九州大学-研究者情報 [吉村康広 (助教) 工学研究院航空宇宙工学部門]

吉村康広（よしむらやすひろ）

データ更新日：2024.04.26

助教　／　工学研究院航空宇宙工学部門

原著論文

1.	Isobe, S., Yoshimura, Y., Handa, T., Itaya, Y., Fukushima, T., Adaptive Relative Orbit Control Considering Laser Ablation Uncertainty, Journal of Space Safety Engineering, 2024.04.
2.	Matsushita, Y., Yoshimura, Y., Nagasaki, S., Hanada, T., Conceptual Study of Improved Photometric Attitude Estimation Using Glint, Aerospace Technology Japan, 2024.05.
3.	Tanahashi, M., Chen, H., Yoshimura, Y., Hanada, T., Origin Identification of Sub-millimeter-sized Debris from In-situ Debris Measurements, Acta Astronautica, Vol. 215 449–454., 2024.02.
4.	Nakajima, Kenta,Yoshimura, Yasuhiro, Chen, Hongru, Hanada, Toshiya, How are multiple satellites seen from the ground?: Relative apparent motion and formation stabilization, Astrodynamics, 8, 1, 2024.01, This paper solves how multiple satellites are seen from the ground. This question is derived by a space- advertising, a public mission in the night sky with a dot matrix of satellites which are bright enough to see in the naked eye. Thus, it is important for space advertisement that the dot matrix is seen as expected. Moreover, the stable dot matrix during a visible span is more valuable. This study relatively formulates an apparent position of a dot from a representative dot seen from the ground to stabilize the dot matrix. The formulation is linear functions of a set of relative orbital elements and reveals the appearance of the dot matrix. A proposed relative variable in the formulation drives the instability of the dot matrix, discovering an initial stable configuration of deputies from a chief. The arbitrary dot matrix designed by the configuration is stable even at low elevations without orbital control during the visible span..
5.	Yoshimura, Yasuhiro, Matsushita, Yuri, Takahashi, Kazunobu, Nagasaki, Shuji, Hanada, Toshiya, Analytic Approximation of High-Fidelity Solar Radiation Pressure, Journal of Guidance, Control, and Dynamics, 10.2514/1.G005961, 2023.01, This paper considers high-fidelity solar radiation pressure that is modeled with a detailed reflection model. The Cook-Torrance model is used to represent the isotropic reflection. Using the spherical Gaussian distribution, the analytical approximation method of the solar radiation pressure is derived..
6.	Sakai Daisuke, Yoshimura Yasuhiro, Hanada Toshiya, Itaya Yuki, Fukushima Tadanori, Contactless Attitude Control of an Uncooperative Satellite by Laser Ablation, Acta Astronautica, 2022.06.
7.	Shuta Fukii, Daisuke Sakai, Yasuhiro Yoshimura, Yuri Matsushita, Toshiya Hanada, Yuki Itaya, Tadanori Fukushima, Assessing Collision Probability in Low-Thrust Deorbit, Journal of Space Safety Engineering, 10.1016/j.jsse.2021.11.002, 9, 1, 47-55, 2022.03, End-of-life support of satellites is necessary to improve post-mission-disposal compliance rates for maintaining space environment. Deorbit mission with low thrust, e.g. a laser, induces a low-level deceleration on the target object that gradually lowers the target altitude. Since such a low-thrust trajectory is time-consuming, the risk of collision greatly influences the mission success rate. In this context, this paper assesses the collision risk during deorbit trajectories with low thrust. Furthermore, parametric studies for the relationship between the re-entry time and the risk of collision are performed..
8.	Aditya Baraskar, Yasuhiro Yoshimura, Shuji Nagasaki, Toshiya Hanada, Space solar power satellite for the Moon and Mars mission, Journal of Space Safety Engineering, 10.1016/j.jsse.2021.10.008, 9, 1, 96-105, 2022.03, This paper presents an overview of space solar power satellites for the Moon and Mars mission and simultaneously demonstrates the compression of traditional power generation methods for the orbiter, lander, and habitat on Mars and the Moon. Interplanetary missions are where the space engineers work on the satellites, conceptual design of space habitat, and exploration system. The state of the art in those missions relies on radioisotope thermoelectric generators or solar panels attached with batteries to store power, both of which are plagued by limitations. For instance, when a spacecraft moves away from the Sun, the energy collection efficiency on the solar panel is reduced, and at temperatures below -100°Celsius, individual solar cells degrade unpredictably, deteriorating the performance of solar arrays. Furthermore, these power generation unit satellites carry a pack of batteries to store energy whose total system accounts for more than 10-25 % of the mass of the satellites. In an interplanetary mission, power generation and management are essential for research and investigation on the surface. For Mars, sandstorms affect the collection of energy at the attached solar panel to the rover. Moreover, the rovers must investigate at the far side of the Moon, where sunlight is unavailable for few consecutive days. This challenge can be suitably overcome by employing space solar power satellites, which can be used for wireless power transmission, independent of its location. Such techniques have possible applications towards power transmission for unmanned aerial vehicles for faster mapping purposes. As such, the dependence of those aerial vehicles towards fixed energy storage becomes alleviated. In hindsight, space solar power satellite serves as a potential for an improved energy transmission source than the traditional method for interplanetary rovers and habitat..
