博士(工学), 東京大学

Control engineering in general

Space crafts

制御工学一般

宇宙飛行体

Informatics, Mechanics and mechatronics

Manufacturing technology (mechanical, electrical/electronic, chemical engineering), Control and systems engineering

Aerospace, marine, and maritime Engineering, Aerospace engineering

Mar. 1973
The University of Tokyo, Faculty of Engineering, 計数工学科

Mar. 2007 - Feb. 2009
評議委員, 日本機械学会, Society

2008 - 2009
評議委員, 計測自動制御学会, Society

Mar. 2007
Fellow, Japan Society of Mechanical Engineers, Society

Mar. 2007
フェロー, 日本機械学会, Society

Feb. 2006 - Jan. 2007
制御部門長, 計測自動制御学会, Society

Mar. 2005 - Feb. 2006
宇宙工学部門部門長, 日本機械学会, Society

Feb. 2005 - Jan. 2006
アドバンスト誘導制御研究会主査, 計測自動制御学会, Society

2004 - 2004
会誌編集委員長, 計測自動制御学会, Society

2003 - 2004
常務理事, 計測自動制御学会, Society

2002 - 2003
宇宙航行部門委員長, 日本航空宇宙学会, Society

2002 - 2003
制御理論部会委員, 計測自動制御学会, Society

2002
論文集校閲委員, 日本機械学会, Society

1996 - 1997
論文集校閲委員, 日本機械学会, Society

Sep. 2013
計測自動制御学会
計測自動制御学会フェロー

Sep. 2011
計測自動制御学会
計測自動制御学会技術賞

Mar. 2007
日本機械学会宇宙工学部門功績賞

Jul. 1997
計測自動制御学会論文賞

Aug. 1993
計測自動制御学会論文賞

線形時変力学系のLMIを用いた静的出力フィードバック制御のL2ゲイン性能最適設計
高久雄一; 木田隆
計測自動制御学会論文集, 計測自動制御学会, 50, 10, 739-745, 01 Oct. 2014, Peer-reviwed
Scientific journal, Japanese

Static Output Feedback Controller Design for Linear Time-Varying Second-order System with Space Application
Yuichi Takaku; Takashi Kida
Proceedings of SICE Annual Conference 2014, SICE, 2041-2046, 09 Sep. 2014, Peer-reviwed
International conference proceedings, English

Robust Model Predictive Control for Flexible Spacecraft Using Reaction Control Systems
Takeya Asakawa; Takashi Kida
Proceedings of SICE Annual Conference 2014, SICE, 2057-2060, 09 Sep. 2014, Peer-reviwed
International conference proceedings, English

Optimal Guidance Law for Lunar Landing using Nonlinear Model Predictive Control
Atsushi Sakamoto; Takashi Kida
Proceedings of SICE Annual Conference 2014, SICE, 2061-2066, 09 Sep. 2014, Peer-reviwed
International conference proceedings, English

Robust Two-Degrees-of-Freedom Attitude Controller Design and Flight Test Result for Engineering Test Satellite-VIII Spacecraft
Tomoyuki Nagashio; Takashi Kida; Yoshiro Hamada; Takashi Ohtani
IEEE TRANSACTIONS ON CONTROL SYSTEMS TECHNOLOGY, IEEE-INST ELECTRICAL ELECTRONICS ENGINEERS INC, 22, 1, 157-168, Jan. 2014, Peer-reviwed, This paper reports flight test results of robust attitude control for the Engineering Test Satellite VIII (ETS-VIII) spacecraft. The main mission of ETS-VIII is to support next-generation mobile digital communications, and for this purpose it is equipped with two large deployable antenna reflectors and a pair of large solar panels that rotate around the pitch axis. We have proposed and demonstrated several control methods for this spacecraft based on advanced control theories for linear parameter varying multi-input multi-output systems, and in this paper we focus on a two-degrees-of-freedom controller. We describe the controller design methods and present the results of on-orbit flight tests. The controller's superiority is demonstrated by comparing its performance with other controllers.
Scientific journal, English

Static Output Feedback Controller Design Based on LMI for Linear Time-Varying Collocated Mechanical System
Yuichi Takaku; Tomoyuki Nagashio; Takashi Kida
11TH IEEE INTERNATIONAL CONFERENCE ON CONTROL AND AUTOMATION (ICCA), IEEE, 467-472, 2014, Peer-reviwed, This paper studies a static output feedback control for linear time-varying collocated mechanical systems. The internal stability and L-2 gain control performance conditions are first derived by utilizing specific system structures. Then we propose a controller design algorithm based on linear matrix inequality to obtain gain-scheduled optimal feedback gains. Simple numerical studies are shown and discussed.
International conference proceedings, English

Model Predictive Control for LPV System using On-off Actuator with Application to Spacecraft Attitude Maneuver
Takeya Asakawa; Takashi Kida
11TH IEEE INTERNATIONAL CONFERENCE ON CONTROL AND AUTOMATION (ICCA), IEEE, 1215-1220, 2014, Peer-reviwed, This paper proposes a model predictive control of linear parameter varying systems driven by non-linear on-off control inputs. We formulate the problem as an integer quadratic programming problem. In order to ensure the closed-loop stability, we newly derive a condition for terminal cost matrices which are obtained by solving linear matrix inequalities. A numerical study is performed to verify the proposed method using a large spacecraft having rotating solar panels.
International conference proceedings, English

コロケーション条件を満たすジャイロシステムの出力フィードバックによるロバスト安定化とLMIによる最適設計
黒滝勇貴; 長塩知之; 木田隆
計測自動制御学会論文集, 48, 10, 952-960, Oct. 2013, Peer-reviwed
Scientific journal, Japanese

Gain Scheduled Tracking Control for Spacecraft with Model Uncertainty
Atsushi Sakamoto; Takashi Kida
Proc. of SICE Annual Conference, 2182-2185, Sep. 2013, Peer-reviwed
International conference proceedings, English

Spacecraft Formation Flying with Thrusters using MPC and Collision Avoidance
Takeya Asakawa; Takashi Kida
Proc. of SICE Annual Conference, 2204-2206, Sep. 2013, Peer-reviwed
International conference proceedings, English

Flight Results of In-Orbit Advanced Attitude Control Experiment using Large Flexible Satellite ETS-VIII and JAXA’s Future Mission
Takashi Ohtani; Yoshiro Hamada; Tomoyuki Nagashio; Takashi Kida
AIAA Guidance, Navigation and Control Conference, AIAA-2013-4715, 1-10, Aug. 2013, Peer-reviwed
International conference proceedings, English

大型柔軟衛星のロバスト制御（入力拘束を考慮したモデル予測制御の適用）
山下哲生; 濱田吉郎; 山口功; 長塩知之; 木田隆
日本機械学会論文集Ｃ編, 79, 802, 1935-1948, Apr. 2013, Peer-reviwed
Scientific journal, Japanese

Application of MPC to Spacecraft Attitude Maneuver using RCS and/or RW
Takeya Asakawa; Takashi Kida
Journal of Space Engineering, The Japan Society of Mechanical Engineers, 6, 1, 1-14, Apr. 2013, Peer-reviwed, This paper applies model predictive control (MPC) to multi-input spacecraft attitude maneuver problems using reaction control systems (RCS) and reaction wheels (RW). For this purpose, we consider linear quadratic cost functions under the input constraints of nonlinear on-off control inputs for RCS and linear continuous inputs with saturation for RW. These are optimized as mixed integer quadratic programming (MIQP) problems. We further analyze the closed-loop stability in the input-to-state stability framework and derive a stability condition described by a linear matrix inequality (LMI). Some numerical studies are performed and the effectiveness of the proposed model predictive control is shown.
Scientific journal, English

An Optimal Design of H-infinity Static Output Feedback Controller using LMI for Collocated Gyroscopic System
Yuki Kurotaki; Tomoyuki Nagashio; Takashi Kida
51th IEEE CDC, 7776-7780, Dec. 2012, Peer-reviwed
International conference proceedings, English

An Optimal H-Infinity Design Using GKYP Lemma for DVDFB Controller and Its Application to Flexible Spacecraft
Yuichi Takaku; Takashi Kida
Trans. JSASS Aerospace Tech, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 10, 28, 53-60, Jan. 2012, Peer-reviwed, This paper proposes a design method of optimal DVDFB (direct velocity and displacement feedback) controller for attitude control of flexible spacecraft whose flexible solar paddles rotate at the orbital rate. The DVDFB controller with collocated sensors and actuators is known to be promising from the robust stability viewpoint even for such a linear parameter varying system. However, the optimal design method is not still well-developed. For this problem, we propose to design an optimal DVDFB controller gain based on LMI (linear matrix inequality) in the H_∞ control framework using GKYP (generalized Kalman-Yakubovich-Popov) lemma. Some numerical simulations are performed to demonstrate the ability.
Scientific journal, English

Nonlinear Tracking Control of Rigid Spacecraft under Disturbance using PD and PID Type H infinity State Feedback
Yuichi Ikeda; Takashi Kida; Tomoyuki Nagashio
50th IEEE CDC-ECC 2011, 6184-6191, Dec. 2011, Peer-reviwed
International conference proceedings, English

Asymmetric Static Output Feedback Control and Optimum Design for Gyroscopic System
Yuki Kurotaki; Takashi Kida; Tomoyuki Nagashio
30th International Conference on Modeling and Simulation Technology, 374-377, Oct. 2011, Peer-reviwed
International conference proceedings, English

Anti-windup Design for Flexible Spacecraft Attitude Control System
Takeya Asakawa; Isao Yamaguchi; Yoshiro Hamada; Tokio Kasai; Tomoyuki Nagashio; Takashi Kida
SICE Annual Conference 2011, 1802-1806, Sep. 2011, Peer-reviwed
International conference proceedings, English

Synthesis of a linearly interpolated gain scheduling controller for large flexible spacecraft ETS-VIII
Yoshiro Hamada; Takashi Ohtani; Takashi Kida; Tomoyuki Nagashio
CONTROL ENGINEERING PRACTICE, PERGAMON-ELSEVIER SCIENCE LTD, 19, 6, 611-625, Jun. 2011, Peer-reviwed, This paper illustrates a design procedure for a linearly interpolated gain scheduling controller for Engineering Test Satellite VIII (ETS-VIII) using its linear parameter-varying (LPV) model. The LPV model here consists of piecewise-linear functions of the paddle rotation angle and a norm-bounded perturbation. The main purpose of this research is to derive a simple structured scheduling law that can be easily implemented in a satellite onboard computer. The derived gain has only two grid points and is scheduled simply by linear interpolation, which is desirable from the standpoint of implementability. Moreover, since the synthesis condition is based on parameter-dependent Lyapunov functions, it gives less conservative results than existing methods. Simulation results are presented to show the effectiveness of the proposed synthesis. (C) 2011 Elsevier Ltd. All rights reserved.
Scientific journal, English

Design and flight test results of robust attitude controller for the ETS-VIII spacecraft
Tomoyuki Nagashio; Takashi Kida; Takashi Ohtani; Yoshiro Hamada
IFAC Proceedings Volumes (IFAC-PapersOnline), 18, 1, 5154-5159, 2011, Peer-reviwed, This paper reports the flight test results of robust attitude controller for Engineering Test Satellite VIII (ETS-VIII) spacecraft. The main mission of ETS-VIII is to support nextgeneration mobile digital communications, and for this purpose it is equipped with two large deployable antenna reflectors and a pair of large solar paddles that rotate around the pitch axis. For the spacecraft, the authors have proposed and demonstrated several control methods based on the advanced control theories for the linear parameter varying multi-input multioutput system. The aim is to develop a baseline for future controller design technology for this class of satellite instead of existing classical PID control laws. This paper describes the on-orbit experiment results and compares these controllers performance. © 2011 IFAC.
International conference proceedings, English

Design and implementation of robust symmetric attitude controller for ETS-VIII spacecraft
Tomoyuki Nagashio; Takashi Kida; Takashi Ohtani; Yoshiro Hamada
CONTROL ENGINEERING PRACTICE, PERGAMON-ELSEVIER SCIENCE LTD, 18, 12, 1440-1451, Dec. 2010, Peer-reviwed, To meet increasing mission requirements, communication satellites are being equipped with large flexible antenna reflectors and solar paddles. A typical such satellite, the Engineering Test Satellite VIII (EIS-VIII) spacecraft, was launched into geostationary orbit by the Japan Aerospace Exploration Agency (JAXA) in December 2006. The main mission of ETS-VIII is to support next-generation mobile digital communications, and for this purpose it is equipped with two large deployable antenna reflectors and a pair of large solar paddles that rotate around the pitch axis. The authors are planning to perform on-orbit attitude control experiments using ETS-VIII at the end of its mission life, aiming to develop a baseline for future controller design for this class of satellite using advanced control theories. This paper proposes two degrees-of-freedom control based on robust direct velocity and displacement feedback as a candidate controller technology. The spacecraft modeling and controller synthesis methods are discussed, and a controller implementation for an on-orbit control experiment is presented with simulation results. (C) 2009 Elsevier Ltd. All rights reserved.
Scientific journal, English

