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 】

• Motion estimation of a stalled aircraft based on image processing

  SAITO YUTA, HIGUTI TAKEHIRO, UENO SEIYA, NAGASAKI FUMINAO

  Proceedings of the Japan Joint Automatic Control Conference ( The Japan Joint Automatic Control Conference )  61 ( 0 )   1708 - 1712   2018.11

  Joint Work

  DOI CiNii

• Improvement of Control Law for Flying Test Bed for Planetary Landing

  T. Naoki, T. Higuchi, S. Ueno

  Proceedings of the SICE Annual Conference 2018 ( The Society of Instrument and Control Engineers )    902 - 907   2018.09

  Joint Work

• Singularity Problem of CMGs on Multi-rotor Vehicles

  HIGUCHI Takehiro, HOSHI Takumi, UENO Seiya

  Journal of The Society of Instrument and Control Engineers ( The Society of Instrument and Control Engineers )  57 ( 4 )   260 - 265   2018.04  [Refereed]

  Joint Work

  DOI CiNii

• Optimal Trajectory of Powered Descending Phase with Coasting for Smart Lander for Investigating Moon

  HIGUCHI Takehiro, UENO Seiya, KIMURA Yuuta

  AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES ( THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES )  17 ( 0 )   55 - 60   2018.03  [Refereed]

  Joint Work

  　View Summary

  <p>This paper is on optimal trajectory of future lunar lander with coasting in powered descending phase. For the light weight/low cost lunar lander, optical navigation using onboard cameras to identify their current state is one of very few techniques available to achieve the pin-point landing. The optical navigation is to be operated between the powered descending phases, when the orbital maneuvering engine (OME) is turned off. This paper shows the series of different coasting conditions and discusses the effect of the coasting to the trajectory and fuel consumption. The results give some ideas for future gravitational planetary missions, which uses coasting during their powered descending phase. In addition, optimal trajectory with double coasting for the SLIM project is shown in this paper.</p>

  DOI CiNii

• Optimization of Lunar Landing Trajectory of Small Lunar Landing Demonstrator SLIM

  UEDA Satoshi, ITO Takahiro, HIGUCHI Takehiro, UENO Seiya, SAKAI Shinichiro

  AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES ( THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES )  17 ( 0 )   45 - 54   2018.03  [Refereed]

  Joint Work

  　View Summary

  Thanks to recent lunar exploration missions, high-resolution lunar surface observation data was obtained. In future lunar exploration, landing is being requested at a specific point having higher scientific interest than other areas. The SLIM project is demonstrating pinpoint landing technology, which entails a combination of “autonomous image-based high-precision navigation technology" and “autonomous guidance technology intended to generate a fuel-optimum landing trajectory." This paper presents powered descending trajectory design in terms of trajectory optimization. As usually considered in general space mission development, an optimal solution in terms of minimum fuel consumption is the basis of investigation. This study addresses trajectory optimization considering specific objective functions derived from practical constraints regarding mission design, such as altitude, downrange length, and visibility from ground stations. In this paper, nominal trajectory design considering minimum fuel consumption is first presented, followed by parametric studies to identify the sensitivity to changes in initial conditions under which powered descending starts. Finally, trajectory optimization results with various types of objective functions are presented.

  DOI CiNii

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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