 

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    Country:Japan  

  • レーザーレンジファインダー(LRF)による探査ローバの自律移動に関する研究

    桜井景太, 外本伸治

    「運動と振動の制御」シンポジウム  2013.8 

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    Country:Japan  

  • レーザーレンジファインダーのみによる自律移動の可能性について

    雲凱, 桜井景太, 金城寛, 外本伸治

    アストロダイナミクス・シンポジウム  2013.7 

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    Country:Japan  

  • SLIM着陸時における挙動解析の比較

    雲凱, ハミドレザ ネマティ, 外本伸治

    宇宙科学技術連合講演会  2013.10 

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    Country:Japan  

  • 脚式移動ローバの動的回転運動による天体表面移動性能

    錦織慎治, 外本伸治, 久保田孝

    宇宙科学技術連合講演会  2013.10 

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    Language:Japanese  

    Country:Japan  

  • On the Possibility of Using Small Asteroids for Deflecting Near-Earth Asteroids

    Yuki Akiyama, Mai Bando, Shinji Hokamoto

    KAIST-Kyushu University Symposium on Aerospace Engineering  2013.11 

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    Country:Korea, Republic of  

  • State Estimation of Quadrotor with Wide-Field Integration of Optic Flow

    Masataka Oishi, Hiroki Matsufuji, Shinji Hokamoto

    KAIST-Kyushu University Symposium on Aerospace Engineering  2013.11 

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    Country:Korea, Republic of  

  • Robust Attitude Control of Spacecraft by Sliding Mode Technique

    Hiroki Ueno, Shinji Hokamoto

    KAIST-Kyushu University Symposium on Aerospace Engineering  2013.11 

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    Country:Korea, Republic of  

  • 低推力宇宙機の平均的な軌道変化の推定

    坂東 麻衣, 伊達直輝, 外本伸治

    SICEシステムインテグレーション部門講演会  2013.12 

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    Country:Japan  

  • マルチエージェントの間接制御についての検討

    野田旬太郞, 坂東 麻衣, 外本伸治

    自律分散システム・シンポジウム  2014.1 

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    Country:Japan  

  • Design Procedure of Chattering Attenuation Sliding Mode Attitude Control of a Satellite System

    Hamidreza Nemati, Shinji Hokamoto

    The 24th AAS/AIAA Space Flight Mechanics Meeting  2014.1 

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    Country:United States  

  • 宇宙状況認識へ向けた低推力宇宙機の軌道推定手法の提案

    伊達直輝, 坂東 麻衣, 外本伸治

    マルチシンポジウム  2014.3 

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    Country:Japan  

  • 並進・回転機構を持つカメラによる探査ローバの環境認識に関する研究

    小林直人, 桜井景太, 金城寛, 外本伸治

    マルチシンポジウム  2014.3 

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    Country:Japan  

  • Realistic terrain reconstruction method by using laser-range-finder International conference

    Kai Yun, Keita Sakurai, Shinji Hokamoto

    The 14th International Space Conference of Pacific-basin Societies  2014.4 

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    Country:China  

  • 低推力宇宙機の軌道推定手法に関する考察

    伊達 直輝, 坂東 麻衣, 外本 伸治

    アストロダイナミクス・シンポジウム  2014.7 

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    Country:Japan  

  • 円制限三体問題におけるフォーメーション制御則について

    坂東 麻衣, Hamidreza Nemati, 秋山祐貴, 外本 伸治

    アストロダイナミクス・シンポジウム  2014.7 

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    Language:Japanese  

    Country:Japan  

  • New Continuous Sliding Mode Design for Spacecraft Attitude Control

    Hamidreza Nemati, Masataka Oishi, Naoto Kobayashi, Ryusuke Nakata, Shinji Hokamoto

    アストロダイナミクス・シンポジウム  2014.7 

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    Country:Japan  

  • 複眼視覚航法を用いた誘導制御 Invited

    外本 伸治

    アストロダイナミクス・シンポジウム  2014.7 

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    Language:Japanese   Presentation type:Oral presentation (invited, special)  

    Country:Japan  

    昆虫の複眼視覚を工学的に模倣したオプティカルフローの広域統合法と呼ばれる手法について,その原理や設計手法,および期待される効果について説明した.この手法は,小型軽量で計算負荷が小さいにもかかわらず,未知の環境地形にロバストに運動状態を推定することができるため,航空機および宇宙機の自律航法システムとして,非常に有用である.

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

    Mai Bando, Naoki Date, Shinji Hokamoto

    The 65th International Astronautical Congress  2014.9 

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    Country:Canada  

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

    Shinji Hokamoto, Masataka Oishi, Naoto Kobayashi, Mai Bando

    The 65th International Astronautical Congress  2014.9 

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    Country:Canada  

  • Wide-Field-Integration of Optic Flowを用いた宇宙機の運動推定

    大石 宜卓, 小林 直人, 外本 伸治

    第58回宇宙科学技術連合講演会  2014.11 

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    Language:Japanese  

    Country:Japan  

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MISC

  • 複眼視覚航法を用いた航空機・宇宙機の運動推定システム

    @外本 伸治

    計測と制御   2018.4

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    Language:Japanese   Publishing type:Article, review, commentary, editorial, etc. (scientific journal)  

    本解説では,飛翔する昆虫が持つ複眼認識システムを航空機・宇宙機に適用することで,未知環境においても自律航行を可能にするシステムについて説明する.まず航空機・宇宙機に搭載されるシステムには,小型・軽量であることが要求される.また自律システムであるためには,オンボードのCPUで処理しなければならないため,計算負荷が小さいことも重要な要素である.さらに,多くの場合,未知環境に対してのロバスト性も要求される.ここでは,画像センサからオプティックフローを求め,その情報を広範囲に統合する“複眼視覚航法”について説明する.これは,複眼を持つ昆虫の視神経回路網で行われていると考えられている処理手法を,工学システムで模擬しようとするものである.

  • ”ドローン(無人航空機)”って何?