Orbital Experiment of Linearly Interpolated Gain Scheduling Attitude Controller Using ETS-VIII Spacecraft
Yoshiro Hamada; Takashi Ohtani; Takashi Kida; Tomoyuki Nagashio; Isao Yamaguchi; Tokio Kasai; Takahiro Igawa; Shinji Mitani; Kei Sunagawa; Masafumi Okeda
18th IFAC Symposium on Automatic Control in Aerospace, 7A-1-2, Sep. 2010, Peer-reviwed
International conference proceedings, English

On-orbit Experiment Results of Robust Symmetric Attitude Controller for ETS-VIII Spacecraft
Tomoyuki Nagashio; Takashi Kida; Takashi Ohtani; Yoshiro Hamada; Isao Yamaguchi; Tokio Kasai; Takahiro Igawa; Shinji Mitani; Kei Sunagawa; Masafumi Ikeda
18th IFAC Symposium on Automatic Control in Aerospace, 7A-1-3, Sep. 2010, Peer-reviwed
International conference proceedings, English

動的出力フィードバックによる宇宙機のトラッキング制御-- 受動性に基づいたアプローチ --
池田裕一; 木田隆; 長塩知之
日本機械学会論文集Ｃ編, 75, 759, 2933-2941, Nov. 2009, Peer-reviwed
Scientific journal, Japanese

An Optimal Design of Symmetric H infinity Static Output Feedback Controller using LMI for Collocated Second-Order Linear System
Tomoyuki Nagashio; Takashi Kida
Proc. of 48th IEEE CDC/28th CCC, 6177-6182, Nov. 2009, Peer-reviwed
International conference proceedings, English

Robust Attitude Control using mu-synthesis for the Large Flexible Satellite ETS-VIII
Takashi Ohtani; Yoshiro Hamada; Tomoyuki Nagashio; Takashi Kida; Shinji Mitani; Isao Yamaguchi; Tokio Kasai; Hirotaka Igawa
Journal of Space Technology and Science, 25, 1, 27-40, Oct. 2009, Peer-reviwed
Scientific journal, English

A Preliminary Study on Precise Attitude Switching Maneuver of Flexible Spacecraft
Takaaki Tanaka; Takashi Kida; Tomoyuki Nagashio; Takashi Ohtani; Isao Yamaguchi; Tokio Kasai; Yoshiro Hamada; Shin-ichiro Sakai; Nobutaka Bando
Journal of Space Engineering, The Japan Society of Mechanical Engineers, 2, 1, 12-24, May 2009, Peer-reviwed, The switching maneuver is one of the missions of spacecraft that is to continue changing the attitude angle of spacecraft to observe multi targets. In performing switching maneuver at high speed, there are such problems that high power actuator is needed and flexible structure of spacecraft is excited. In this report, we study the problems of high speed and precise attitude switching maneuver by using control moment gyros (CMGs). For designing feedback controller, we propose to use gain scheduled DVDFB control that is optimized via LMI. The control performance is evaluated by simulations and some important issues for achieving control specifications are discussed.
Scientific journal, English

Robust Control of Flexible Mechanical Systems by Utilizing Symmetry and Its Application to Large Space Structures
Tomoyuki Nagashio; Takashi Kida
IEEE TRANSACTIONS ON CONTROL SYSTEMS TECHNOLOGY, IEEE-INST ELECTRICAL ELECTRONICS ENGINEERS INC, 17, 3, 671-680, May 2009, Peer-reviwed, The control of flexible mechanical systems has been extensively studied in a variety of fields. For mechanical systems with collocated sensors and actuators, the use of symmetric controllers is known to be effective. The symmetric controller guarantees the robust stability of the closed-loop system irrespective of the system parameters by virtue of the structure of the dynamical equation having positive definite or semidefinite symmetric coefficient matrices. Although this controller is superior to existing parametric approaches, systematic procedures for obtaining specific control performance other than the stability of the closed-loop system have not yet been fully established. This paper proposes an optimal design method for symmetric controllers in the sense of the H(infinity) norm by solving the linear matrix inequalities reduced from the bounded real lemma under the symmetry constraint. This method is then extended to static output feedback control and gain-scheduled control. Finally, the design method is applied to a flexible spacecraft attitude control problem, and its validity is confirmed.
Scientific journal, English

Stabilizing Nonlinear Adaptive PID State Feedback Control for Spacecraft Capturing
Yuichi Ikeda; Takashi Kida; Tomoyuki Nagashio
Proc. of the 17th IFAC World Congress, 15040-15045, Jul. 2008, Peer-reviwed
International conference proceedings, English

Design and Implementation of Robust Symmetric Attitude Controller for ETS-VIII Spacecraft
Tomoyuki Nagashio; Takashi Kida; Takashi Ohtani; Yoshiro Hamada
Proc. Of the 17th IFAC World Congress, 3434-3439, Jul. 2008, Peer-reviwed
International conference proceedings, English

パラメータに対して区分線形なスケジュールドゲインの設計法
濱田吉郎; 大谷崇; 木田隆; 長塩知之
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 44, 6, 492-498, Jun. 2008, Peer-reviwed, This paper proposes a new synthesis of a gain scheduling controller. Using the dilation lemma, the synthesis condition is derived in terms of linear matrix inequalities with a line-search parameter, which can be solved numerically. Although previous design methods guarantee control performance for every parameter value, resultant gains tend to be too complicated to be implemented in a real system. In contrast, our method yields simple scheduling laws which are preferable for implementation. Derived scheduling laws are piecewise-linear on scheduling parameters and have fewer grid points than scheduling laws of a previous method. Since the synthesis is based on parameter-dependent Lyapunov functions, simple scheduling laws can be derived without deteriorating the performance of the closed loop system. A numerical example demonstrates the effectiveness of the proposed method.
Scientific journal, Japanese

きく８号(ETS-VIII)のロバスト姿勢制御系設計 - DVDFBの特徴を活かした二自由度制御系の適用 -
長塩知之; 木田隆; 濱田吉郎; 大谷崇
計測自動制御学会論文集, 計測自動制御学会, 44, 6, 499-507, Jun. 2008, Peer-reviwed
Scientific journal, Japanese

きく８号(ETS-VIII)のロバスト姿勢制御系設計 - ゲインスケジューリング制御の適用 -
濱田吉郎; 大谷崇; 木田隆; 長塩知之
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 44, 6, 508-517, Jun. 2008, Peer-reviwed, In this paper a new design method for a gain scheduling controller is described which will be employed in an on-orbit control experiment using Engineering Test Satellite VIII. Using this method, a robust control system that is resilient to changes in the paddle rotation angle and higher order vibration modes is designed as this method can treat the satellite system as a linear parameter varying (LPV) system whose dynamics vary according to the paddle rotation angle. The derived gains can be easily scheduled since the scheduling law consists of small number of grid points and requires just linear interpolation calculation. Using this method, stability and performance are guaranteed at each parameter value (paddle angle in this case). Some simulation results are provided to show the effectiveness of our controller.
Scientific journal, Japanese

Robust Attitude Control Using Mu-synthesis of Large Flexible Satellite ETS-VIII
Takashi Ohtani; Yoshiro Hamada; Tomoyuki Nagashio; Takashi Kida; Shinji Mitani; Isao Yamaguchi; Tokio Kasai; Hirotaka Igawa
Proc. of 7th International ESA Conference on Guidance, Navigation & Control Systems, 1-6, Jun. 2008, Peer-reviwed
International conference proceedings, English

PID型状態フィードバックによる宇宙機の非線形トラッキング制御
池田裕一; 木田隆; 長塩知之
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 44, 2, 236-244, Feb. 2008, Peer-reviwed, In this paper, we consider the position and attitude (six degrees of freedom) tracking control of rigid body spacecraft by PID-type state feedback control in order to remove the position and attitude error that are caused by step disturbance. Firstly, the relative motion equation of the six degrees of freedom rigid body spacecraft is derived. Secondly, we design PID type state feedback control law so that the closed loop system of the relative motion equation is asymptotically stabilized. Then, we extend the results to PID type adaptive state feedback controller with physical parameter update law. Finally, the effectiveness of the control methods is verified by simulations.
Scientific journal, Japanese

On-orbit Experiment Plan of Robust Attitude Control of ETS-VIII
Takashi Ohtani; Yoshiro Hamada; Tomoyuki Nagashio; Takashi Kida; Shinji Mitani; Isao Yamaguchi; Tokio Kasai
Proc. of SICE Annual Conference 2007, 2264-2267, Sep. 2007, Peer-reviwed
International conference proceedings, English

Robust Attitude Control of ETS-VIII Spacecraft via Symmetric Controller
Tomoyuki Nagashio; Takashi Kida; Takashi Ohtani; Yoshiro Hamada
Proc. of 17th IFAC Symposium on Automatic Control in Aerpspace, MO-02, Jun. 2007, Peer-reviwed
International conference proceedings, English

Gain Scheduling Controller Design for Engineering Test Satellite ETS-VIII
Yoshiro Hamada; Takashi Ohtani; Takashi Kida; Tomoyuki Nagashio
Proc. of 17th IFAC Symposium on Automatic Control in Aerospace, TH-01-1, Jun. 2007, Peer-reviwed
International conference proceedings, English

Pointing Control of Mobile Antenna on Vehicle
Tomoyuki Nagashio; Takashi Kida
J. of System Design and Dynamics, The Japan Society of Mechanical Engineers, 1, 2, 236-244, May 2007, Peer-reviwed, This paper describes a pointing control of a mobile antenna mounted on a vehicle. For precise pointing, the antenna must be controlled to point to a target under the influence of continuous disturbances acting on the vehicle. For this purpose, we propose an optimal controller design method in a framework of the H_∞ gain-scheduled controller synthesis. By this synthesis, the optimal controller is obtained by using parameter varying notch-filter in order to attenuate the various frequency disturbances. We apply this design method to an automobile model having a rotating antenna.
Scientific journal, English

A new gain scheduling controller synthesis and its application to attitude control systems of a large flexible satellite
Yoshiro Hamada; Takashi Ohtani; Takashi Kida; Tomoyuki Nagashio
Proceedings of the IEEE International Conference on Control Applications, 2914-2920, 2007, Peer-reviwed, This paper proposes a new synthesis of a gain scheduling controller based on approximation of Lyapunov solutions with spline functions. Using the proposed synthesis, scheduled controllers, which do not require large programs when implemented in an actual control system, can be derived by setting the number of "knots" (i.e. grid points) of the controller as small as possible. Scheduled controllers which are piecewise-linear on a parameter can also be obtained by adding some constraints to the derived condition. The synthesis is applied to design an attitude controller of a large flexible satellite and simulation results are provided to show the effectiveness of our synthesis. ©2006 IEEE.
International conference proceedings, English

衛星通信用船舶搭載型トラッキングアンテナの高精度化
山岡天平; 明愛国; 木田隆; 金森哉吏; 佐藤基夫
日本機械学会論文集Ｃ編, The Japan Society of Mechanical Engineers, 73, 725, 170-176, Jan. 2007, Peer-reviwed, Recently, data traffic for satellite communications is increasing rapidly, due to the various new purposes besides the conventional voice phone and facsimile. For the reason, it is necessary to realize high frequency communications, which is assured by high accuracy of tracking control of an antenna. This paper aims at the accuracy improvement of conventional tracking antennas by introducing H-infinity control. In this paper, the basic characteristics of tracking antenna are investigated by experiments and the model of the antenna for controller design is established. Based on the model, a H-infinity controller is designed and implemented to the antenna. Experimental results show that the tracking accuracy can be improved to ±0.25 [deg], which is four times higher than that by the conventional controller.
Scientific journal, Japanese

軌道上における故障衛星捕捉時の安定化非線形制御
伊藤玲; 池田裕一; 長塩知之; 木田隆
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 42, 11, 1208-1215, Nov. 2006, Peer-reviwed, In the future space infrastructure, the missions of refueling and capturing of the inoperative spacecraft by the orbital servicing vehicle or the space robot is considered. To achieve them, the six degrees of freedom tracking control of the chaser spacecraft is required to approach the target spacecraft. Moreover, the stability of the connected system of the chaser and target must be ensured. In this paper we derive the conditions for the feedback gains that satisfy the stability of the spacecraft system before and after the capturing separately. These conditions are described by the matrix inequalities. Then, we solve these inequalities simultaneously to yield the feedback gains. The controller thus obtained is applicable to the stabilizing problem before and after the connection. The effectiveness of control laws is verified by numerical simulations.
Scientific journal, Japanese

