Kyushu University Academic Staff Educational and Research Activities Database
List of Presentations
Yasuhiro Yoshimura Last modified date:2021.06.11

Assistant Professor / Department of Aeronautics and Astronautics / Faculty of Engineering

1. Kondo, K., Yoshimura, Y., Bando, M., Nagasaki, S., & Hanada, T., Model Predictive Approach for Detumbling an Underactuated Satellite, AIAA Scitech 2020 Forum, 2020.01.
2. Baraskar, A., et al., SPACE SOLAR POWER SATELLITE FOR INTERPLANETARY MISSION, IAC CyberSpace Edition 2020, 2020.10.
3. Masahir Furumoto, Yasuhiro Yoshimura, Toshiya Hanada, Improvement in an Estimation Method of the Debris Environment Utilizing In-situ Measurements, The 32nd International Symposium on Space Technology and Science, 2019.06.
4. Ryohei Arakawa, Yuri Matsushita, Yasuhiro Yoshimura, Toshiya Hanada, Attitude Estimation of Space Objects Using Imaging Observations and Deep Learning, The 20th Annual Advanced Maui Optical and Space Surveillance Technologies (AMOS) Conference, 2019.09.
5. Kota Kondo, Yasuhiro Yoshimura, Detumbling with Model Predictive Control for an Underactuated Small Satellite, Region VII Student Paper Conference, 2019.12.
6. Masaya Nitta, Yasuhiro Yoshimura, Toshiya Hanada, Space Debris Mitigation by Passive Debris Removal in Large Constellation, The 1st Intl Orbital Debris Conference, 2019.12.
7. Yuri Matsushita, Ryohei Arakawa, Yasuhiro Yoshimura, Toshiya Hanada, Light Curve Analysis and Attitude Estimation of Space Objects Focusing on Glint, The 1st Intl Orbital Debris Conference, 2019.12.
8. Daigo Izumizawa, Masahiro Furumoto, Yasuhiro Yoshimura, Toshiya Hanada, Generalized Collision Flux Approximation for In-situ Measurements, The 1st Intl Orbital Debris Conference, 2019.12.
9. Yasuhiro Yoshimura, Yuri Matsushita, Ryohei Arakawa, Toshiya Hanada, Combining Photometric Data Formulation with Attitude Model of a Spinning Solar Sail Spacecraft, 1st International Orbital Debris Conference, 2019.12.
10. Kota Kondo, Yasuhiro Yoshimura, Mai, Bando, Shuji Nagasaki, Toshiya, Hanada, Model Predictive Approach for Detumbling an Underactuated Satellite, AIAA SciTech 2020 Forum, 2020.01.
11. Kota Sato, Makoto Hanada, Yasuhiro Yoshimura, Toshiya Hanada, Taku Izumiyama, Ryu Shinohara, The optimal collision avoidance maneuver with multiple objects in Geo, 70th International Astronautical Congress, IAC 2019, 2019.01, This study aims to develop a new collision avoidance strategy for geostationary spacecraft. Recently, the continuous growth of space objects is increasing the collision risk among them. In the future, it will be necessary to operate the spacecraft while avoiding much space objects. However, there is a limit of fuel loading in a spacecraft, so it will be important to save fuel consuming each collision avoidance maneuvers not to shorten spacecraft lifetime rapidly. The proposed strategy considers the following points to save fuel and extend a spacecraft lifetime as much as possible. The first point is to avoid as many objects as possible at once maneuver so that the maximum collision probability is less than 1.0 × 10%&. The second point is to minimize fuel consumed by collision avoidance maneuvers and the next orbit maintenance maneuver. The last point is to maximize the period to keep a spacecraft in the station-keeping slot. To realize this strategy, multi-objective genetic algorithm optimizes maneuver time and maneuver vector. In the simulation, to simplify, a spacecraft avoids two approaching objects. The Spacecraft conducts collision avoidance maneuver as the East-West control maneuver and the North-South control maneuver, separately. As a result, in the case of once maneuver, collision avoidance is succeeded but the station-keeping period was too short, especially in the case of an East-West control maneuver. Therefore, it needs to conduct many maneuvers before the closest approach..