    外本 伸治

    九州学士会報,第37号   2016.8

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    Language:Japanese  

  • 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ンシップ

    坂東 麻衣, 外本 伸治

    工学教育   2014.3

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    Language:Japanese  

Industrial property rights

Patent   Number of applications: 1   Number of registrations: 0
Utility model   Number of applications: 0   Number of registrations: 0
Design   Number of applications: 0   Number of registrations: 0
Trademark   Number of applications: 0   Number of registrations: 0

Professional Memberships

  • 計測自動制御学会

  • 日本機械学会

  • 日本航空宇宙学会

  • American Institute of Aeronautics and Astonautics

  • 計測自動制御学会

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  • 日本航空宇宙学会

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  • 日本機械学会

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  • 日本ロボット学会

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  • アメリカ航空宇宙学会(American Institute of Aeronautics and Astronautics)

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  • Society of Instrument and Control Engineering

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  • Japan Society of Mechanical Engineering

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  • Japan Society for Aeronautics and Space Sciences

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  • American Institute of Aeronautics and Astronautics

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  • American Institute of Aeronautics and Astonautics

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Committee Memberships

  • 九州大学   人事委員会委員  

    2021.4 - 2023.3   

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    Committee type:Other

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  • 日本航空宇宙学会 西部支部   Organizer   Domestic

    2021.3 - 2022.2   

  • 九州大学   学府学務委員会委員  

    2020.4 - 2022.3   

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    Committee type:Other

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  • 日本航空宇宙学会 西部支部   支部長   Domestic

    2020.3 - 2021.2   

  • 機械学会 ロボメカ委員   Organizer   Domestic

    2019.4 - 2021.3   

  • 日本航空宇宙学会 西部支部   副支部長   Domestic

    2019.3 - 2020.2   

  • 日本航空宇宙学会 西部支部   Organizer   Domestic

    2018.1 - 2022.1   

  • 日本航空宇宙学会 西部支部   幹事   Domestic

    2018.1 - 2022.1   

  • 日本航空宇宙学会 西部支部   幹事  

    2018.1   

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  • IAC Astrodynamics session 委員   Organizer   Foreign country

    2014.11 - 2021.10   

  • 日本航空宇宙学会 西部支部   幹事   Domestic

    2011.2 - 2015.2   

  • 日本航空宇宙学会 西部支部   Organizer   Domestic

    2010.3 - 2011.2   

  • 日本航空宇宙学会 西部支部   会計幹事,常任幹事   Domestic

    2010.3 - 2011.2   

  • 日本航空宇宙学会 西部支部   常任幹事   Domestic

    2009.2 - 2011.2   

  • 計測自動制御学会 九州支部   Organizer   Domestic

    2006.1 - 2008.1   

  • 計測自動制御学会 九州支部   事業委員   Domestic

    2004.1 - 2007.1   

  • 日本航空宇宙学会   宇宙航行部門委員   Domestic

    2000.4 - 2003.3   

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Academic Activities

  • セッションオーガナイザー

    第67回 宇宙科学技術連合講演会  ( Japan ) 2023.10

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  • 世話人

    アストロダイナミクスシンポジウム  ( Japan ) 2023.7

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    Type:Competition, symposium, etc. 

  • 座長(司会)

    アストロダイナミクスシンポジウム  ( Japan ) 2023.7

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    Type:Competition, symposium, etc. 

  • LOC委員(地元事業実行委員) International contribution

    34th ISTS  ( Japan ) 2023.6

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship) International contribution

    34th ISTS  ( Japan ) 2023.6

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    Type:Competition, symposium, etc. 

  • chairman International contribution

    AeroResCon&MechResCon2023  ( Italy ) 2023.3

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    Type:Competition, symposium, etc. 

  • Screening of academic papers

    Role(s): Peer review

    2023

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    Type:Peer review 

    Number of peer-reviewed articles in foreign language journals:9

    Number of peer-reviewed articles in Japanese journals:0

  • 座長(司会)

    第66回 宇宙科学技術連合講演会  ( Japan ) 2022.11

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    Type:Competition, symposium, etc. 

  • セッションオーガナイザー

    第66回 宇宙科学技術連合講演会  ( Japan ) 2022.11 - 2021.11

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    Type:Competition, symposium, etc. 

  • 座長(司会)

    アストロダイナミクスシンポジウム  ( Japan ) 2022.7

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    Type:Competition, symposium, etc. 

  • 世話人

    アストロダイナミクスシンポジウム  ( Japan ) 2022.7

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    Type:Competition, symposium, etc. 

  • Committee member

    AerospaceForum 2022  ( Spain ) 2022.4 - 2022.10

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    Type:Competition, symposium, etc. 

  • Screening of academic papers

    Role(s): Peer review

    2022

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    Type:Peer review 

    Number of peer-reviewed articles in foreign language journals:6

    Number of peer-reviewed articles in Japanese journals:1

  • 座長(司会)

    第65回 宇宙科学技術連合講演会  ( Japan ) 2021.11

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  • セッションオーガナイザー

    第65回 宇宙科学技術連合講演会  ( Japan ) 2021.11

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  • 座長(司会)

    アストロダイナミクスシンポジウム  ( Japan ) 2021.7

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    Type:Competition, symposium, etc. 

  • 世話人

    アストロダイナミクスシンポジウム  ( Japan ) 2021.7

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    Type:Competition, symposium, etc. 

  • 宇宙科学に関する学術研究およびこれに関する業務について,宇宙航空研究開発機構 宇宙科学研究所長の諮問に答える

    宇宙科学運営協議会 運営協議員  2021.4 - 2023.3

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  • Screening of academic papers

    Role(s): Peer review

    2021

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    Type:Peer review 

    Number of peer-reviewed articles in foreign language journals:7

  • 座長(司会)

    第64回 宇宙科学技術連合講演会  ( Japan ) 2020.10

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  • セッションオーガナイザー

    第64回 宇宙科学技術連合講演会  ( Japan ) 2020.10

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    Type:Competition, symposium, etc. 

  • Screening of academic papers

    Role(s): Peer review

    2020

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    Type:Peer review 

    Number of peer-reviewed articles in foreign language journals:4

    Proceedings of International Conference Number of peer-reviewed papers:41

  • 座長(Chairmanship)

    日本航空宇宙学会西部支部講演会  ( Japan ) 2019.11

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    Type:Competition, symposium, etc. 

  • セッションオーガナイザー

    第63回 宇宙科学技術連合講演会  ( Japan ) 2019.11

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    Type:Competition, symposium, etc. 

  • Chairman International contribution

    International Astronautical Congress  ( UnitedStatesofAmerica ) 2019.10

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship) International contribution

    32nd ISTS  ( Japan ) 2019.6

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    Type:Competition, symposium, etc. 