Asymptotic stability of second-order linear time-varying systems
Ryotaro Okano; Takashi Kida; Tomoyuki Nagashio
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, AMER INST AERONAUT ASTRONAUT, 29, 6, 1472-1476, Nov. 2006, Peer-reviwed
Scientific journal, English

Formation Flight of Spacecraft in Earth Orbit via MPC
Satoshi Asawa; Tomoyuki Nagashio; Takashi Kida
Proc. of SICE-ICCAS 2006, 2207-2211, Oct. 2006, Peer-reviwed
International conference proceedings, English

On Stability of LSS using DVDFB Controller with Nonlinear Sensors and Actuators
Ryuta Nakama; Tomoyuki Nagashio; Takashi Kida
Proc. of SICE-ICCAS 2006, 4384-4387, Oct. 2006, Peer-reviwed
International conference proceedings, English

Nonlinear Adaptive Control for Stabilizing Spacecraft System at Capturing Phase
Akira Ito; Yuichi Ikeda; Tomoyuki Nagashio; Takashi Kida
Proc. of 25th ISTS/9th ISSFD, 625-630, Jun. 2006, Peer-reviwed
International conference proceedings, English

Optimal H∞ PD Controller Design for Flexoble Spacecraft by Branch and Bound Algorithm
Ryotaro Okano; Tomoyuki Nagashio; Takashi Kida
Trans. JSASS Space Technology, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 4, -, 11-15, Mar. 2006, Peer-reviwed, This paper proposes optimization of the PD controller gains by minimizing H infinity norm for flexible spacecraft attitude control. Solving the problem is known to be difficult because it is described by a bilinear matrix inequality (BMI) that cannot be transformed into linear matrix inequalities (LMIs). In order to solve it within practical computation time, we revise the branch and bound algorithm and incorporate the quantization of the variable domains. The ETS-VI mathematical model is used to demonstrate its ability.
Scientific journal, English

Feedback control of plants driven by nonlinear, actuators via input-state linearization
T Ninomiya; Yamaguchi, I; T Kida
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, AMER INST AERONAUT ASTRONAUT, 29, 1, 20-24, Jan. 2006, Peer-reviwed, A new systematic method to design a control law for a linear system with a nonlinear input is proposed. Conventionally, the inverse of the nonlinear function is often used to such problems, but it requires too much calculation to solve the nonlinear equation at each control step. Accordingly, we propose a new method that only applies the derivative of the nonlinear function. The essential idea of this method is to extend the original system with a pseudostate variable. This approach makes it possible to avoid to use the inverse of the nonlinear function and reduces the calculation load. Some numerical simulations are presented to illustrate the validity of this method.
Scientific journal, English

Boundedness Analysis of Control System Having Dead-Zone
Tatsuya Maeda; Tomoyuki Nagashio; Takashi Kida
Proc. of 17th International Symposium on Mathematical Theory of Networks and Systems, 1806-1810, 2006, Peer-reviwed
International conference proceedings, English

基礎加振を利用した実験モーダル解析
篠原隆; 小林勇介; 明愛国; 木田隆; 飯塚進; 金森哉吏
日本機械学会論文集Ｃ編, 71, 712, 3388-3395, Dec. 2005, Peer-reviwed
Scientific journal, Japanese

Symmetric Controller Design for Symmetric Plant Using Matrix Inequalitiesw Conditions
Tomoyuki Nagashio; Takashi Kida
Proc. of 44th IEEE Conference on Decision and Control, 7704-7707, Dec. 2005, Peer-reviwed
International conference proceedings, English

移動体に搭載したアンテナの指向制御
長塩知之; 木田隆
日本機械学会論文集Ｃ編, 71, 711, 3123-3129, Nov. 2005, Peer-reviwed
Scientific journal, Japanese

Reduced-Order Symmetric H-infinity Control for Robust Attitude Control of Flexible Spacecraft
Maiko Shibata; Tomoyuki Nagashio; Takashi Kida
Proc. of SICE 2005, 1959-1962, Aug. 2005, Peer-reviwed
International conference proceedings, English

Disturbance Attenuation Control of Mobile Antenna Using Parameter Varying Notch Filter
Tomoyuki Nagashio; Takashi Kida
Proc. of 2005 International Conference on Control Application, TC4.5, 1087-1092, Aug. 2005, Peer-reviwed
International conference proceedings, English

Nonlinear Control Experiment of RC Car Using Internet
Kenichi Aoto; Masahiro Inoue; Tomoyuki Nagashio; Takashi Kida
Proc. of 2005 IEEE International Conference on Control Application, WC2.1, 1575-1580, Aug. 2005, Peer-reviwed
International conference proceedings, English

６自由度剛体宇宙機の非線形Ｈ∞制御
池田裕一; 青砥健一; 木田隆; 長塩知之
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 41, 3, 193-201, Mar. 2005, Peer-reviwed, In this paper, we consider six dof (degree of freedom) control of rigid body spacecraft via nonlinear H_∞ control method. Firstly, the motion equation of the six dof rigid body spacecraft is described and the error system is derived. Secondly, we show that the error system can be stabilized by PD control law with the constant coefficient as the case of attitude control and that it guarantees structural robust stability with respect to physical parameter error. Thirdly, based on nonlinear. H_∞ control, the design conditions of a gain that the control law becomes suboptimal H_∞ state feedback control are given. Finally, effectiveness of the control methods is verified by simulations.
Scientific journal, Japanese

Direct Displacement Feedback による非線形機械システムの制御
池田裕一; 木田隆; 長塩知之
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 41, 2, 102-110, Feb. 2005, Peer-reviwed, In this paper, we consider control of nonlinear mechanical systems by symmetric controller (DDFB controller). Firstly, we discribe DDFB controller for linear mechanical systems. Secondly, we show that nonlinear mechanical systems are stabilized by DDFB controller. Especially, we also show that for underactuated systems DDFB controller is a class of Euler-Lagrange (EL) controller for underactuated systems and that it is a special class of strict positive real based dynamic output controller to control EL systems. Finally, obitained results are verified by simulations.
Scientific journal, Japanese

伸展する宇宙構造物のゲンスケジューリング制御（第２報，柔軟構造物の場合）
李光焔; 長塩知之; 木田隆
日本機械学会論文集Ｃ編, 71, 702, 581-588, Feb. 2005, Peer-reviwed
Scientific journal, Japanese

柔軟宇宙機の６自由度非線形制御 -- 受動性に基づくアプローチ --
池田裕一; 木田隆; 長塩知之
システム制御情報学会論文集, システム制御情報学会, 18, 1, 1-9, Jan. 2005, Peer-reviwed
Scientific journal, Japanese

ディスクリプタ方程式を用いた柔軟宇宙機のゲインスケジューリング制御
奥田亮; 長塩知之; 木田隆
日本機械学会論文集Ｃ編, 71, 701, 157-163, Jan. 2005, Peer-reviwed
Scientific journal, Japanese

Accuracy improvement of ship mounted tracking antenna for satellite communications
Aiguo Ming; Tempei Yamaoka; Takashi Kida; Chisato Kanamori; Motoo Satoh
2005 IEEE International Conference on Mechatronics and Automations, Vols 1-4, Conference Proceedings, IEEE, 1369-1374, 2005, Peer-reviwed, Recently, data traffic for satellite communications is increasing rapidly, due to various new purposes besides the conventional voice phone and facsimile. For the reason, it is necessary to realize high frequency communications, which is to be assured by high accuracy of tracking control of an antenna. To meet the needs, this paper aims at the accuracy improvement of conventional ship mounted tracking antennas by introducing H-inrinity control. In this paper, the basic characteristics of tracking antenna are investigated by experiments and the model of the antenna for controller design is established. Based on the model, an H-infinity controller is designed and implemented to the antenna. Experimental results show that the tracking accuracy can be improved to +/- 0.3 [deg], which is five times higher than that by the conventional controller.
International conference proceedings, English

Gain scheduling controller synthesis with spline-type parameter-dependent quadratic forms via dilated linear matrix inequalities
Yoshiro Hamada; Isao Yamaguchi; Takashi Kida
2005 44TH IEEE CONFERENCE ON DECISION AND CONTROL & EUROPEAN CONTROL CONFERENCE, VOLS 1-8, IEEE, 1313-1318, 2005, Peer-reviwed, This paper proposes a new synthesis of a gain scheduling controller based on the approximation of Lyapunov matrices by spline functions. The synthesis condition is described as dilated linear matrix inequalities which can be solved numerically. While in a previous study the derived feedback gains always have the same knots as the approximated Lyapunov matrices, our condition enables the feedback gains to have fewer knots without conservatism. Scheduled gains which are piecewise-linear on a parameter can also be obtained by adding constraints to the proposed synthesis condition.
International conference proceedings, English

Robust Control of Flexible Mechanical Systems by Utilizing Symmetry and Its Application to Large Space Structures
Tomoyuki Nagashio; Takashi Kida
IEEE 2004 CCA/ISIC/CACSD, Sep. 2004, Peer-reviwed
International conference proceedings, English

Passivity Based Control of Nonlinear Flexible Spacecraft
Yuichi Ikeda; Takashi Kida; Tomoyuki Nagashio
10th IFAC/IFORS/IMACS/IFIP Symposium on Large Scale Systems: Theory and Applications, LSS2004, Jul. 2004, Peer-reviwed
International conference proceedings, English

Linear State Feedback Control for Spacecraft with On-off Type Reaction Control Systems
Isao Yamaguchi; Tetsujiro Ninomiya; Takashi Kida; Yoshiro Hamada; Shuichi Sasa
10th IFAC/IFORS/IMACS/IFIP Symposium on Large Scale Systems: Theory and Applications, LSS2004, Jul. 2004, Peer-reviwed
International conference proceedings, English

A Study on Gain-Scheduling Control for a Large Flexible Satellite with Parameter Variation
Yoshiro Hamada; Isao Yamaguchi; Tokio Kasai; Takashi Kida; Tomoyuki Nagashi; Kenichi Nigo
10th IFAC/IFORS/IMACS/IFIP Symposium on Large Scale Systems: Theory and Applications, LSS2004, Jul. 2004, Peer-reviwed
International conference proceedings, English

Optimal static output feedback control for large space structures and its application to local control
T Nagashio; K Yamada; K Miyaji; T Kida
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, JAPAN SOC AERONAUT SPACE SCI, 47, 155, 1-8, May 2004, Peer-reviwed, A static output feedback control having positive definite gains is known to give a certain robust stability to a class of collocated space structures. This paper studies an optimal design for static output feedback gains which minimize the H norm so that the closed-loop system has the prescribed disturbance attenuation capability. For this purpose, two synthesis methods via linear matrix inequalities are proposed. Then, considering structural robustness, the construction of a local feedback control system is investigated. System features include a set of local controllers with a simple structure and the high fault tolerance for preserving closed-loop stability. The validity is numerically shown using a simple uniform beam model.
Scientific journal, English

線形システムのオンオフ状態フィードバック制御系の設計
二宮哲次郎; 木田隆; 山口功
日本航空宇宙学会論文集, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 52, 604, 182-195, May 2004, Peer-reviwed, This paper studies the controller design problem for linear time-invariant systems that have on-off type actuators. Although phase-plane analysis, the describing function approach and pulse-modulation technologies have been studied in the classical literature, such approaches do not permit the direct application of optimal controller design techniques including non-linear effects. In this paper, we propose the application of input-state linearization theory to the general class of single on-off input plants. The linearized space resulting from this method allows the application of any linear controller design tool. The method is also extended to be applicable to on-off controllers with a dead-band. To demonstrate the effectiveness of this approach, some numerical studies are presented including the lunar landing problem, and the results are evaluated and compared with numerical optimal solutions.
Scientific journal, Japanese

伸展する宇宙構造物のゲインスケジューリング制御
李光焔; 長塩知之; 木田隆
日本機械学会論文集Ｃ編, The Japan Society of Mechanical Engineers, 70, 693, 1401-1408, May 2004, Peer-reviwed, This paper studies a control of the extending space structures in orbit under gravity-gradient environment. To this end, it first introduces an equation of motion of the satellite that extends on the orbit and shows that it is a linear time-varying system. Then it is represented as a linear parameter varying system and gain-scheduling control method is applied to control it. In.order to design the non-conservative controller, the analytical method of constructing the smallest number of scheduling parameters is proposed based on a typical cylinder model. Finally, even when the generalized plant has the model error, it is shown to be applicable by adding the robust property with the constant matrix scaling. The availability of the proposed methods is proved through numerical simulations.
Scientific journal, Japanese

Numerical Solution of a Rigid Spacecraft Nonlinera H-infinity Attitude Control Law
Kenichi Aoto; Fumichika Hattori; Tomoyuki Nagashi; Takashi Kida
Proc. of 24th International Symposium on Space Technology and Sciences, May 2004, Peer-reviwed
International conference proceedings, English

