Research Career 【 display / non-display 】

Research Career 【 display / non-display 】

• Periodic Optiomal Controller for Multi-Joint Space structure

  Project Year：  -   

• Attitude Control of Satellites using CMGs

  Project Year：  -   

• Automatic Flight Control of Indoor UAVs

  The Other Research Programs  

  Project Year：  -   

• Automatic Flight Control of UAVs

  Grant-in-Aid for Scientific Research  

  Project Year：  -   

• Controller Design for Super Multi-Joint Space structure

  Project Year：  -   

Books 【 display / non-display 】

Books 【 display / non-display 】

• Advances in the Astronautical Sciences：Applications of Space Technology for Humanity

  上野誠也 (Part： Joint Work )

  Univelt Inc.  2012.12

• Numerical Analysis Theory and Application

  J. Awrejcewicz, et. al. (Part： Joint Work )

  InTech  2011.07 ISBN: 9789533073897

• Ａdvances in the Astronautical Sciences：Space Activities and Cooperation Contributing to All Pacific Basin Countries

  上野誠也 (Part： Joint Work )

  Univelt Inc.  2010.12

Papers 【 display / non-display 】

Papers 【 display / non-display 】

• Semi-Optimal Control Using Shooting Method for Real Time Minimum-Time Maneuver of Satellite with VSCMG

  Tsuchiya Mitsuyoshi, Higuchi Takehiro

  AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES ( THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES )  20 ( 0 )   9 - 18   2021.04

  Joint Work

  　View Summary

  <p>This study explores the minimum-time attitude maneuver of satellites using Control Moment Gyros (CMG). The CMG system is able to generate high torque and run for longer term than other actuators. However, it is known that the singular input that cannot generate effective torque appears in the optimal control for the minimum-time maneuver of a rigid spacecraft with a pyramid type SGCMG system. In previous studies, a new system equipped with variable speed CMG (VSCMG) to the CMG where the singular input appeared has been proposed. It is shown that the new system can rotate faster than the normal pyramid type SGCMG system in the simulation based on the optimal control law. However, for applications in actual satellites, numerical optimization cannot be used due to the high calculation cost. The objective of this study is to make the new semi-optimal control law for the minimum time attitude maneuver of the satellite equipped with the VSCMG. The new control law is designed using a rule-based feedforward control combined with feedback control. The result by numerical simulation has shown that the proposed control law enables the satellite to achieve faster maneuver without iterative calculations. </p>

  DOI CiNii

• Semi-Optimal Control for Minimum-Time Maneuver of Satellite with Variable Speed Pyramid Type SGCMGs

  TSUCHIYA Mitsuyoshi, HIGUCHI Takehiro

  TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN ( 一般社団法人 日本航空宇宙学会 )  19 ( 1 )   24 - 33   2021.01

  Joint Work

  　View Summary

  <p>This study explores the minimum-time attitude maneuver of satellites using Control Moment Gyros (CMG). The CMG system is able to generate high torque and run for longer term than other actuators. However, it is known that the singular input that cannot generate effective torque appears in the optimal control for the minimum-time maneuver of a rigid spacecraft with a pyramid type SGCMG system. In previous studies, a new system equipped with variable speed CMG (VSCMG) to the CMG where the singular input appeared has been proposed. It is shown that the new system can rotate faster than the normal pyramid type SGCMG system in the simulation based on the optimal control law. However, for applications in actual satellites, numerical optimization cannot be used due to the high calculation cost. The objective of this study is to make the new semi-optimal control law for the minimum time attitude maneuver of the satellite equipped with the SGCMG with the variable speed wheel. The new control law is designed using a rule-based feedforward control combined with feedback control. The result by numerical simulation has shown that the proposed control law enables the satellite to achieve faster maneuver without any initial assumptions.</p>

  DOI CiNii

• Synchronizing Motion Control for Tumbling Space Debris Using Robotic Arm

  Takehiro Higuchi, Tomoaki Fujihara

  Proceedings of SICE 2020     2020.09

  Joint Work

• Development of Towed-Type Multi-rotor With Fixed Stabilizers

  Daichi AOKI, Takehiro HIGUCHI, Seiya UENO

  Proceedings of 11th Asia-Pacific International Symposium on Aerospace Technology (APISAT)     2019.12

  Joint Work

• Minimum-Time Maneuver of Satellite with VS-Pyramid Type SGCMGs

  Mitsuyoshi Tsuchiya, Kohei Oikawa, Takehiro Higuchi

  Proceedings of 11th Asia-Pacific International Symposium on Aerospace Technolog     2019.12

  Joint Work

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Academic Awards Received 【 display / non-display 】

Academic Awards Received 【 display / non-display 】

• SICE-ICASE International Joint Conference 2006 Young Author Award

  2006.10    

• ISTS Student Session JSASS President Award

  2002    

Grant-in-Aid for Scientific Research 【 display / non-display 】

Grant-in-Aid for Scientific Research 【 display / non-display 】

• Developement of High Torque Pyramid Type Micro VS-CMG Applying Singular Input

  Grant-in-Aid for Scientific Research(C)

  Project Year： 2020.04  -    Investigator(s): Takehiro Higuchi

• Experiment on Control Conflict of Avoidance Manuvoer of Small UAV

  Grant-in-Aid for Young Scientists(B)

  Project Year： 2007.04  -  2009.03