  • Screening of academic papers

    Role(s): Peer review

    2019

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    Type:Peer review 

    Number of peer-reviewed articles in foreign language journals:8

    Proceedings of International Conference Number of peer-reviewed papers:49

  • セッションオーガナイザー

    第62回 宇宙科学技術連合講演会  ( Japan ) 2018.10

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    Type:Competition, symposium, etc. 

  • Chairman International contribution

    International Astronautical Congress  ( Germany ) 2018.9

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship)

    アストロダイナミクスシンポジウム  ( Japan ) 2018.7

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    Type:Competition, symposium, etc. 

  • Screening of academic papers

    Role(s): Peer review

    2018

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    Type:Peer review 

    Number of peer-reviewed articles in foreign language journals:2

    Proceedings of International Conference Number of peer-reviewed papers:67

  • セッションオーガナイザー

    第61回 宇宙科学技術連合講演会  ( Japan ) 2017.10

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    Type:Competition, symposium, etc. 

  • Chairman International contribution

    International Astronautical Congress  ( Austria ) 2017.9

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship) International contribution

    31st ISTS  ( Japan ) 2017.6

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    Type:Competition, symposium, etc. 

  • Astrodynamics Committee member International contribution

    68th International Astronautical Congress  ( Australia ) 2017.4 - 2018.3

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship)

    マルチシンポジウム  ( Japan ) 2017.3

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    Type:Competition, symposium, etc. 

  • Screening of academic papers

    Role(s): Peer review

    2017

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    Type:Peer review 

    Number of peer-reviewed articles in foreign language journals:6

    Proceedings of International Conference Number of peer-reviewed papers:63

  • 不明 International contribution

    International Astronautical Congress  ( Mexico ) 2016.9

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    Type:Competition, symposium, etc. 

  • 実行委員

    日本機械学会2016年度年次大会  ( Japan ) 2016.9

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    Type:Competition, symposium, etc. 

  • セッションオーガナイザー

    第60回宇宙科学技術連合講演会  ( Japan ) 2016.9

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    Type:Competition, symposium, etc. 

  • セッションオーガナイザー

    第60回 宇宙科学技術連合講演会  ( Japan ) 2016.9

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    Type:Competition, symposium, etc. 

  • Astrodynamics Committee member International contribution

    67th International Astronautical Congress  ( Guadarajara Mexico ) 2016.1 - 2016.12

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    Type:Competition, symposium, etc. 

  • 不明 International contribution

    International Astronautical Congress  ( Israel ) 2015.10

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    Type:Competition, symposium, etc. 

  • セッションオーガナイザー

    第59回宇宙科学技術連合講演会  ( Japan ) 2015.10

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  • 座長(Chairmanship),セッションオーガナイザー

    宇宙科学技術連合講演会  ( Japan ) 2015.10

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship) International contribution

    30th ISTS  ( Japan ) 2015.7

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    Type:Competition, symposium, etc. 

  • Astrodynamics Committee member International contribution

    66th International Astronautical Congress  ( Jerusalem Israel ) 2015.1 - 2015.12

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship)

    宇宙科学技術連合講演会  ( Japan ) 2014.11

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    Type:Competition, symposium, etc. 

  • セッションオーガナイザー

    第58回宇宙科学技術連合講演会  ( Japan ) 2014.11

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship)

    アストロダイナミクスシンポジウム  ( Japan ) 2014.7

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    Type:Competition, symposium, etc. 

  • d-セッション委員長 International contribution

    30th International Symposium on Space Technology and Sciences  ( Kobe Japan ) 2014.4 - 2015.12

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship)

    マルチシンポジウム  ( Japan ) 2014.3

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship)

    宇宙科学技術連合講演会  ( Japan ) 2013.11

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship)

    アストロダイナミクスシンポジウム  ( Japan ) 2013.7

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship) International contribution

    29th ISTS  ( Japan ) 2013.6

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    Type:Competition, symposium, etc. 

  • 司会(Moderator)

    宇宙科学技術連合講演会  ( Japan ) 2012.11

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    Type:Competition, symposium, etc. 

  • 司会(Moderator) International contribution

    The Sixth KAIST-Kyushu University Joint Workshop  ( Korea ) 2012.9

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship)

    アストロダイナミクスシンポジウム  ( Japan ) 2012.7

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    Type:Competition, symposium, etc. 

  • 実行委員 International contribution

    29th International Symposium on Space Technology and Sciences  ( Nagoya Japan ) 2012.6 - 2013.7

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  • 司会(Moderator)

    宇宙科学技術連合講演会  ( Japan ) 2011.11

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship)

    日本航空宇宙学会西部支部講演会  ( Japan ) 2011.11

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    Type:Competition, symposium, etc. 

  • 実行委員 International contribution

    28th International Symposium on Space Technology and Sciences  ( Okinawa Japan ) 2011.6 - 2011.11

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  • 司会(Moderator) International contribution

    28th ISTS  ( Japan ) 2011.6

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    Type:Competition, symposium, etc. 

  • 実行委員 International contribution

    18th IFAC Symposium on Automatic Control in Aerospace  ( Nara Japan ) 2010.9

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    Type:Competition, symposium, etc. 

  • 司会(Moderator) International contribution

    KAIST-KU Symposium on Aerospace Engineering  ( Korea ) 2009.12

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship)

    アストロダイナミクスシンポジウム  ( Japan ) 2009.7

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    Type:Competition, symposium, etc. 

  • 司会(Moderator) International contribution

    27th ISTS  ( Japan ) 2009.5

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    Type:Competition, symposium, etc. 

  • 実行委員(チュートリアル担当)

    ロボメック2009  ( Japan ) 2009.5

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  • 座長(Chairmanship)

    アストロダイナミクスシンポジウム  ( Japan ) 2008.8

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship)

    アストロダイナミクスシンポジウム  ( Japan ) 2007.7

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    Type:Competition, symposium, etc. 