クオータニオンフィードバックによる柔軟宇宙機の姿勢制御
池田裕一; 木田隆; 長塩知之
計測自動制御学会論文集, 40, 2, 239-246, Feb. 2004, Peer-reviwed
Scientific journal, Japanese

ＢＭＩ解法のための分枝限定法に関する考察 - 下界値計算法の改良による高速化 -
岡野竜太郎; 木田隆; 長塩知之
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 40, 1, 45-53, Jan. 2004, Peer-reviwed, This paper studies the reduction of computation time of the global optimization for bilinear matrix inequality. For the purpose, we investigate the branch and bound algorithm and improve its lower bound calculation algorithm. With this improvement, the elapsed time for one iteration becomes shorter and the iteration number is decreased. Other amendments are added to the branch and bound algorithm with this improvement. We show that this improvement is effective through some computer experiments. In the computer experiment, the static output feedback gain synthesis that is known to be a BMI problem is considered.
Scientific journal, Japanese

対称性を利用した大型衛星のロバスト制御
長塩知之; 山田和弘; 木田隆
計測自動制御学会論文集, 39, 4, 408-414, Apr. 2003, Peer-reviwed
Scientific journal, Japanese

パラメータ変動のある大型柔軟衛星のロバストゲインスケジューリング制御
杉田秀彦; 濱田吉郎; 山口功; 葛西時雄; 木田隆; 長塩知之; 児子健一郎
日本機械学会論文集（Ｃ）, 69, 678, 112-119, Feb. 2003, Peer-reviwed
Scientific journal, Japanese

Gain-Scheduling Control for Extending Space Structures
Kouen Li; Tomoyuki Nagashio; Takashi Kida
Motion and Vibration Control, The Japan Society of Mechanical Engineers, 6, 2, 955-960, Aug. 2002, Peer-reviwed, This paper studies a control of the extending space structures in orbit under gravity-gradient environment. To this end, it first introduces an equation of motion of the satellite that extends on the orbit and shows that it is a linear time-varying system. Then it is represented as a linear parameter varying system and the way applying Gain-scheduling control method is described. Finally, by using a simple column model, it gives an example that the gravity-gradient stability condition which stands up for the non-extending satellite becomes ineffective for the extending one and that the obtained controller can stabilize it within the sufficient accuracy.
International conference proceedings, English

Optimal Static Output Feedback Control for Large Space Structures
Tomoyuki Nagashio; Kazuhiro Yamada; Kaneko Miyaji; Takashi Kida
23rd International Symposium on Space Technology and Sciences, 943-948, May 2002, Peer-reviwed
International conference proceedings, English

Study of On-Orbit System Identification Experiments on Engineering Test Satellite-VIII in Normal Control Mode
Tokio Kasai; Isao Yamaguchi; Hirotaka Igawa; Yoshiro Hamada; Kenichiro Nigo; Masafumi Ikeda; Kei Sunagawa; Takashi Kida
23rd International Symposium on Space Technology and Sciences, May 2002, Peer-reviwed
International conference proceedings, English

技術試験衛星VIII型による軌道上システム同定実験のための予備検討
山口功; 葛西時雄; 木田隆; 児子健一郎; 池田正文; 井川寛隆
計測自動制御学会論文集, 38, 3, 277-283, Mar. 2002, Peer-reviwed
Scientific journal, Japanese

System Identification Experiments of Large Space Structures
Isao Yamaguchi; Takashi Kida
Trans. of the Society of Instrument and Control Engineering, E-1, 1, 312-321, Mar. 2002, Peer-reviwed
Scientific journal, English

伸展する宇宙構造物の安定性と安定化
岡野竜太郎; 木田隆
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 38, 3, 284-292, Mar. 2002, Peer-reviwed, This paper studies the problem of stabilization of extending space structures. We derive the equations of motion of the structure extending in orbit under the gravity gradient torque environment. Because the equation is a time-varying system, the existing condition of gravity gradient stabilization developed for the non-extending system is not valid for the case. Therefore we newly derive a stability condition of time-varying systems, based on which the asymptotically stabilizing control law is derived. The obtained result is confirmed by some simulations. It is also shown that the same stability condition is applicable when the structure has physical parameter errors.
Scientific journal, Japanese

Nonlinera Spacecraft Attitude Control by Control Moment Gyro
Kenichi Aoto; Kenji Tsuto; Tomoyuki Nagashio; Takashi Kida
INTERMAC 2001 Joint Technical Conference, Nov. 2001
International conference proceedings, English

Robust Control of Spacecraft with Mobile Appendages
Tomoyuki Nagashio; Takashi Kida
Trans. of the Japan Society for Aeronautics and Space Sciences, 44, 143, 40-47, 2001, Peer-reviwed
Scientific journal, English

On Local Control of Space Structures
Noriaki Takemura; Tomoyuki Nagashio; Takashi Kida; Keiji Komatsu
Proc. of 22nd International Symposium on Space Technology and Sciences, Morioka, Japan, May 28-June 1, May 2000, Peer-reviwed
International conference proceedings, English

Robust Control of Spacecraft with Mobile Appendages
Tomoyuki Nagashio; Takashi Kida
Proc. of 22nd International Symposium on Space Technology and Sciences, Morioka, Japan, May 28-June 1, May 2000, Peer-reviwed
International conference proceedings, English

Attitude control of spacecraft with mobile antenna by a gain-scheduled H-infinity controller
T Nagashio; T Kida
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, JAPAN SOC AERONAUT SPACE SCI, 43, 139, 16-22, May 2000, Peer-reviwed, This paper studies the attitude control problem of a class of data relay satellite which has a large mobile antenna for tracking target spacecraft in low orbit. The movement of the antenna disturbs the satellite attitude motion through dynamic coupling of the motions of the antenna and the satellite main body. Tn the operation, control of the spacecraft attitude must be maintained even when the antenna rotates at a high angular velocity. In this paper, we apply robust gain-scheduled controller synthesis to this problem. The controller is designed as a robust stabilizing controller based on the H-alpha controller synthesis of linear parameter varying system. The capability of the method is investigated by a numerical study.
Scientific journal, English

LPVモデルを用いた宇宙構造物の制御（LMIによるゲインスケジュールH∞制御設計）
長塩知之; 木田 隆
日本機械学会論文集（C編）, 66, 649, 3019-3025, 2000, Peer-reviwed
Scientific journal, Japanese

軌道上で増設される宇宙構造物の分散制御
望月一憲; 木田隆; 小松敬治; 山口功
計測自動制御学会論文集, 計測自動制御学会, 36, 1, 82-89, 2000, Peer-reviwed
Scientific journal, Japanese

Nonlinear Control of Arm-mounted Orbital Servicing Vehicle by Imput-State Linearization
Kazutaka Yamamoto; Isao Yamaguchi; Takashi Kida
50th International Astronautical Congress, IAF-99-A.5.05, Oct.4-8, Amsterdam, Netherlands, Oct. 1999, Peer-reviwed
International conference proceedings, English

Robust Attitude Controller Design of Linear Parameter Varying Spacecraft via μ Synthesis and Gain Scheduling
Tomoyuki Nagashio; Takashi Kida
Proc. of IEEE International Conference on Control Application, Aug.22-27, Hawaii, USA, 979-984, Aug. 1999, Peer-reviwed
International conference proceedings, English

On-orbit system identification experiments on Engineering Test Satellite-VI
S Adachi; Yamaguchi, I; T Kida; T Sekiguchi; K Yamada; Y Chida
CONTROL ENGINEERING PRACTICE, PERGAMON-ELSEVIER SCIENCE LTD, 7, 7, 831-841, Jul. 1999, Peer-reviwed, On-orbit system identification experiments were performed using the Engineering Test Satellite-VI (ETS-VI), launched in 1994. The purpose of the experiments is to check the validity of a mathematical model for ETS-VI which was previously obtained by ground experiments. Two kinds of system identification schemes are utilized. One is a traditional scheme based on polynomial black-box models such as the prediction error method, and the other is a subspace method based on state-space models. The purpose of this paper is to compare these system identification schemes using experimental data. It will be shown that the subspace method proves to be promising for the system identification of large space structures typified by ETS-VI. (C) 1999 Elsevier Science Lid. All rights reserved.
Scientific journal, English

大型宇宙構造物の分散DVDFB制御―耐故障性と最適性―
小林洋二; 池田雅夫; 藤崎泰正; 松田雅義; 木田 隆
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 35, 7, 919-925, 1999, Peer-reviwed, Decentralized control is considered for large space structures composed of a number of subsystems which are connected by springs and dampers. It is assumed that sensors and actuators are collocated. It has been known that the overall system is stable under any perturbations in mass, damping and stiffness if the control law for each subsystem is direct velocity and displacement feedback (DVDFB). In this paper, a condition on interconnections between subsystems is presented under which stability of the overall system is preserved even in case some local controllers fail. Furthermore, it is shown that with appropriately chosen gains, the decentralized DVDFB is optimal for a quadratic cost function.
Scientific journal, Japanese

パラメータ変動のある宇宙構造物の制御（ディスクリプタ形式によるμ設計）
長塩知之; 木田 隆
日本機械学会論文集（C編）, 65, 636, 2693-2699, 1999, Peer-reviwed
Scientific journal, Japanese

Nonlinear Control of Orbital Servicing Vehicle
Takashi Kida; Toshihiro Mochizuki; Isao Yamaguchi
49th International Astronautical Congress, IAF-98-A, Sept.28-Oct.2, Melbourne, Australia, Sep. 1998, Peer-reviwed
International conference proceedings, English

On-orbit attitude control experiments using ETS-VI by H-infinity control and two-degree-of-freedom control
Y Chida; H Soga; Y Yamaguchi; T Kida; Yamaguchi, I; T Sekiguchi
CONTROL ENGINEERING PRACTICE, PERGAMON-ELSEVIER SCIENCE LTD, 6, 9, 1109-1116, Sep. 1998, Peer-reviwed, The engineering Test Satellite VI (ETS-VI) is a three-axis-stabilized satellite launched by NASDA in 1994. On-orbit experiments, which consist of identification and attitude-control experiments, were planned as one of the ETS-VI on-board experimental programs, and were carried out in 1995. This experimental program was called 'FLEX' (FLexible EXperiments). The purpose of FLEX was to establish fundamental attitude-controller design methods for a flexible-structure satellite. In this paper, attitude controller design methods for FLEX are discussed, and some results of the attitude-control experiments are presented. The attitude controllers were designed using an H-infinity, control method and a two-degree-of-freedom control method. H-infinity, controllers were derived using the specified stability degree method. On the other hand, conventional two-degree-of-freedom control design methods could not be applied for the FLEX, because the program memory area was restricted to about 2.6 Kbytes. In this paper, feedforward control design methods which never increase the order of the controller were proposed and applied. Experimental results showed a rapid tracking response and high disturbance-attenuation performance, which have been anticipated by simulations on the ground. Noting that the on-orbit experiments presented here have not previously been carried out, the authors believe these results will be utilized for attitude controller design in the future. (C) 1998 Elsevier Science Ltd. All rights reserved.
Scientific journal, English

Three-Axis Attitude Control of Spacecraft with Rotating Flexible Solar Pannels
Tomoyuki Nagashio; Takashi Kida
Proc. of Fourth International Conference on Motion and Vibration Control, ETH Zurich, Switzerland, August 25-28, 969-974, Aug. 1998, Peer-reviwed
International conference proceedings, English

Decentralized Control of Large Space Structures Expandingly Constructed in Orbit
Takashi Kida; Kazunori Mochzuki; Kenji Komatsu; Isao Yamaguchi
Proc. of 21th International Symposium on Space Technology and Science, ISTS 98-c-04, May 24-31, Ohmiya, 562-566, May 1998, Peer-reviwed
International conference proceedings, English

Open-Loop System Identification of Large Space Structures from Closed-Loop Impulse Response by On-Orbit Excitation
Isao Yamaguchi; Takashi Kida; Takeshi Sekiguchi
Proc. of 21th International Symposium on Space Technology and Science, ISTS 98-c-04, May 24-31, Ohmiya, 718-723, May 1998, Peer-reviwed
International conference proceedings, English

Decentralized control of expandingly constructed large space structures
T Kida; K Komatsu; Yamaguchi, I
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, AMER INST AERONAUT ASTRONAUT, 21, 2, 356-358, Mar. 1998, Peer-reviwed
Scientific journal, English

On-orbit identification experiments by Engineering Test Satellite-VI
S Adachi; Yamaguchi, I; T Kida; T Sekiguchi; K Yamada; Y Chida
(SYSID'97): SYSTEM IDENTIFICATION, VOLS 1-3, PERGAMON PRESS LTD, 401-406, 1998, Peer-reviwed, On-orbit system identification experiments have been performed using Engineering Test Satellite-VI (ETS-VI) launched in 1994. The purpose of the experiments is to check the validity of a mathematical model for ETS-VI which was previously obtained by ground experiments. Two kinds of system identification algorithms are utilized. One is a prediction error method and the other is a subspace-based method. The purpose of this paper is to compare these system identification algorithms using experimental data. It will be shown that the subspace method is promising for system identification of large space structures.
International conference proceedings, English

