Research Career 【 display / non-display 】

Research Career 【 display / non-display 】

• Optimal control of aircrafts

  Project Year：  -   

• Attitude control of satellites

  Project Year：  -   

• Optimal guidance and control of manipulators

  Project Year：  -   

• Optimum trajectory design for planetary explorer

  Project Year：  -   

Papers 【 display / non-display 】

Papers 【 display / non-display 】

• Control Law of Target Tracking for Multiple Autonomous UAVs Using Virtual Forces

  KATA Hiroaki, UENO Seiya

  Transactions of the Society of Instrument and Control Engineers ( The Society of Instrument and Control Engineers )  55 ( 3 )   189 - 196   2019

  Joint Work

  　View Summary

  <p>Position control law for multiple unmanned aerial vehicles (UAVs) to monitor a moving target using virtual forces is proposed. A monitoring image of the target that acquired by a nearby UAV is sent to base through the UAVs network. Each UAV forms a communication network and calculates own moving amount with a virtual forces using only information in local area. Numerical simulations show that the proposed control law is valid.</p>

  DOI CiNii

• Control Technology Used in Aerospace

  UENO Seiya, ICHIKAWA Tsutomu

  Journal of The Society of Instrument and Control Engineers ( The Society of Instrument and Control Engineers )  57 ( 4 )   212 - 213   2018

  Joint Work

  DOI CiNii

• 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

  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

  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

  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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Review Papers 【 display / non-display 】

Review Papers 【 display / non-display 】

• Reliability of Control System in Aerospace Field

    30 ( 5 ) 386 - 391   2008.07

  Introduction and explanation (scientific journal)   Single Work

Preferred joint research theme 【 display / non-display 】

Preferred joint research theme 【 display / non-display 】