  • 座長(Chairmanship)

    アストロダイナミクスシンポジウム  ( Japan ) 2006.7

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  • 座長(Chairmanship)

    アストロダイナミクスシンポジウム  ( Japan ) 2005.7

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  • 見学旅行部会部会長 International contribution

    第56回国際宇宙会議  ( Japan )

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  • 参加登録委員会委員 International contribution

    第24回国際航空科学会議  ( Japan )

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  • 第24回国際航空科学会議 International contribution

    ( 横浜 Japan )

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  • 第56回国際宇宙会議 International contribution

    ( 福岡 Japan )

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Research Projects

  • Hayabusa 2 拡張ミッションプロジェクト

    2022.7

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  • 小型SAR衛星の高度化に向けた姿勢制御系の開発

    2021.4 - 2024.3

    Joint research

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    Authorship:Principal investigator  Grant type:Other funds from industry-academia collaboration

  • 小型SAR衛星の高度化に向けた研究

    2021.4

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    Authorship:Principal investigator 

  • 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

    Grant number:20H02354  2020 - 2023

    Japan Society for the Promotion of Science  Grants-in-Aid for Scientific Research  Grant-in-Aid for Scientific Research (B)

    外本 伸治, 坂東 麻衣

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    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

  • レンズを広角化したPX4Flowセンサ情報を用いたオプティックフローWFI法の研究

    2018.11 - 2019.3

    Research commissions

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  • オプッティクフローWFI法のMAV飛行制御への適用のためのPX4Flowセンサ情報処理技術の研究

    2017.9 - 2018.2

    Research commissions

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    Authorship:Principal investigator  Grant type:Other funds from industry-academia collaboration

  • オプティックフローWFI法のMAV飛行制御への適用のための処理技術の研究

    2016.8 - 2017.3

    Research commissions

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  • 自然に学ぶものづくり 研究助成プログラム 「昆虫の複眼システムに学ぶ屋内自律飛行における障害物回避」

    2016

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    Grant type:Donation

  • オプティカルフロー広域統合法を用いた無人航空機の飛行制御技術の研究

    2015.9 - 2016.3

    Joint research

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    Authorship:Principal investigator  Grant type:Other funds from industry-academia collaboration

  • 複眼視覚航法を用いたロバスト自律航法システムの開発

    Grant number:15K14254  2015 - 2017

    Grants-in-Aid for Scientific Research  Grant-in-Aid for challenging Exploratory Research

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    Authorship:Principal investigator  Grant type:Scientific research funding

  • MAVの屋内航法技術に関する研究

    2014.7 - 2015.3

    Joint research

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    Authorship:Principal investigator  Grant type:Other funds from industry-academia collaboration

  • MAVの屋内航法技術に関する研究

    2013.10 - 2020.3

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    Authorship:Principal investigator 

  • MAVの屋内航法技術に関する研究

    2013.10 - 2014.3

    Joint research

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    Authorship:Principal investigator  Grant type:Other funds from industry-academia collaboration

  • Hayabusa 2 プロジェクト

    2010.4 - 2022.6

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    Authorship:Collaborating Investigator(s) (not designated on Grant-in-Aid) 

  • 光学観測を用いたはやぶさカプセル大気再突入軌道決定

    2010.4 - 2011.3

    Joint research

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    Authorship:Principal investigator  Grant type:Other funds from industry-academia collaboration

  • Hayabusa 光跡観測ミッション

    2010.4 - 2011.3

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    Authorship:Principal investigator 

  • 月小型実験機(SLIM)に関する研究

    2010.4

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    Authorship:Coinvestigator(s) 

  • 工・農技術融合による有機農業の高度化(アイガモロボットの開発)

    2010

    社会連携事業

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    Authorship:Principal investigator  Grant type:On-campus funds, funds, etc.

  • 月惑星探査における不整地移動探査システムの研究

    2008.4 - 2016.3

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    Authorship:Collaborating Investigator(s) (not designated on Grant-in-Aid) 

  • 月資源利用研究会

    2005.4 - 2008.3

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    Authorship:Coinvestigator(s) 

  • ソーラーセイル姿勢/軌道制御系の実験的検証と設計に関する基礎研究

    Grant number:17560699  2005 - 2006

    Grants-in-Aid for Scientific Research  Grant-in-Aid for General Research (C)

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    Authorship:Principal investigator  Grant type:Scientific research funding

  • ソーラーセイルプロジェクト

    2004.4 - 2007.3

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    Authorship:Coinvestigator(s) 

  • 惑星エアロブレーキに関する研究

    2003.4 - 2007.3

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    Authorship:Coinvestigator(s) 

  • 全方向型惑星探査ローバーの開発とその挙動解析・制御に関する研究

    Grant number:12450395  2000 - 2002

    Japan Society for the Promotion of Science  Grants-in-Aid for Scientific Research  Grant-in-Aid for Scientific Research (B)

      More details

    Authorship:Principal investigator  Grant type:Scientific research funding

  • 多重テザー衛星システムのダイナミクスと制御

    1999

    Japan Society for the Promotion of Science  特定国派遣研究者

      More details

    Grant type:Joint research

  • 無重力環境下での柔軟マニピュレータ系の挙動と制御に関する研究

    1997.4 - 1999.3

    Joint research

      More details

    Grant type:Other funds from industry-academia collaboration

▼display all

Educational Activities

  • Undergratuate Course:
    Fundamentals of Guidance and Control I, Fundamentals of Guidance and Control II
    Graduate Course:
    Advanced Guidance and Control I, Instrumentation, Seminar of Aerospace Engineering I, Seminar of Aerospace Engineering II, Aerospace Engineering Laboratory,
    Advanced Guidance and Control