On-orbit robust control experiment of flexible spacecraft ETS-VI
T Kida; Yamaguchi, I; Y Chida; T Sekiguchi
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, AMER INST AERONAUT ASTRONAUT, 20, 5, 865-872, Sep. 1997, Peer-reviwed, An on-orbit attitude and vibration control experiment has been performed as a part of experiments of the ETS-VI, which was launched by the H-II rocket in August 1994. The purpose is to develop precise attitude central technology for future large spacecraft or large space structures. To this end, we have designed three types of controllers in linear quadratic Gaussian and H infinity, frameworks to achieve the robust stability against residual modes and modal parameter errors. The experiments were done at the beginning of 1995, and their feasibility has been proved. The flight experiment results and the modeling and the controller synthesis methods are reported. Based on the on orbit results, the capabilities of controllers are compared and discussed.
Scientific journal, English

ETS-VI軌道上同定実験データによる予測誤差法と部分空間法の比較
足立修一; 永田寛; 山口功; 木田隆; 関口毅
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 33, 8, 805-811, Aug. 1997, Peer-reviwed, System identification experiments for a large space structure (LSS) have been performed as ones of on-orbit experiments using Engineering Test Satellite-VI (ETS-VI) which was launched in August 1994. The purpose of the system identification experiments is to check the validity of a mathematical model for ETS-VI which was previously obtained by ground experiments. There are two types of excitation methods by gas jet thrusters of Reaction Control System (RCS), that is, an impulse excitation and random excitation. In this paper, we concentrate on the latter excitation method. As an output signal, the satellite attitude along the excited axis is monitored during the experiments. Two kinds of methods are utilized for system identification. One is based on polynomial models such as a prediction error method (as a special case, least-squares method is included), and an instrumental variable method. The other is a subspace-based method which has been of great interest recently. The purpose of this paper is to compare these system identification methods based on experimental data. It will be shown that the subspace method is promising for system identification of LSS.
Scientific journal, Japanese

宇宙構造物のロバスト制御の実験的検討
木田隆; 山口功; 千田有一; 関口毅
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 33, 7, 639-647, Jul. 1997, Peer-reviwed, On-Orbit control experiment of ETS-VI has been successfully performed. The purpose is to demonstrate the robust control capability in the large space structures control technology. This paper describes the experiment results of four types of robust controllers designed in LQG and H^∞ framework. The modeling method and the controllers design procedures are outlined. The obtained experiment results are analyzed and compared with the simulation results.
Scientific journal, Japanese

Decentralized Control of Space Structures by mu synthesis
Takashi Kida; Isao Yamaguchi
Proc. of 2nd Asian Control Conference, 215-218, Jul. 1997, Peer-reviwed
International conference proceedings, English

閉ループ系のインパルス応答列による開ループ系の同定とその宇宙構造物への応用
山口功; 木田隆
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 33, 4, 311-313, Apr. 1997, Peer-reviwed, This paper disscusses open loop system identification method from impulse response of closed loop system using ERA. Some experimental demonstration using Engineering Test Satellite-VI (ETS-VI) is shown to verify the validity of the algorithm.
Scientific journal, Japanese

H∞制御によるETS-VIの軌道上での姿勢制御実験
木田隆; 山口功; 千田裕一; 関口毅
日本航空宇宙学会誌, 45, 520, 284-294, 1997, Peer-reviwed
Scientific journal, Japanese

ETS-VI On-orbit System Identification Experiment
Isao Yamaguchi; Takashi Kida; Keiji Komatsu; Masaaki Sano; Takeshi Sekiguchi; Shin-ichi Ishikawa; Shin-ichiro Ichikawa; Katsuhiko Yamada; Yuichi Chida; Shuichi
International Journal of Japan Society of Mechanical Engineering, 40, 4, 623-629, 1997, Peer-reviwed
Scientific journal, English

周波数整形H∞制御を用いた柔構造衛星の軌道上姿勢制御実験
柏瀬俊夫; 山田克彦; 阿波祐二; 関口毅; 木田隆
日本機械学会（Ｃ）, 64, 606, 476-483, 1997, Peer-reviwed
Scientific journal, Japanese

On-orbit Attitude Control Experiments for ETS-VI by I-PD Control
Takeshi Sekiguchi; Takashi Kida; Isao Yamaguchi; Yuichi Chida; Takashi Shigemasa; Yoshitake Yamaguchi; Hiroshi Soga; Masaya Mine
Journal of Space Technology and Sciences, 11, 1, 1-8, 1997, Peer-reviwed
Scientific journal, English

H∞制御と２自由度系によるETS-VIの軌道上制御実験
千田有一; 山口慶剛; 曽我広志; 木田隆; 山口功; 関口毅
計測自動制御学会論文集, 32, 3, 423-425, Mar. 1996, Peer-reviwed
Scientific journal, Japanese

１入力多出力系としての柔軟宇宙構造物のモーダルパラメータ同定実験
山口功; 木田隆; 葛西時雄; 佐野政明; 小松敬治
計測自動制御学会論文集, 計測自動制御学会, 32, 3, 423-425, Mar. 1996, Peer-reviwed
Scientific journal, Japanese

On-orbit attitude control experiments for ETS-VI - I-PD and two-degree-of-freedom H-infinity control
Y Chida; Y Yamaguchi; H Soga; T Kida; Yamaguchi, I; T Sekiguchi
PROCEEDINGS OF THE 35TH IEEE CONFERENCE ON DECISION AND CONTROL, VOLS 1-4, I E E E, 486-488, 1996, Peer-reviwed, Engineering Test Satellite VI (ETS-VI) is a three-axis-stabilized satellite launched by National Space Development Agency of Japan in 1994. Identification and attitude control experiments on orbit were planned as one of the ETS-VI experimental programs and were carried out in 1995. These experiments were the first tests fulfilled by Japan for a real on-orbit satellite. In this paper, we present certain results of the attitude control experiments using I-PD control and two-degree-of-freedom control based on H-infinity control. Experimental results showed that these controllers provide the expected control performance and that these design methods are effective for satellite control.
International conference proceedings, English

On-Orbit Ropbust Control Experiment of Felexible Spacecraft ETS-VI
Takashi Kida; Isao Yamaguchi; Yuichi Chida; Takeshi Sekiguchi
AIAA Guidance, Navigation, and Control Conference, 1996, Peer-reviwed
International conference proceedings, English

Attitude Control of an Artificial Satellite Using H∞ and Two-Degree-Of Freedom Control
Yuichi Chida; Yoshitake Yamaguchi; Hiroshi Soga; Takashi Kida; Isao Yamaguchi; Takeshi Sekiguchi
Proc. of 13th IFAC World Congress, 189-194, 1996, Peer-reviwed
International conference proceedings, English

On-Orbit Experiments of Frequency-Shaped H∞ Control of Flexible Space Structures
Toshio Kashiwase; Katsuhiko Yamada; Yuji Awa; Takshi Sekiguchi; Takashi Kida
Proc. of 11th International Astrodynamics Symposium, 1996, Peer-reviwed
International conference proceedings, English

On-Orbit Attitude Control Experiment of ETS-VI
Takashi Kida; Takeshi Sekiguchi; Yuuichi Chida; Toshio Kashiwase
Proc. of 11th International Astrodynamics Symposium, 17-20, 1996, Peer-reviwed
International conference proceedings, English

Experimental demonstration of LSS system identification by eigensystem realization algorithm
YAMAGUCHI, I; T KIDA; T KASAI
PROCEEDINGS OF THE 1995 AMERICAN CONTROL CONFERENCE, VOLS 1-6, AMER AUTOMATIC CONTROL COUNCIL, 407-411, 1995, Peer-reviwed
International conference proceedings, English

Decentralized Control of Large Space Structures
Takashi Kida; Keiji Komatsu
Proc. of 1st Asian Control Conference, 445-448, 1994, Peer-reviwed
International conference proceedings, English

宇宙ロボットのＤＰによる最適軌道生成
山口功; 木田隆; 上野誠也; 田中正樹
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 29, 10, 1184-1190, Oct. 1993, Peer-reviwed, This paper discusses the optimal hand trajectories generation for a space robot manipulator. On the topic, the analytical optimal solution exists only for a simplified mathematical model. For the practical case where mass and moment of inertia of links are taken into account, large-dimensional non-linear two point boundary value problem must be solved to obtain the optimal hand trajectory. In this numerical approach, iterative calculation is required to improve the accuracy of solution that takes too much time and cost. In this paper new optimization algorithm by the method of Dynamic Programming (DP) is proposed to solve optimal hand trajectories for the general space robot model with a two-joint arm in the two dimensional coordinate system. This method has the advantages reducing the computational time substantially. Comparison with the numerical results by the method of optimal control theory are made to demonstrate the accuracy of the proposed method.
Scientific journal, Japanese

加速度計出力を用いた宇宙構造物の時間領域での同定
山口功; 佐々修一; 木田隆
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 29, 8, 721-723, Aug. 1993, Peer-reviwed, This paper describes the application of system identification method in the time domain using accelerometer outputs that are typical measurement devices for satellite and space strucures. ERA (Eigen-system Realization Algorithm) modified by the iterative least square method is applied in the analysis. Results of numerical simulations for ETS-VI which will be launched by H-II rocket in 1994 show the validity of the method.
Scientific journal, Japanese

Optimality of Direct Velocity and Displacement Feedback for Large Space Structures with Collocated Sensors and Actuators
Masao Ikeda; Kazuhisa Koujitani; Takashi Kida
12th IFAC World Congress, Jul. 1993, Peer-reviwed
International conference proceedings, English

著しい形態変化を伴う多体システムの動的シミュレーションアルゴリズム
狼嘉彰; 岡本修; 山口功; 木田隆
日本機械学会論文集（Ｃ）, The Japan Society of Mechanical Engineers, 59, 568, 3778-3784, 1993, Peer-reviwed, The objective of this paper is to establish a computer algorithm capable of simulating dynamics of variable configuration systems based on the unified matrix approach for multibody systems of N bodies connected by M generic hinges with M ≥ N. The system may have an arbitrary system topology, including chain, tree and closed-loop configuration. Hinge can be either a physical joint mechanism such as gimbal, ball-joint, or spring-damper, or a hypothetical connecting point of two adjacent bodies as in case of docking. Any change in configuration and constraint conditions has been modeled by a function dependent on time and states. The approach developed here is essentially based on the formulation of a matrix form of the linear algebraic equation to be solved simultaneously for the time derivatives of non-holonomic angular and linear momenta, and the internal non-working constraint torques and forces. The non-holonomic momenta are derived for each body referring to the angular and linear velocities with respect to the inertially fixed frame expressed in the body frame of each body. With this selection of the variables, the linear equation takes a form Ax=B, where the coefficient matrix A represents the system configuration and the constraint conditions. This approach has been proven useful in simulation, such as separation, connection, topology change, and change in constraint degrees-of-freedom.
Scientific journal, Japanese

Target Capture Control Ground Experiments by Space Robot Manupulator Arm
Fuyuto Terui; Seiya Ueno; Isao Yamaguchi; Masaaki Tanaka; Takashi Kida
Proc. of JSME International Conference on Advanced Mechatronics, 842-847, 1993, Peer-reviwed
International conference proceedings, English

ETS-VI Attitude Control Experiments on Orbit with Flexible Structures
Masaya Mine; Hiroshi Soga; Takashi Kida; Isao Yamaguchi; Mamoru Iino; Yuichi Chida
Proc. of International Symposium on Theory of Machines and Mechanism, 775-780, Sep. 1992, Peer-reviwed
International conference proceedings, English

Robust Controller Design for LSS Attitude Control and Experimental Demonstartion
Yuichi Chida; Takashi Kida; Isao Yamaguchi; Masaya Mine; Hiroshi Soga
Preprint of International Symposium on Robotics, Mechatronics and Manufacturing Systems, 883-888, Sep. 1992, Peer-reviwed
International conference proceedings, English

大型宇宙構造物の姿勢制御実験
木田隆; 山口功; 池田雅夫
計測自動制御学会論文集, 28, 1, 107-115, 1992, Peer-reviwed
Scientific journal, Japanese

大型宇宙構造物の同定実験 - 矩形波入力による時間領域での同定
山口功; 木田隆
計測自動制御学会論文集, 28, 8, 982-990, 1992, Peer-reviwed
Scientific journal, Japanese

折り返し法を用いた大型衛星の姿勢制御
足立修一; 木田隆; 高木康夫; 森泰親
計測自動制御学会論文集, 27, 9, 1018-1024, Sep. 1991, Peer-reviwed
Scientific journal, Japanese