12. Yasuhiro Yoshimura, Magnetic Attitude Control of Satellites Using Coarse Pulse-Width-Modulation of Magnetorquers, 68th International Astronautical Congress, 2017.01, Magnetorquers enable energy efficient attitude control of microsatellites in low Earth orbits. The challenging problem for the magnetic attitude control is the limitations on their component capability, and high-frequency Pulse- Width-Modulation (PWM) actuations are difficult to implement. Moreover since the magnetorquers generate control torques into a plane orthogonal to the geomagnetic field, three-axis attitude control using only the magnetorquers is challenging. In this context, this study deals with the magnetic attitude control of satellites using only magnetorquers that are driven with coarse PWM. The coarse PWM actuations in this study mean that the magnetorquers are successively actuated by on-state and then off-state in each actuation cycle of a few seconds. The difficulties of the coarse PWM actuations stem from the followings: 1) Conventional techniques for feedback controllers are hard to be applied because the magnitude of the magnetic moment is constant. 2) The dynamics of the satellite has nonlinear terms in control torques due to coarse PWM actuations. First, the dynamics of the satellite with on-off inputs are formulated as a discrete system in order to deal with the coarse PWM actuations of the magnetorquers. Then, to tackle with the nonlinearity of the control torques, averaging method for general case is used for reducing to the problem that is dynamic quantizer is applicable. As a preliminary study, dynamic quantizer is designed for satellites in sun-synchronous orbits and is verified for the coarse input system..
13. Yasuhiro Yoshimura, Takashi Matsuno, Shinji Hokamoto, Satellite position and attitude control by on-off thrusters considering mass change, 2011 AAS/AIAA Astrodynamics Specialist Conference, ASTRODYNAMICS 2011, 2011.07, This paper deals with the two-dimensional position and attitude control of a satellite by on-off thrusters which are fixed to the satellite's body. Since the thrusters generate constant and unilateral forces, the equations of motion form nonholonomic constraint and cannot be integrated. Furthermore, the satellite's mass changes due to the fuel consumption. Utilizing Fresnel integrals and the partial integrals, we derive the approximate analytic solution considering the satellite's mass change to achieve a specified satellite's position and attitude. The accuracy of the proposed approximate technique is verified by applying it to a condition considered in SLIM project of JAXA..
14. Yasuhiro Yoshimura, Takashi Matsuno, Shinji Hokamoto, Position and attitude control of an underactuated satellite with constant thrust, AIAA Guidance, Navigation and Control Conference 2011, 2011.08, This paper discusses a position and attitude control problem of an underactuated satellite which uses on-off thruster mechanisms for control. Each thrusters has constant orientation relative to the satellite's body, and can generate only unilateral forces. The purpose of this paper is to clarify the control law for simultaneous position and attitude control for this type of satellite configuration. Considering the input constraints, we obtain the analytical solutions of the satellite's translational and rotational motion. Then the control procedure utilizing an invariant manifold is derived. Some numerical simulations are shown to verify the effectiveness of the proposed controller..
15. Yasuhiro Yoshimura, Hirohisa Kojima, Optimal Fault-Tolerant Configurations of Thrusters, The 31st International Symposium on Space Technology and Science, 2017.06.
16. Hirohisa Kojima, Kana Hiraiwa, Yasuhiro Yoshimura, Koki Hidaka, Experimental Study on Line-of-Sight (LOS) Attitude Control Using Control Moment Gyros under Micro-Gravity Environment, The 31st International Symposium on Space Technology and Science, 2017.06.
17. Yasuhiro Yoshimura, Suboptimal Formation Reconfiguration of Satellites Under Input Directional Constraints, 2014 Asia-Pacific International Symposium on Aerospace Technology, 2014.09.
18. Yasuhiro Yoshimura, Shunsuke Tsuge, Shinji Hokamoto, Relative Position and Attitude Control of a Satellite Considering Fuel Efficiency, 29th International Symposium on Space Technology and Science, 2013.06.
19. Yasuhiro Yoshimura, Shinji Hokamoto, Optimal Formation Reconfiguration of Satellites with Attitude Constraints Using Thrusters, 5th International Conference on Spacecraft Formation Flying Missions and Technologies, 2013.05.
20. Yasuhiro Yoshimura, Shinji Hokamoto, Attitude Control of an Underactuated Satellite with Constant Torques, The Sixth KAIST-Kyushu University Joint Workshop Mechanical and Aerospace Engineering, 2012.09.
21. Yasuhiro Yoshimura, Takashi Matsuno, Shinji Hokamoto, 3-D Attitude Control of an Underactuated Satellite with Constant Inputs, The 28th International Symposium on Space Technology and Science, 2010.12.
22. Yasuhiro Yoshimura, Takashi Matsuno, Shinji Hokamoto, Three Dimensional Attitude Control of an Underactuated Satellite with Thrusters, 4th Asia International Symposium on Mechatronics, 2009.12.
23. Yasuhiro Yoshimura, Shinji Hokamoto, The Minimum Necessary Number of Thrusters to Control Satellite Attitude, The 4th KAIST-Kyushu Univ. Symposium on Aerospace Engineering.