Class subject

  • 機器学特論

    2024.10 - 2025.3   Second semester

  • 誘導・制御基礎論Ⅱ

    2024.10 - 2025.3   Second semester

  • 誘導制御講究

    2024.4 - 2025.3   Full year

  • 航空宇宙工学演習I

    2024.4 - 2025.3   Full year

  • 航空宇宙工学演習Ⅱ

    2024.4 - 2025.3   Full year

  • 誘導・制御基礎論I

    2024.4 - 2024.9   First semester

  • 力学基礎

    2024.4 - 2024.9   First semester

  • 誘導制御特論I

    2023.10 - 2024.3   Second semester

  • 誘導・制御基礎論Ⅱ

    2023.10 - 2024.3   Second semester

  • 航空宇宙工学演習I

    2023.4 - 2024.3   Full year

  • 航空宇宙工学演習Ⅱ

    2023.4 - 2024.3   Full year

  • 誘導制御講究

    2023.4 - 2024.3   Full year

  • 誘導・制御基礎論I

    2023.4 - 2023.9   First semester

  • 航空宇宙工学A

    2023.4 - 2023.6   Spring quarter

  • 誘導・制御基礎論ⅡB

    2022.12 - 2023.2   Winter quarter

  • 機器学特論

    2022.10 - 2023.3   Second semester

  • 誘導・制御基礎論ⅡA

    2022.10 - 2022.12   Fall quarter

  • 航空宇宙工学演習I

    2022.4 - 2023.3   Full year

  • 航空宇宙工学演習Ⅱ

    2022.4 - 2023.3   Full year

  • 誘導制御講究

    2022.4 - 2023.3   Full year

  • 力学基礎

    2022.4 - 2022.9   First semester

  • 誘導・制御基礎論I

    2022.4 - 2022.6   Spring quarter

  • 誘導・制御基礎論ⅡB

    2021.12 - 2022.2   Winter quarter

  • Advanced Guidance and Control I

    2021.10 - 2022.3   Second semester

  • 誘導制御特論I

    2021.10 - 2022.3   Second semester

  • 航空宇宙工学A

    2021.10 - 2021.12   Fall quarter

  • 誘導・制御基礎論ⅡA

    2021.10 - 2021.12   Fall quarter

  • 誘導制御講究

    2021.4 - 2022.3   Full year

  • 航空宇宙工学演習I

    2021.4 - 2022.3   Full year

  • 航空宇宙工学演習Ⅱ

    2021.4 - 2022.3   Full year

  • 力学基礎

    2021.4 - 2021.9   First semester

  • 誘導・制御基礎論I

    2021.4 - 2021.6   Spring quarter

  • 誘導・制御基礎論ⅡB

    2020.12 - 2021.2   Winter quarter

  • 機器学特論

    2020.10 - 2021.3   Second semester

  • 誘導・制御基礎論ⅡA

    2020.10 - 2020.12   Fall quarter

  • 航空宇宙工学演習I

    2020.4 - 2021.3   Full year

  • 航空宇宙工学演習Ⅱ

    2020.4 - 2021.3   Full year

  • 誘導制御講究

    2020.4 - 2021.3   Full year

  • 基幹物理学IA演習

    2020.4 - 2020.9   First semester

  • 基幹物理学IA

    2020.4 - 2020.9   First semester

  • 誘導・制御基礎論I

    2020.4 - 2020.6   Spring quarter

  • 誘導・制御基礎論ⅡB

    2019.12 - 2020.2   Winter quarter

  • 誘導制御特論I

    2019.10 - 2020.3   Second semester

  • 誘導・制御基礎論ⅡA

    2019.10 - 2019.12   Fall quarter

  • 誘導制御講究

    2019.4 - 2020.3   Full year

  • 航空宇宙工学演習I

    2019.4 - 2020.3   Full year

  • 航空宇宙工学演習Ⅱ

    2019.4 - 2020.3   Full year

  • 基幹物理学IA

    2019.4 - 2019.9   First semester

  • 基幹物理学IA演習

    2019.4 - 2019.9   First semester

  • 誘導・制御基礎論I

    2019.4 - 2019.6   Spring quarter

  • 機器学特論

    2018.10 - 2019.3   Second semester

  • 誘導・制御基礎論Ⅱ

    2018.10 - 2019.3   Second semester

  • 航空宇宙工学演習I

    2018.4 - 2019.3   Full year

  • 航空宇宙工学演習Ⅱ

    2018.4 - 2019.3   Full year

  • 航空宇宙工学実験

    2018.4 - 2019.3   Full year

  • 誘導制御講究

    2018.4 - 2019.3   Full year

  • 誘導・制御基礎論I

    2018.4 - 2018.9   First semester

  • 誘導制御特論I

    2017.10 - 2018.3   Second semester

  • 誘導・制御基礎論Ⅱ

    2017.10 - 2018.3   Second semester

  • 航空宇宙工学演習I

    2017.4 - 2018.3   Full year

  • 誘導制御演習Ⅱ

    2017.4 - 2018.3   Full year

  • 航空宇宙工学実験

    2017.4 - 2018.3   Full year

  • 誘導制御講究

    2017.4 - 2018.3   Full year

  • 基幹物理学IA

    2017.4 - 2017.9   First semester

  • 基幹物理学IA演習

    2017.4 - 2017.9   First semester

  • 誘導・制御基礎論I

    2017.4 - 2017.9   First semester

  • 機器学特論

    2016.10 - 2017.3   Second semester

  • 誘導・制御基礎論Ⅱ

    2016.10 - 2017.3   Second semester

  • 誘導制御講究

    2016.4 - 2017.3   Full year

  • 誘導制御演習I

    2016.4 - 2017.3   Full year

  • 誘導制御演習Ⅱ

    2016.4 - 2017.3   Full year

  • 誘導制御工学実験

    2016.4 - 2017.3   Full year

  • 基幹物理学IA

    2016.4 - 2016.9   First semester

  • 基幹物理学IA演習

    2016.4 - 2016.9   First semester

  • 誘導・制御基礎論I

    2016.4 - 2016.9   First semester

  • 飛行制御特論I

    2015.10 - 2016.3   Second semester

  • 誘導・制御基礎論Ⅱ

    2015.10 - 2016.3   Second semester

  • 誘導制御演習I

    2015.4 - 2016.3   Full year

  • 誘導制御演習Ⅱ

    2015.4 - 2016.3   Full year

  • 誘導制御工学実験

    2015.4 - 2016.3   Full year

  • 誘導制御講究

    2015.4 - 2016.3   Full year

  • 航空宇宙工学実験

    2015.4 - 2015.9   First semester

  • 誘導・制御基礎論I

    2015.4 - 2015.9   First semester

  • Instrumentation

    2014.10 - 2015.3   Second semester

  • 誘導・制御基礎論Ⅱ

    2014.10 - 2015.3   Second semester

  • 機器学特論

    2014.10 - 2015.3   Second semester

  • 誘導制御演習I

    2014.4 - 2015.3   Full year

  • 誘導制御演習Ⅱ

    2014.4 - 2015.3   Full year

  • 誘導制御工学実験

    2014.4 - 2015.3   Full year