Ｉ-ＰＤ制御を用いた大型衛星の姿勢制御系の一設計法
足立修一; 重政隆; 木田隆
計測自動制御学会論文集, 27, 2, 242-244, Feb. 1991, Peer-reviwed
Scientific journal, Japanese

Collocated LSS制御系の伝達零
木田隆; 小松敬治; 池田雅夫
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 27, 9, 1076-1078, 1991, Peer-reviwed, Two algorithms of obtaining the transmission zeros of collocated LSS system modelled by the FEM method are proposed. Their physical meanings are investigated and a numerical example is demonstrated to verify the results.
Scientific journal, Japanese

人工衛星の非線形運動の線形化について
木田隆; 山口功
計測自動制御学会論文集, 27, 9, 1073-1075, 1991, Peer-reviwed
Scientific journal, Japanese

Robust stability—degree assignment and its applications to the control of flexible structures
Hidenori Kimura; Taro Oike; Atsuyoshi Miura; Kenji Akai; Takashi Kida
International Journal of Robust and Nonlinear Control, 1, 3, 153-169, 1991, Peer-reviwed, A new method of robust controller synthesis is introduced which is an extension of robust stabilization to robust stability‐degree assignment. This method guarantees a lower bound of stability degree for all uncertainties within a prescribed magnitude band. The method is applied to the control of four types of flexible structures, namely, colocated beam, non‐colocated beam, beam with moving base and large scale satellite model. Excellent performances have been obtained experimentally with respect to the response speed and the robustness. Copyright © 1991 John Wiley &
Sons, Ltd.
Scientific journal, English

ＤＶＦＢを用いたアクティブマスダンパの制振特性解析
上野誠也; 木田隆; 山口功; 平子敬一; 田中正樹
日本機械学会論文集（Ｃ）, 57, 536, 69-73, 1991, Peer-reviwed
Scientific journal, Japanese

大型宇宙構造物の同定実験
足立修一; 重政隆; 山口功; 木田隆
計測自動制御学会論文集, The Society of Instrument and Control Engineers, 26, 11, 1275-1282, Nov. 1990, Peer-reviwed, This paper considers the modal parameter identification problem for an LSS (Large Space Structure) from measured input-output data. The selection of setting parameters for identification, such as the sampling rate and identification model order, has great influence on the identification accuracy. This paper proposes a new identification method which uses decimated input-output data. The decimation consists of two parts, first the input-output data are filtered by low-pass filters, and then resampled by the lower sampling rate. The elastic modes can be identified accurately by proper choice of the cut-off frequency of the filter. In the proposed identification method, the model order is determined by the frequency domain criterion, that is, the flatness of the identification residual sequence. The effectiveness of the proposed identification method is shown by identification experiments which were carried out by using a ground-based test model.
Scientific journal, Japanese

Antenna Pointing System on Flexible Space Structures
Takashi Kida; Isao Yamaguchi; Seiya Ueno; Masaaki Tanaka; Keiichi Hirako
Proc. of 17th International Symposium on Space Technology and Science, 1165-1170, May 1990, Peer-reviwed
International conference proceedings, English

Robust Control for Large Space Structures: Spillover Suppression by Frequency-Shaped Optimal Regulator
Takashi Kida; Masao Ikeda
Selected Papers from IFAC Symposium on Automatic Control in Aerospace, 165-170, Jul. 1989, Peer-reviwed
International conference proceedings, English

ROBUST LSS CONTROLLER-DESIGN BY FREQUENCY SHAPING
T KIDA; Y TSUBOKAWA; M IKEDA
AIAA GUIDANCE, NAVIGATION AND CONTROL CONFERENCE, PTS 1 AND 2, AMER INST AERONAUTICS & ASTRONAUTICS, 942-948, 1989, Peer-reviwed
International conference proceedings, English

高域遮断特性をもたせた最適レギュレータとその大型宇宙構造物の制御への応用
木田隆; 山口功; 池田雅夫
計測自動制御学会論文集, 25, 4, 448-454, 1989, Peer-reviwed
Scientific journal, Japanese

Collocated Feedbackによる宇宙構造物の最適制御
糀谷和久; 池田雅夫; きた隆
計測自動制御学会論文集, 25, 8, 882-888, 1989, Peer-reviwed
Scientific journal, Japanese

大型宇宙構造物のDVFB制御
木田隆; 山口功; 上野誠也; 平子敬一
計測自動制御学会論文集, 25, 12, 1324-1330, 1989, Peer-reviwed
Scientific journal, Japanese

柔軟構造系のロバスト制御
田川泰敬; 木田隆; 狼嘉彰; 山口功
日本機械学会論文集（Ｃ）, 55, 517, 2419-2427, 1989, Peer-reviwed
Scientific journal, Japanese

A Flight Experiment on Flexible Spacecraft Attitude Control
Takashi Kida; Isao Yamaguchi; Yoshiaki Ohkami; Shinichiro Ichikawa; Yasuhiro Kawada
29th Congress of International Astronautical Federation, Jul. 1988, Peer-reviwed
International conference proceedings, English

柔軟衛星のモデリングと姿勢制御
田川泰敬; 山口功; 木田隆; 山田元
日本機械学会論文集（Ｃ）, 54, 507, 2689-2696, 1988, Peer-reviwed
Scientific journal, Japanese

Filter Accomodated Regulator for Large Space Structures Control and Its Robustness
Takashi Kida; Isao Yamaguchi; Masao Ikeda
proc. of 16th International Symposium on Space Technology and Science, 1383-1388, 1988, Peer-reviwed
International conference proceedings, English

Experimental Results of LSS Damping Enhancement with Active Mass Damper
Takashi Kida; Isao Yamaguchi; Yoshiaki Ohkami; Yoshiharu Shimamoto; Keiichi Hirako; Seiya Ueno
Proc. of 16th International Symposium on Space Technology and Science, 591-596, 1988, Peer-reviwed
International conference proceedings, English

大型柔軟衛星の三軸制御に関する研究
木田隆; 山口功; 岡本修; 狼嘉彰; 市川信一郎; 田中俊輔
日本航空宇宙学会, The Japan Society for Aeronautical and Space Sciences, 35, 407, 569-576, 1987, Peer-reviwed, This paper studies three-axis attitude control problems of a class of flexible spacecraft having elastic appendages. A Linear Quadratic Regulator (LQR) associated with a state estimator is designed to control its attitude and the appendage vibration, simultaneously. In order to evaluate and demonstrate the controller performance, ground-based control experiments are conducted, using a ETS (Engineering Test Satellite)-VI laboratory model supported on a single-axis air-table. The evaluation is made concerning mainly with (a) LQR realization by using a thruster and a reaction wheel, and (b) stability robustness against the truncated vibration modes of flexible appendages.
Scientific journal, Japanese

AN OPTIMAL SLEWING MANEUVER APPROACH FOR A CLASS OF SPACECRAFT WITH FLEXIBLE APPENDAGES
T KIDA; YAMAGUCHI, I; Y OHKAMI; K HIRAKO; H SOGA
ACTA ASTRONAUTICA, PERGAMON-ELSEVIER SCIENCE LTD, 13, 6-7, 311-318, Jun. 1986, Peer-reviwed
Scientific journal, English

An Approach to Local Decentralized Control for Large Flexible Space Structures
Takashi Kida; Isao Yamaguchi; Yoshiaki Ohkami
Guidance, Navigation and Control Conference, Aug. 1985, Peer-reviwed
International conference proceedings, English

A Matrix Approach to Dynamics Formulation of Comlex Space Structures
Yoshiaki Ohkami; Osamu Okamoto; Takashi Kida; Isao Yamaguchi; Kotaro Matsumoto
Proc. of 5th VPI & SU/AIAA Symposium on Dynamics and Control of Large Flexible Spacecraft, 325-340, Jun. 1985, Peer-reviwed
International conference proceedings, English

POLES AND TRANSMISSION ZEROS OF FLEXIBLE SPACECRAFT CONTROL-SYSTEMS
T KIDA; Y OHKAMI; S SAMBONGI
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, AMER INST AERONAUT ASTRONAUT, 8, 2, 208-213, 1985, Peer-reviwed
Scientific journal, English

A PRELIMINARY-STUDY ON DECENTRALIZED CONTROL OF LARGE-SCALE FLEXIBLE SPS
T KIDA; Y OHKAMI
SPACE SOLAR POWER REVIEW, PERGAMON-ELSEVIER SCIENCE LTD, 5, 2, 171-177, 1985, Peer-reviwed
Scientific journal, English

Local Output-Feedback for Large Flexible Space Structure
Takashi Kida; Isao Yamaguchi; Yoshiaki Ohkami
Proc. of 14th International Symposium on Space Technology and Science, 969-974, Jun. 1984, Peer-reviwed
International conference proceedings, English

Horizon Scanner Flight Experiment on Engineering Test Satellite IV
Takashi Kida; Yoshiaki Ohkami; Chikara Murakami; Masami Ikeuchi; Takahiro Suzuki; Yasuhumi Wakabayashi
Proc. of 13th International Symposium on Space Technology and Science, 731-736, Jun. 1982, Peer-reviwed
International conference proceedings, English

On Modern Modal Controller for Flexible Space Structures: A Sensitivity Analysis
Takashi Kida; Osamu Okamoto; Yoshiaki Ohkami
Proc. of NCKU/AAS International Symposium on Engineering Science and Mechanics, 968-978, Dec. 1981, Peer-reviwed
International conference proceedings, English

A Sensitivity Analysis on Modal Controller for Flexible Space Structures
Takashi Kida; Osamu Okamoto; Yoshiaki Ohkami
Proc. of 8th IFAC World Congress, XVI, 46-51, Aug. 1981, Peer-reviwed
International conference proceedings, English

Some Aspects of Flexible Spacecraft Attitude Control
Takashi Kida; Yoshiaki Ohkami
31st Congress of International Astronautical Federation, Sep. 1980, Peer-reviwed
International conference proceedings, English

Simulation of Digital Controller for Flexible Spacecraft Attitude Control
Yoshiaki Ohkami; Osamu Okamoto; Takashi Kida
Proc. of 2nd VPI & SU/AIAA Symposium on Dynamics and Control of Large Flexible Spacecraft, 177-189, Jun. 1979, Peer-reviwed
International conference proceedings, English

Synthesis and Development Procedure of Microprocessor Software Program for Spacecraft Digital Attitude Control
Takashi Kida; Osamu Okamoto; Yoshiaki Ohkami
Trans. of Japan Society for Aeronautics and Space Sciences, 21, 54, 173-181, 1979, Peer-reviwed
Scientific journal, English

Numerical Simulation of Spacecraft Digital Attitude Control Using Microprocessor
Takashi Kida; Osamu Okamoto; Yoshiaki Ohkami
Proc. of 12th International Symposium on Space Technology and Science, 383-388, 1977, Peer-reviwed
International conference proceedings, English

A Method of Determination of Three Principal Axes of Inertia of a Simulated Satellite Supported on a Spherical Air Bearing
Chikara Murakami; Takashi Kida; Atsushi Nakajima
Trans. of Japan Society for Aeronautics and Space Science, 19, 46, 179-188, 1976, Peer-reviwed
Scientific journal, English

宇宙機の相対運動とその制御 – ランデブーおよびフォーメーションフライト --
木田隆; 山口功
Jun. 2005, システム/制御/情報, 49, 6, 230-237, Japanese, Introduction other

宇宙開発を支える制御技術
千田有一; 木田隆
The Society of Instrument and Control Engineers, Apr. 2003, 計測と制御, 42, 4, 333-335, Japanese, Introduction other, 0453-4662, 130003454542

宇宙機の安定化と制御系設計
木田隆
Oct. 2001, システム/制御/情報, 45, 10, 556-561, Japanese, Introduction other

大型宇宙システムとその振動制御
木田 隆
日本設計工学会, 1999, 設計工学, 34, 1, 9-13, Japanese, Introduction other, 0919-2948, 10002248979, AN10402165

宇宙システムと振動制御
木田 隆
計測自動制御学会, 1998, 計測と制御（計測自動制御学会）, 37, 8, 569-571, Japanese, Introduction other, 0453-4662, 10004317751, AN00072406

きく6号を用いた姿勢制御実験-IPD制御，2自由度H∞制御の応用
千田有一; 木田 隆; 関口 毅
Institute of Systems, Control and Information Engineers, 1998, システム／制御／情報, 42, 11, 591-598, Japanese, Introduction other, 0916-1600, 110003891379, AN10062329