  • 誘導制御講究

    2014.4 - 2015.3   Full year

  • Aerospace Engineering III

    2014.4 - 2014.9   First semester

  • 基幹物理学IA

    2014.4 - 2014.9   First semester

  • 基幹物理学IA演習

    2014.4 - 2014.9   First semester

  • 誘導・制御基礎論I

    2014.4 - 2014.9   First semester

  • 飛行制御特論I

    2013.10 - 2014.3   Second semester

  • 誘導・制御基礎論Ⅱ

    2013.10 - 2014.3   Second semester

  • 誘導制御演習Ⅱ

    2013.4 - 2014.3   Full year

  • 誘導制御工学実験

    2013.4 - 2014.3   Full year

  • 誘導制御演習I

    2013.4 - 2014.3   Full year

  • Aerospace Engineering III

    2013.4 - 2013.9   First semester

  • 誘導・制御基礎論I

    2013.4 - 2013.9   First semester

  • コアセミナー

    2013.4 - 2013.9   First semester

  • 飛行制御特論I

    2012.10 - 2013.3   Second semester

  • 誘導・制御基礎論Ⅱ

    2012.10 - 2013.3   Second semester

  • 誘導制御工学実験

    2012.4 - 2013.3   Full year

  • 誘導制御演習I

    2012.4 - 2013.3   Full year

  • 誘導制御演習Ⅱ

    2012.4 - 2013.3   Full year

  • 誘導・制御基礎論I

    2012.4 - 2012.9   First semester

  • コアセミナー

    2012.4 - 2012.9   First semester

  • 誘導・制御基礎論Ⅱ

    2011.10 - 2012.3   Second semester

  • 誘導制御工学実験

    2011.4 - 2012.3   Full year

  • 誘導制御演習I

    2011.4 - 2012.3   Full year

  • 誘導制御演習Ⅱ

    2011.4 - 2012.3   Full year

  • 飛行制御特論I

    2011.4 - 2011.9   First semester

  • コアセミナー

    2011.4 - 2011.9   First semester

  • 誘導・制御基礎論I

    2011.4 - 2011.9   First semester

  • 誘導・制御基礎論Ⅱ

    2010.10 - 2011.3   Second semester

  • 誘導制御工学実験

    2010.4 - 2011.3   Full year

  • 誘導制御演習I

    2010.4 - 2011.3   Full year

  • 誘導制御演習Ⅱ

    2010.4 - 2011.3   Full year

  • 飛行制御特論I

    2010.4 - 2010.9   First semester

  • コアセミナー

    2010.4 - 2010.9   First semester

  • 誘導・制御基礎論I

    2010.4 - 2010.9   First semester

  • 機器学特論

    2009.10 - 2010.3   Second semester

  • 誘導制御演習Ⅱ

    2009.4 - 2010.3   Full year

  • 誘導制御工学実験

    2009.4 - 2010.3   Full year

  • 誘導制御演習I

    2009.4 - 2010.3   Full year

  • 誘導・制御基礎論Ⅱ

    2009.4 - 2009.9   First semester

  • コアセミナー

    2009.4 - 2009.9   First semester

  • 誘導・制御基礎論I

    2008.10 - 2009.3   Second semester

  • 誘導制御工学実験

    2008.4 - 2009.3   Full year

  • 誘導制御演習Ⅱ

    2008.4 - 2009.3   Full year

  • 誘導制御演習I

    2008.4 - 2009.3   Full year

  • 誘導・制御基礎論Ⅱ

    2008.4 - 2008.9   First semester

  • コアセミナー

    2008.4 - 2008.9   First semester

  • 誘導・制御基礎論Ⅰ

    2007.10 - 2008.3   Second semester

  • 機器学特論

    2007.10 - 2008.3   Second semester

  • 誘導制御演習I

    2007.4 - 2008.3   Full year

  • 誘導制御工学実験

    2007.4 - 2008.3   Full year

  • 誘導制御演習II

    2007.4 - 2008.3   Full year

  • 誘導・制御基礎論Ⅱ

    2007.4 - 2007.9   First semester

  • コアセミナー

    2007.4 - 2007.9   First semester

  • 誘導・制御基礎論Ⅰ

    2006.10 - 2007.3   Second semester

  • 誘導制御演習I

    2006.4 - 2007.3   Full year

  • 誘導制御工学実験

    2006.4 - 2007.3   Full year

  • 誘導制御演習II

    2006.4 - 2007.3   Full year

  • 誘導・制御基礎論Ⅱ

    2006.4 - 2006.9   First semester

  • 機器学特論

    2005.10 - 2006.3   Second semester

▼display all

FD Participation

  • 2023.7   Role:Participation   Title:若手教員による研究紹介⑨ 「Smart waste management system」 「体内の組み込みセンサーに向けた技術、メタマテリアル支援無線給電及び通信システム」

    Organizer:[Undergraduate school/graduate school/graduate faculty]

  • 2023.4   Role:Participation   Title:若手教員による研究紹介⑧「文字列数理の世界」「超伝導回転機の研究と経産省での業務について」

    Organizer:[Undergraduate school/graduate school/graduate faculty]

  • 2022.9   Role:Participation   Title:Understanding the Faculty Evaluation Systems at Kyushu University

    Organizer:University-wide

  • 2022.5   Role:Participation   Title:若手教員による研究紹介④「量子コンピュータ・システム・アーキテクチャの研究~道具になることを目指して~」

    Organizer:[Undergraduate school/graduate school/graduate faculty]

  • 2021.9   Role:Participation   Title:JST 次世代研究者挑戦的研究プログラム

    Organizer:University-wide

  • 2020.12   Role:Participation   Title:Moodle&MS Teams連携によるオンライン講義実施報告

    Organizer:[Undergraduate school/graduate school/graduate faculty]

  • 2020.11   Role:Participation   Title:海外留学危機管理セミナー 「あなたは責任を持って学生を海外留学に送り出せますか?-新型コロナ感染症と留学について-」

    Organizer:University-wide

  • 2020.6   Role:Participation   Title:どんな3ポリシーが、どのように役立つのかー 九州大学カリキュラム・マップの威力ー

    Organizer:[Undergraduate school/graduate school/graduate faculty]

  • 2018.11   Role:Participation   Title:ハラスメント防止のための研修会

    Organizer:[Undergraduate school/graduate school/graduate faculty]

  • 2018.1   Role:Participation   Title:M2B(みつば)学習支援システム講習会,研究分析ツール「SciVal」及び研究者プロファイリングツール「Pure」

    Organizer:[Undergraduate school/graduate school/graduate faculty]

  • 2017.8   Role:Participation   Title:「学術研究・産学官連携本部における研究支援等について」「教育・研究に関する東北大学工学研究科・工学部の取組」

    Organizer:[Undergraduate school/graduate school/graduate faculty]

  • 2016.6   Role:Participation   Title:ハラスメント防止のための研修会

    Organizer:[Undergraduate school/graduate school/graduate faculty]

  • 2014.8   Role:Participation   Title:新GPA制度実施に向けたFDについて

    Organizer:University-wide

  • 2013.11   Role:Participation   Title:著作権と機関リポジトリ ~ 博士論文のインターネット公表

    Organizer:[Undergraduate school/graduate school/graduate faculty]

  • 2013.5   Role:Participation   Title:基幹教育と基幹教育カリキュラム

    Organizer:[Undergraduate school/graduate school/graduate faculty]

  • 2013.1   Role:Participation   Title:ハラスメント防止に関する研修会

    Organizer:[Undergraduate school/graduate school/graduate faculty]

  • 2009.12   Role:Participation   Title:教育の質向上支援プログラム(EEP)

    Organizer:[Undergraduate school/graduate school/graduate faculty]

  • 2009.10   Role:Participation   Title:九州大学工学研究院FD(部門内FD)「科研費申請に係わる研究計画調書の記述法の改善」

    Organizer:Undergraduate school department

  • 2009.10   Role:Participation   Title:九州大学工学研究院FD「農学研究院における英語教育に関する検討について」

    Organizer:[Undergraduate school/graduate school/graduate faculty]

  • 2002.12   Role:Participation   Title:九州大学全学FD

    Organizer:University-wide

▼display all

Visiting, concurrent, or part-time lecturers at other universities, institutions, etc.

  • 2009  宇宙航空研究開発機構宇宙科学研究本部  Classification:Affiliate faculty  Domestic/International Classification:Japan 

  • 2008  宇宙航空研究開発機構宇宙科学研究本部  Classification:Affiliate faculty  Domestic/International Classification:Japan 

  • 2003  九州工業大学・工学部  Classification:Part-time lecturer  Domestic/International Classification:Japan 

    Semester, Day Time or Duration:後期,水曜日

  • 2002  九州工業大学・工学部  Classification:Part-time lecturer  Domestic/International Classification:Japan 

    Semester, Day Time or Duration:後期,月曜日

Other educational activity and Special note

  • 2017  Class Teacher  学部

  • 2016  Class Teacher  学部

  • 2015  Class Teacher  学部

  • 2015  Coaching of Students' Association  バドミントン部

     詳細を見る

    顧問

  • 2014  Coaching of Students' Association  バドミントン部

     詳細を見る

    顧問

  • 2013  Coaching of Students' Association  バドミントン部

     詳細を見る

    顧問

  • 2012  Class Teacher  学部

  • 2012  Coaching of Students' Association  バドミントン部

     詳細を見る

    顧問

  • 2011  Class Teacher  学部

  • 2011  Coaching of Students' Association  バドミントン部

     詳細を見る

    顧問

  • 2010  Class Teacher  学部

  • 2010  Coaching of Students' Association  バドミントン部

     詳細を見る

    顧問

  • 2009  Class Teacher  学部

  • 2009  Coaching of Students' Association  バドミントン部

     詳細を見る

    顧問

  • 2008  Coaching of Students' Association  バドミントン部

     詳細を見る

    顧問

  • 2007  Coaching of Students' Association  バドミントン部

     詳細を見る

    監督

  • 2006  Class Teacher  学部

  • 2006  Coaching of Students' Association  バドミントン部

     詳細を見る

    監督

  • 2005  Class Teacher  学部

  • 2005  Coaching of Students' Association  バドミントン部

     詳細を見る

    監督

  • 2004  Coaching of Students' Association  バドミントン部

     詳細を見る

    監督

  • 2003  Coaching of Students' Association  バドミントン部

     詳細を見る

    監督

  • 2002  Coaching of Students' Association  バドミントン部

     詳細を見る

    監督

▼display all

Outline of Social Contribution and International Cooperation activities

  • 公開講座等
     2002年11月 筑紫高校一日総合大学講師
     2004年 1月 スーパーサイエンスハイスクール講師
    2006年10月 伝習館高校
    2010年10月 済々黌高校
    2016年11月 舟入高校
    2017年 3月 東明館高校
    2019年10月  熊本学園大学附属高校
    2022年 3月 徳山高校

Social Activities

  • 宇宙工学から見て,なぜ天体探査ローバーが難しいのか3

    福岡市科学館  福岡市科学館  2023.8

     More details

    Audience:General, Scientific, Company, Civic organization, Governmental agency

    Type:Lecture

  • 宇宙工学から見て,なぜ天体探査ローバーが難しいのか2

    福岡市科学館  福岡市科学館  2022.8

     More details

    Audience:General, Scientific, Company, Civic organization, Governmental agency

    Type:Lecture

  • 航空宇宙分野での制御について

    徳山高校(山口)  2022.3

     More details

    Audience:Infants, Schoolchildren, Junior students, High school students

    Type:Seminar, workshop

  • 宇宙工学から見て,なぜ天体探査ローバーが難しいのか

    福岡市科学館  福岡市科学館  2021.8

     More details

    Audience:General, Scientific, Company, Civic organization, Governmental agency

    Type:Lecture

  • 九州大学における研究の一例 ~航空/宇宙分野での制御~

    熊本学園大学付属高等学校(熊本)  2019.10

     More details

    Audience:Infants, Schoolchildren, Junior students, High school students

    Type:Seminar, workshop

  • 九州大学における研究の一例 ~航空/宇宙分野での制御~

    熊本学園大学付属高等学校(熊本)  2019.10

     More details

    Type:Seminar, workshop

    researchmap

  • ドローン(無人航空機)について

    東明館高校(佐賀)  2017.3

     More details

    Audience:Infants, Schoolchildren, Junior students, High school students

    Type:Seminar, workshop

  • ドローン(無人航空機)について

    東明館高校(佐賀)  2017.3

     More details

    Type:Seminar, workshop

    researchmap

  • 宇宙探査システムとその制御について ~大学における研究例~

    舟入高校(広島)  2016.11

     More details

    Audience:Infants, Schoolchildren, Junior students, High school students

    Type:Seminar, workshop

  • 宇宙探査システムとその制御について ~大学における研究例~

    舟入高校(広島)  2016.11

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    Type:Seminar, workshop

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  • ドローンについて

    福岡ロータリークラブ  2015.9

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    Audience:General, Scientific, Company, Civic organization, Governmental agency