人工衛星の力学と制御ハンドブック
姿勢制御研究委員会
Japanese, Joint work, 培風館, Jul. 2007

航空宇宙工学便覧第３版
日本航空宇宙学会
Japanese, Contributor, 丸善, Nov. 2005

フィードバック制御の基礎
木田隆
Japanese, 培風館, Nov. 2003

人工衛星と宇宙探査機
木田隆; 小松敬治; 川口淳一郎
Japanese, Joint work, コロナ社, Sep. 2001

Spacecraft Attitude Control and Dynamics
木田隆
Japanese, Corona Publishing Co. , Ltd., Mar. 1999

宇宙工学入門２
茂原正道; 木田隆
Japanese, Joint work, 培風館, 1998

H∞制御の実プラントへの応用
計測自動制御学会
Japanese, Editor, コロナ社（計測自動制御学会編）, 1996

回転する太陽電池パネルをもつ柔軟宇宙機の入力整形手法を用いた高速・高精度姿勢マヌーバ制御
千田祐希; 長塩知之; 木田隆
Oral presentation, Japanese, 第56回自動制御連合講演会, 日本機械学会, 新潟, Domestic conference
17 Nov. 2013

Tube MPC による柔軟構造物の振動を考慮した人工衛星の姿勢制御
一志太樹; 木田隆
Oral presentation, Japanese, 第56回自動制御連合講演会, Domestic conference
17 Nov. 2013

スラスタ配置を考慮した宇宙機のオンオフ姿勢制御 - モデル予測制御と0-1最適化
小泉祐輔; 浅川岳也; 木田隆
Oral presentation, Japanese, 計測自動制御学会,第30回誘導制御シンポジウム
May 2013

モデル予測制御による人工衛星のフォーメーションフライトと衝突回避
吉光亮; 木田隆
Oral presentation, Japanese, 計測自動制御学会,第13回計測自動制御学会制御部門大会
Mar. 2013

ＬＭＩを用いた柔軟宇宙構造物の構造パラメータと制御則の同時最適化
山本一路; 木田隆
Oral presentation, Japanese, 計測自動制御学会,第13回計測自動制御学会制御部門大会
Mar. 2013

アクチュエータのオンオフ特性を考慮したモデル予測制御
淺川岳也; 木田隆
Oral presentation, Japanese, 計測自動制御学会,第12回計測自動制御学会制御部門大会
Mar. 2012

線形時変力学系の安定性と安定化制御器の設計
高久雄一; 木田隆
Oral presentation, Japanese, 計測自動制御学会,第12回計測自動制御学会制御部門大会
Mar. 2012

入力拘束を考慮した柔軟衛星のAnti-windup制御
淺川岳也; 山口功; 濱田吉郎; 葛西時雄; 長塩知之; 木田隆
Oral presentation, Japanese, 計測自動制御学会,第28回誘導制御シンポジウム
May 2011

パラメータ変動を持つ柔軟宇宙機のGKYP補題を用いたDVDFB制御系の最適設計
高久雄一; 長塩知之; 木田隆
Oral presentation, Japanese, 計測自動制御学会,第11回制御部門大会
Mar. 2011

入力拘束を考慮したロバスト予測制御の柔軟衛星への適用
山下哲生; 濱田吉郎; 山口功; 木田隆; 長塩知之
Oral presentation, Japanese, 計測自動制御学会,第11回制御部門大会
Mar. 2011

ジャイロ剛性項を持つ力学系の非対称静的出力フィードバック制御とその最適化
黒滝勇貴; 長塩知之; 木田隆
Oral presentation, Japanese, 計測自動制御学会,第11回制御部門大会
Mar. 2011

入力拘束を考慮したモデル予測制御の柔軟衛星への適用
山下哲生; 濱田吉郎; 山口功; 木田隆; 長塩知之
Oral presentation, Japanese, 日本機械学会,第53回自動制御連合講演会
Nov. 2010

プラクティカル安定性に基づく宇宙機の離散トラッキング制御
西村麻希; 長塩知之; 木田隆
Oral presentation, Japanese, 日本機械学会,第53回自動制御連合講演会
Nov. 2010

宇宙機の対称性を利用した力学系の安定性と制御系による安定化・最適化
長塩知之; 木田隆
Oral presentation, Japanese, 理論応用力学会,第59回理論応用力学講演会講演論文集
Jun. 2010

宇宙機の非線形トラッキング制御問題とその解法について
坂本篤志; 長塩知之; 木田隆
Oral presentation, Japanese, 計測自動制御学会,第27回誘導制御シンポジウム
May 2010

一般化ＫＹＰ補題を用いた柔軟衛星のＤＶＤＦＢ制御器のＨ∞最適設計
高久雄一; 長塩知之; 木田隆
Oral presentation, Japanese, 計測自動制御学会,第27回誘導制御シンポジウム
May 2010

人工衛星に搭載された可動アンテナの高精度指向を実現するための制御系設計
後藤亮; 長塩知之; 木田隆
Oral presentation, Japanese, 日本機械学会,第18回スペースエンジニアリングコンファレンス
Jan. 2010

柔軟衛星のオンライン同定とインップットシェーピング手法への適用
武富遊; 岸本長; 長塩知之; 木田隆; 山口功
Oral presentation, Japanese, 日本機械学会,第18回スペースエンジニアリングコンファレンス
Jan. 2010

線形時変機械システムのフィードバック制御によるロバスト安定化
木村匠; 長塩知之; 木田隆
Oral presentation, Japanese, 計測自動制御学会,自動制御連合講演会
Nov. 2009

入力拘束を考慮した柔軟衛星のモデル予測制御
木田隆; 長塩知之
Oral presentation, Japanese, 計測自動制御学会,第26回誘導制御シンポジウム
May 2009

入力整形による柔軟衛星の姿勢角変更と実験による検証
岸本長; 山田敦大; 長塩知之; 木田隆; 山口功
Oral presentation, Japanese, 計測自動制御学会,第26回誘導制御シンポジウム
May 2009

偏心ホイールを擾乱源とする宇宙機の姿勢制御
門倉雄大; 坪内健; 長塩知之; 木田隆; 山口功
Oral presentation, Japanese, 計測自動制御学会,第26回誘導制御シンポジウム
May 2009

センサフュージョンによる宇宙機の姿勢制御
森敦司; 木田隆; 長塩知之
Oral presentation, Japanese, 日本機械学会,第17回スペースエンジニアリング・コンファレンス
Jan. 2009

柔軟衛星の姿勢制御のためのＨ∞PD制御系設計
崔星太; 長塩知之; 木田隆
Oral presentation, Japanese, 日本機械学会,第17回スペースエンジニアリング・コンファレンス
Jan. 2009

ＣＭＧを用いた柔軟衛星の高速高精度スイッチングマヌーバ
田中敬朗; 長塩知之; 木田隆; 巳谷真司; 大谷崇; 山口功; 葛西時雄; 濱田吉郎; 井川寛隆; 坂井真一郎; 坂東信尚; 中邨勉
Oral presentation, Japanese, 日本航空宇宙学会,第52回宇宙科学技術連合講演会講演集
Nov. 2008

ＡＳＴＲＯ－Ｇの高速・高精度姿勢変更のためのＣＭＧ制御則の一検討
中邨勉; 坂東信尚; 坂井真一郎; 神谷俊夫; 小倉直人; 長塩知之; 木田隆; 斎藤宏文
Oral presentation, Japanese, 日本航空宇宙学会,第52回宇宙科学技術連合講演会講演集
Nov. 2008

大型柔軟衛星ＡＳＴＲＯ－Ｇの高精度スイッチングマヌーバのための制御手法に関する検討
長塩知之; 木田隆; 巳谷真司; 大谷崇; 山口功; 葛西時雄; 濱田吉郎; 井川寛隆; 坂井真一郎; 坂東信尚; 中邨勉
Oral presentation, Japanese, 計測自動制御学会,第25回誘導制御シンポジウム
May 2008

柔軟構造を有する人工衛星ＡＳＴＲＯ－Ｇの高精度姿勢変更のための制御手法
中邨勉; 坂東信尚; 坂井真一郎; 長塩知之; 木田隆; 葛西時雄; 山口功; 大谷崇; 斎藤宏文
Oral presentation, Japanese, 計測自動制御学会,第25回誘導制御シンポジウム
May 2008

ＣＭＧを用いた柔軟衛星のＨ∞制御によるスイッチングマヌーバ
田中敬朗; 木田隆; 長塩知之
Oral presentation, Japanese, 日本機械学会,第16回スペースエンジニアリングコンファレンス
Jan. 2008

ハイブリッド専用ディーゼルエンジンの低温始動の解析
関和穂; 長塩知之; 木田隆; 新野典彦; 増田学; 小幡篤臣
Oral presentation, Japanese, 計測自動制御学会,第24回誘導制御シンポジウム
Oct. 2007

複数のアクチュエータを用いた大型宇宙構造物の非線形トラッキング制御
高橋幸秀; 池田裕一; 長塩知之; 木田隆; 小松敬治
Oral presentation, Japanese, 計測自動制御学会,第24回誘導制御シンポジウム
Oct. 2007

宇宙機の非線形サンプル地制御
片山朗; 長塩知之; 木田隆
Oral presentation, Japanese, 計測自動制御学会,第24回誘導制御シンポジウム
Oct. 2007

柔軟衛星のコロケーションフィードバック制御系の離散化に伴う安定解析
椋木祥吾; 木田隆; 長塩知之
Oral presentation, Japanese, 日本機械学会,第１５回スペースエンジニアリングコンファレンス
Jan. 2007

オンオフアクチュエータを用いた状態フィードバック制御系の設計
竹下祥; 木田隆; 長塩知之
Oral presentation, Japanese, 日本機械学会,第１５回スペースエンジニアリングコンファレンス
Jan. 2007

技術試験衛星VIII型の姿勢制御実験
長塩知之; 木田隆; 大谷崇; 濱田吉郎
Oral presentation, Japanese, 計測自動制御学会,第２３回誘導制御シンポジウム
Nov. 2006

不感帯を持つ制御系の安定性解析
前田達矢; 木田隆; 長塩知之
Oral presentation, Japanese, 計測自動制御学会,第６回制御部門大会
Jun. 2006

非対称な制御仕様を満たす対称なＨ∞制御器の存在条件
長塩知之; 木田隆
Oral presentation, Japanese, 計測自動制御学会,第６回制御部門大会
May 2006

軌道上で構築される大型宇宙構造物の非線形分散制御
高橋幸秀; 伊藤玲; 池田裕一; 木田隆; 長塩知之
Oral presentation, Japanese, 計測自動制御学会,第６回制御部門大会
May 2006

移動体に搭載したアンテナの指向制御
加藤剛; 楢原高行; 昆仁毅; 長塩知之; 木田隆
Oral presentation, Japanese, 日本機械学会,第１４回スペースエンジニアリングコンファレンス
Dec. 2005

対称な低次元Ｈ∞制御器を用いた技術試験衛星VIII型の姿勢制御
柴田舞子; 椋木祥吾; 長塩知之; 木田隆; 大谷崇; 濱田吉郎
Oral presentation, Japanese, 計測自動制御学会,第48回自動制御連合講演会
Nov. 2005

楕円軌道上のフォーメーションフライトのための制御設計
浅輪智; 木田隆; 長塩知之
Oral presentation, Japanese, 計測自動制御学会,第４８回自動制御連合講演会
Nov. 2005

人工衛星捕捉時の安定化非線形制御
伊藤玲; 池田裕一; 長塩知之; 木田隆
Oral presentation, Japanese, 計測自動制御学会,第２２回誘導制御シンポジウム
Oct. 2005

柔軟マルチボディシステムのモデリングと制御系設計
田口雅矢; 池田裕一; 木田隆; 長塩知之
Oral presentation, Japanese, 日本機械学会,日本機械学会2005年度年次大会
Sep. 2005

宇宙機の非線形Ｈ∞トラッキング制御
池田裕一; 木田隆; 長塩知之
Oral presentation, Japanese, 計測自動制御学会,第５回制御部門大会
May 2005

入力拘束を持つ宇宙機の制御系設計（リファレンスガバナによる方法）
玉屋悠介; 木田隆; 長塩知之
Oral presentation, Japanese, 日本機械学会第１３回スペースエンジニアリングコンファレンス
Jan. 2005

移動体に搭載したアンテナの追従制御
長塩知之; 楢原高行; 加藤剛; 木田隆
Oral presentation, Japanese, 日本機械学会第１３回スペースエンジニアリングコンファレンス
Jan. 2005

対称なＨ∞制御器のためのＬＭＩ条件とその拡張について
長塩知之; 木田隆
Oral presentation, Japanese, 計測自動制御学会第３３回制御理論シンポジウム
Nov. 2004

宇宙機の非線形分散制御とその故障衛星捕捉問題への適用
伊藤玲; 池田裕一; 青砥健一; 長塩知之; 木田隆
Oral presentation, Japanese, 計測自動制御学会第２１回誘導制御シンポジウム
Oct. 2004

大型宇宙構造物のＨ∞制御器の低次元化
柴田舞子; 長塩知之; 木田隆
Oral presentation, Japanese, 計測自動制御学会第２１回誘導制御シンポジウム
Oct. 2004

移動体の遠隔操縦システム
井上正洋; 谷川倫章; 岩崎圭亮; 窪田誠; 長塩知之; 木田隆
Oral presentation, Japanese, 計測自動制御学会第２１回誘導制御シンポジウム
Oct. 2004

On-off アクチュエータをもつシステムの制御系設計
前田達矢; 長塩知之; 木田隆
Oral presentation, Japanese, 計測自動制御学会，第４回制御部門大会
May 2004

移動体に搭載したアンテナの指向制御
長塩知之; 星野一也; 木田隆
Oral presentation, Japanese, 計測自動制御学会第４回制御部門大会
May 2004

剛体宇宙機の非線形Ｈ∞制御則の数値解法
青砥健一; 長塩知之; 木田隆
Oral presentation, Japanese, 第３２回制御理論シンポジウム
Nov. 2003

対称な制御器の設計に関する一考察
長塩知之; 木田隆
Oral presentation, Japanese, 第３２回制御理論シンポジウム
Nov. 2003

対称な制御器による非線形機械システムの制御
池田裕一; 木田隆; 長塩知之
Oral presentation, Japanese, 第３２回制御理論シンポジウム
Nov. 2003

対称な制御器による非線形機械システムの制御
池田裕一; 木田隆; 長塩知之
Oral presentation, Japanese, 第３２回制御理論シンポジウム
Nov. 2003

ディスクリプタ方程式を用いたゲインスケジューリング制御
奥田亮; 木田隆; 長塩知之
Oral presentation, Japanese, 第２０回誘導制御シンポジウム
Oct. 2003

移動体の遠隔操縦システムの試作 - 非線形性を考慮した自律制御 -
井上正洋; 榊原圭一; 青砥健一; 長塩知之; 木田隆
Oral presentation, Japanese, 第２０回誘導制御シンポジウム
Oct. 2003

宇宙機の非線形Ｈ∞制御則の数値解法
服部文周; 木田隆; 長塩知之; 青砥健一
Oral presentation, Japanese, 第２０回誘導制御シンポジウム
Oct. 2003

柔軟宇宙機の姿勢制御 - 受動性に基づく手法の拡張 -
池田裕一; 木田隆; 長塩知之
Oral presentation, Japanese, 第３回制御部門大会資料
Apr. 2003

Ｈ∞ノルムを最小化する静的出力フィードバック制御器の設計 - 分枝限定法を用いたＢＭＩ大域的最適化 -
岡野竜太郎; 木田隆; 長塩知之
Oral presentation, Japanese, 第３回制御部門大会
Apr. 2003

コロケーションを用いたセンサとアクチュエータの最適配置
宮地加根子; 木田隆; 長塩知之; 小松敬治
Oral presentation, Japanese, 第３回制御部門大会
Apr. 2003

バックステッピング法による柔軟宇宙機の姿勢と振動の制御
池田裕一; 青砥健一; 長塩知之; 木田隆
Oral presentation, Japanese, 第３１回制御理論シンポジウム
Nov. 2002

対称な制御器の最適設計に関する一考察
長塩知之; 木田隆
Oral presentation, Japanese, 第３１回制御理論シンポジウム
Nov. 2002

対称なＨ∞制御器を用いた宇宙構造物のロバスト制御
長塩知之; 木田隆
Oral presentation, Japanese, 第１１回アストロダイナミックスシンポジウム
Jul. 2002

対称性を利用した大型人工衛星のロバスト制御
山田和弘; 長塩知之; 木田隆
Oral presentation, Japanese, 第２回制御部門大会
May 2002

バックステッピング法による柔軟宇宙機の姿勢制御
池田裕一; 青砥健一; 長塩知之; 木田隆
Oral presentation, Japanese, 第２回制御部門大会
May 2002

LMIを用いたDVDFB制御器の設計とその拡張について
長塩知之; 木田隆; 山田和弘
Oral presentation, Japanese, 第30回制御理論シンポジウム
Nov. 2001

ゲインスケジュールドH∞制御による人工衛星用アンテナの指向制御
吉野薫; 長塩知之; 木田隆
Oral presentation, Japanese, 第44回自動制御連合講演会
Nov. 2001

技術試験衛星VIII型の定常姿勢制御モードにおける軌道上システム同定の検討
児子健一郎; 池田正文; 砂川圭; 井川寛隆; 葛西時雄; 山口功; 濱田吉郎; 木田隆
Oral presentation, Japanese, 第44回自動制御連合講演会
Nov. 2001

LMIを用いたDVDFB制御ゲインの最適設計
山田和弘; 木田隆; 長塩知之
Oral presentation, Japanese, 第18回誘導制御シンポジウム
Oct. 2001

GPSを用いた宇宙機のH∞制御
曽根康弘; 木田隆; 長塩知之
Oral presentation, Japanese, 第18回誘導制御シンポジウム
Oct. 2001

コンピュータグラフィックスを用いた非線形H∞制御による宇宙機の遠隔操縦
佐藤秀世; 木田隆; 長塩知之
Oral presentation, Japanese, 第18回誘導制御シンポジウム
Oct. 2001

可動クレーンを有する大型宇宙構造物の姿勢制御
富永誉也; 木田隆; 長塩知之
Oral presentation, Japanese, 宇宙科学研究所第10回アストロダイナミックスシンポジウム
Jul. 2001

伸展する宇宙構造物のゲインスケジューリング制御
李光焔; 長塩知之; 木田隆
Oral presentation, Japanese, 宇宙科学研究所第10回アストロダイナミックスシンポジウム
Jul. 2001

H∞ノルムを最小とするDVDFB制御ゲインの設計とその宇宙構造物への応用
山田和弘; 木田隆; 長塩知之
Oral presentation, Japanese, 計測自動制御学会第1回制御部門大会
May 2001

Articulated Spacecraftの制御
長塩知之; 木田隆
Oral presentation, Japanese, 第７回運動と振動の制御シンポジウム
Apr. 2001

技術試験衛星VIII型による軌道上柔軟構造パラメータ同定実験
児子健一郎; 砂川圭; 山口功; 葛西時雄; 井川寛隆; 木田隆
Oral presentation, Japanese, 第７回運動と振動の制御シンポジウム
Apr. 2001

２自由度回転体の制御系設計に関する一考察
長塩知之; 木田隆
Oral presentation, Japanese, 第29回制御理論シンポジウム資料
May 2000

厳密な線形化を用いた非線型H∞制御の宇宙機への応用
青砥健一; 木田 隆
Oral presentation, Japanese, 第29回制御理論シンポジウム資料
2000

非線形Ｈ∞制御の宇宙機への応用
青砥健一; 木田 隆
Oral presentation, Japanese, 第10回アストロダイナミックスシンポジウム
2000

伸展する宇宙構造物の安定化に関する一考察
岡野竜太郎; 木田 隆
Oral presentation, Japanese, 第10回アストロダイナミックスシンポジウム
2000

CMGを用いた人工衛星の非線形姿勢運動の制御
津藤健士; 木田 隆; 青砥健一
Oral presentation, Japanese, 第10回アストロダイナミックスシンポジウム
2000

技術試験衛星VIII型による軌道上システム同定の検討
山口 功; 葛西時雄; 木田 隆; 児子健一郎; 池田正文; 井川寛隆
Oral presentation, Japanese, 第44回宇宙科学技術連合講演会
2000

画像処理による宇宙構造物のシステム同定
管慎太郎; 木田 隆; 山口 功; 葛西時雄
Oral presentation, Japanese, 第17回誘導制御シンポジウム資料
2000

大型宇宙構造物の多入力多出力システムとしての同定
田中健作; 木田 隆; 山口 功; 葛西時雄
Oral presentation, Japanese, 第17回誘導制御シンポジウム資料
2000

重力傾度トルクを考慮した伸展する宇宙構造物の安定性と安定化
岡野竜太郎; 木田 隆
Oral presentation, Japanese, 第17回誘導制御シンポジウム資料
2000

CMGを用いた宇宙機の制御と特異点回避の問題
津藤健士; 木田 隆
Oral presentation, Japanese, 第17回誘導制御シンポジウム資料
2000

与えられたH∞ノルム条件を満たすDVDFB制御ゲインの設計
山田和弘; 木田 隆
Oral presentation, Japanese, 第17回誘導制御シンポジウム資料
2000

LMIを用いたパラメータ変動にある宇宙構造物のゲインスケジュールH∞制御
長塩知之; 木田 隆
Oral presentation, Japanese, 第6回運動と振動の制御シンポジウム講演論文集，千葉大学
1999

大型宇宙構造物の局所制御系設計
竹村紀章; 木田 隆; 小松敬治
Oral presentation, Japanese, Proc. of 9th Astrodynamics Symposium
1999

パラメータ変動のある人工衛星のロバスト制御系設計
長塩知之; 木田 隆
Oral presentation, Japanese, 第28回制御理論シンポジウム資料
1999

厳密な線形化による宇宙ロボットの制御（故障衛星の捕獲問題への適用）
山本和孝; 木田 隆; 山口 功
Oral presentation, Japanese, 日本機械学会年次大会
1999

LTI及びLPVモデルを用いた人工衛星の姿勢制御系設計
長塩知之; 木田 隆
Oral presentation, Japanese, 日本機械学会年次大会
1999

部分構造モデルを用いた宇宙構造物の制御系設計
竹村紀章; 木田 隆; 小松敬治
Oral presentation, Japanese, 第16回誘導制御シンポジウム資料
1999

厳密な線形化による宇宙機の追従制御（ドッキング時の操縦支援システムへの応用について）
山本和孝; 木田 隆; 山口 功; 岡本 修
Oral presentation, Japanese, 計測自動制御学会，第16回誘導制御シンポジウム資料
1999

月面における飛行移動と数理計画法による飛行経路最適化について
岡田史弘; 木田 隆; 山口 功; 佐々修一; 川勝康弘
Oral presentation, Japanese, 計測自動制御学会，第16回誘導制御シンポジウム資料
1999

月着陸機の月面飛行移動の最適制御
岡田史弘; 木田 隆; 山口 功; 佐々修一; 川勝康弘
Oral presentation, Japanese, 第42回自動制御連合講演会講演前刷集
1999

相対姿勢表現を用いた軌道上作業機の6自由度運動の線形化による制御
望月俊宏; 山口 功; 木田 隆
Oral presentation, English, Proc. of 8th Workshop on Astrodynamics and Flight Mechanics, Institute of Space and Astronautical Science, Kanagawa
1998

軌道上で構築される大型宇宙構造物の分散制御
望月一憲; 木田 隆; 小松敬治; 山口 功
Oral presentation, Japanese, Proc. of 8th Workshop on Astrodynamics and Flight Mechanics, Institute of Space and Astronautical Science, Kanagawa
1998

柔軟構造物の波動制御に関する研究-DOFB制御とH∞ロバスト制御
松本慶吾; 木田 隆; 小松敬治
Oral presentation, Japanese, Proc. of 8th Workshop on Astrodynamics and Flight Mechanics, Institute of Space and Astronautical Science, Kanagawa,
1998

軌道上作業衛星による故障衛星への接近・捕獲のためのパラメータ推定と制御
望月俊宏; 山口 功; 佐々修一; 木田 隆
Oral presentation, Japanese, 計測自動制御学会，第15回誘導制御シンポジウム資料
1998

軌道上で構築される大型宇宙構造物の分散制御
望月一憲; 木田 隆; 小松敬治; 山口 功
Oral presentation, Japanese, 計測自動制御学会，第15回誘導制御シンポジウム資料
1998

柔軟構造物の波動伝搬の遮断に関する研究
松本慶吾; 木田 隆; 小松敬治
Oral presentation, Japanese, 計測自動制御学会，第15回誘導制御シンポジウム資料
1998

BMIを用いたプルーフマス・アクチュエータの設計・構造系と制御系の同時設計
清水貴志; 木田 隆
Oral presentation, Japanese, 計測自動制御学会，第15回誘導制御シンポジウム資料
1998

軌道上作業衛星による故障衛星への接近
望月俊宏; 山口 功; 木田 隆
Oral presentation, Japanese, 第41回自動制御連合講演会，大分
1998

回転する太陽電池パドルをもつ人工衛星のロバスト制御
長塩知之; 木田隆
Oral presentation, Japanese, 第5回運動と振動の制御シンポジウム講演論文集
Nov. 1997

パラメータ変動のある宇宙構造物のロバスト制御
長塩知之; 木田隆
Oral presentation, Japanese, 第7回アストロダイナミックスシンポジウム講演集
Jul. 1997

IEEE

American Institute of Aeronautics and Astronautics

システム制御情報学会

Japan Aeronautics and Space Sciences

Japan Society of Mechanical Engineers

Society for Instrumant and Control Enginerrs