    Type:Seminar, workshop

  • ドローンについて

    福岡ロータリークラブ  2015.9

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    Type:Seminar, workshop

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  • ドローンについて

    九州学士会  2015.6

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    Audience:General, Scientific, Company, Civic organization, Governmental agency

    Type:Lecture

  • ドローンについて

    九州学士会  2015.6

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    Type:Visiting lecture

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  • 九州学生バドミントン連盟 会長

    2015

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    九州学生バドミントン連盟 会長

  • 福岡県学生バドミントン連盟 会長

    2015

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    福岡県学生バドミントン連盟 会長

  • 九州学生バドミントン連盟 会長

    2015

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    Type:Other

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  • 福岡県学生バドミントン連盟 会長

    2015

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    Type:Other

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  • 九州学生バドミントン連盟 会長

    2014

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    九州学生バドミントン連盟 会長

  • 福岡県学生バドミントン連盟 会長

    2014

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    福岡県学生バドミントン連盟 会長

  • 九州学生バドミントン連盟 会長

    2014

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    Type:Other

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  • 福岡県学生バドミントン連盟 会長

    2014

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    Type:Other

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  • 九州学生バドミントン連盟 会長

    2013

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    九州学生バドミントン連盟 会長

  • 福岡県学生バドミントン連盟 会長

    2013

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    福岡県学生バドミントン連盟 会長

  • 九州学生バドミントン連盟 会長

    2013

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    Type:Other

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  • 福岡県学生バドミントン連盟 会長

    2013

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    Type:Other

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  • 九州学生バドミントン連盟 会長

    2012

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    九州学生バドミントン連盟 会長

  • 福岡県学生バドミントン連盟 会長

    2012

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    福岡県学生バドミントン連盟 会長

  • 九州学生バドミントン連盟 会長

    2012

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    Type:Other

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  • 福岡県学生バドミントン連盟 会長

    2012

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    Type:Other

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  • 九州学生バドミントン連盟 会長

    2011

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    九州学生バドミントン連盟 会長

  • 福岡県学生バドミントン連盟 会長

    2011

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    福岡県学生バドミントン連盟 会長

  • 九州学生バドミントン連盟 会長

    2011

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    Type:Other

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  • 福岡県学生バドミントン連盟 会長

    2011

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    Type:Other

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  • ”済々未来講座”講師

    済々黌高校(熊本市)  2010.10

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    Audience:Infants, Schoolchildren, Junior students, High school students

    Type:Seminar, workshop

  • ”済々未来講座”講師

    済々黌高校(熊本市)  2010.10

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    Type:Seminar, workshop

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  • 九州学生バドミントン連盟 会長

    2010

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    九州学生バドミントン連盟 会長

  • 福岡県学生バドミントン連盟 会長

    2010

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    福岡県学生バドミントン連盟 会長

  • 九州学生バドミントン連盟 会長

    2010

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    Type:Other

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  • 福岡県学生バドミントン連盟 会長

    2010

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    Type:Other

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  • 九州学生バドミントン連盟 会長

    2009

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    九州学生バドミントン連盟 会長

  • 福岡県学生バドミントン連盟 会長

    2009

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    福岡県学生バドミントン連盟 会長

  • 九州学生バドミントン連盟 会長

    2009

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    Type:Other

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  • 福岡県学生バドミントン連盟 会長

    2009

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    Type:Other

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  • 九州学生バドミントン連盟 会長

    2008

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    九州学生バドミントン連盟 会長

  • 福岡県学生バドミントン連盟 会長

    2008

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    福岡県学生バドミントン連盟 会長

  • 九州学生バドミントン連盟 会長

    2008

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    Type:Other

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  • 福岡県学生バドミントン連盟 会長

    2008

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    Type:Other

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  • ”ミラクルステージ”講師

    伝習館高校(柳川市)  2006.10

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    Audience:Infants, Schoolchildren, Junior students, High school students

    Type:Seminar, workshop

  • ”ミラクルステージ”講師

    伝習館高校(柳川市)  2006.10

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    Type:Seminar, workshop

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  • スーパーサイエンスハイスクール

    修猷館高校(福岡市)  2004.1

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    Audience:Infants, Schoolchildren, Junior students, High school students

    Type:Seminar, workshop

  • スーパーサイエンスハイスクール

    修猷館高校(福岡市)  2004.1

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    Type:Seminar, workshop

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  • 一日総合大学

    筑紫高校(筑紫野市)  2002.11

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    Audience:Infants, Schoolchildren, Junior students, High school students

    Type:Seminar, workshop

  • 一日総合大学

    筑紫高校(筑紫野市)  2002.11

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    Type:Seminar, workshop

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Activities contributing to policy formation, academic promotion, etc.

  • 2023.4 - 2025.3   宇宙科学運営協議会 運営協議員

    宇宙科学に関する学術研究およびこれに関する業務について,宇宙航空研究開発機構 宇宙科学研究所長の諮問に答える

  • 2022.5 - 2024.4   九州航空宇宙開発推進協議会 幹事

    九州における航空宇宙産業の振興を図る

  • 2021.7 - 2024.7   福岡県航空機産業振興会 副会長

    航空機産業の福岡県内への誘致促進及び振興等を図る

  • 2021.4 - 2023.3   宇宙科学運営協議会 運営協議員

    宇宙科学に関する学術研究およびこれに関する業務について,宇宙航空研究開発機構 宇宙科学研究所長の諮問に答える

  • 2019.5 - 2021.4   宇宙工学委員会

    宇宙科学に関する研究計画やプロジェクトの企画等について審議する

  • 2017.5 - 2019.4   宇宙工学委員会

    宇宙科学に関する研究計画やプロジェクトの企画等について審議する

  • 2015.5 - 2017.4   宇宙工学委員会

    宇宙科学に関する研究計画やプロジェクトの企画等について審議する

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Acceptance of Foreign Researchers, etc.

  • 北京航空航天大学

    Acceptance period: 2005.10 - 2006.3   (Period):1 month or more

    Nationality:China

    Business entity:On-campus funds

Travel Abroad

  • 2005.8

    Staying countory name 1:United States   Staying institution name 1:不明