9.	Hanada Toshiya, Fujita Koki, Yoshimura, Yasuhiro, Estimation of Orbital Parameters of Broken-up Objects from In-situ Debris Measurements, Frontiers in Space Technologies, 2022.03.
10.	Kota Sato, Yasuhiro Yoshimura, Toshiya Hanada, Taku Izumiyama, Ryu Shinohara, The collision avoidance strategy for geostationary satellites considering orbit maintenance, Journal of Space Safety Engineering, 10.1016/j.jsse.2021.08.004, 8, 4, 331-338, 2021.12, This study aims to develop an effective strategy for geostationary satellites to avoid collisions with space debris satisfying various operational constraints. Recently, the number of space objects is continuously increasing to threaten operational satellites in the geostationary region. Studies on collision avoidance have been advanced for a long time, but not sufficiently considered orbit maintenance after maneuvering. Not to shorten satellite lifetime by collision avoidance, it is necessary to consider orbit maintenance after maneuvering. Besides, orbit maintenance regularly conducted differs between chemical thruster and electric thruster, so that two different avoidance strategies may be required. This study adopts a Multi-objective Genetic Algorithm to find out an optimal strategy for each thruster under various constraints on the operation. This paper also demonstrates that the optimal collision avoidance maneuvering can achieve both collision avoidance and orbit maintenance with less fuel than regular orbit control..
11.	Matsushita Yuri, Yoshimura, Yasuhiro, Hanada Toshiya, Itaya, Yuki, Fukushima, Tadanori, Risk Assessment of Large Constellation of Satellites in Low Earth Orbit, Aerospace Technology Japan, 2021.10.
12.	Baraskar Aditya Chen Hongru Yoshimura Yasuhiro Nagasaki Shuji Hanada Toshiya , Verify the Wireless Power Transmission in Space using Satellite to Satellite System, International Journal of Emerging Technologies, 12, 2, 110-118, 2021.08.
13.	Kota Kondo, Ilya Kolmanovsky, Yasuhiro Yoshimura, Mai Bando, Shuji Nagasaki, Toshiya Hanada, Nonlinear Model Predictive Detumbling of Small Satellites with a Single-axis Magnetorquer, Journal of Guidance, Control, and Dynamics, 10.2514/1.G005877, 44, 6, 1211-1218, 2021.06.
14.	Furumoto, M., Yoshimura, Y., and Hanada, T., Improvement in an Estimation Method of the Debris Environment Utilizing In-situ Measurements, Transactions of the Japan Society for Aeronautical and Space Sciences, 2020.10.
15.	Yasuhiro Yoshimura, Yuri Matsushita, Ryohei Arakawa, Toshiya Hanada, Light Curve Approximation Using an Attitude Model of Solar Sail Spacecraft, Journal of Guidance, Control, and Dynamics, 10.2514/1.G004966, 43, 10, 1960-1966, 2020.07, Light curves are formulated using bidirectional reflectance distribution functions (BRDFs), which describe the ratio of light intensity between irradiance and radiance. The simplest BRDF is parameterized with Lambertian diffusion and perfect specular reflection. This model has been widely used in research on light curves as well as solar radiation pressure (SRP) modeling. SRP and its torque are one of main disturbances that contribute to spacecraft translational and rotational motion, which are also formulated with BRDFs..
16.	Yutaka Kodama, Masahiro Furumoto, Yasuhiro Yoshimura, Koki Fujita, Toshiya Hanada, Estimation of orbital parameters of broken-up objects from in-situ debris measurements, Advances in Space Research, 10.1016/j.asr.2018.07.034, 63, 1, 394-403, 2019.01, [URL], © 2018 COSPAR Even sub-millimeter-size debris could cause a fatal damage on a spacecraft. Such tiny debris cannot be followed up or tracked from the ground. Therefore, Kyushu University has initiated IDEA the project for In-situ Debris Environmental Awareness, which conducts in-situ measurements of sub-millimeter-size debris. One of the objectives is to estimate the location of on-orbit satellite fragmentations from in-situ measurements. The previous studies revealed that it is important to find out the right nodal precession rate to estimate the orbital parameters of a broken-up object properly. Therefore, this study derives a constraint equation that applies to the nodal precession rate of the broken-up object. This study also establishes an effective procedure to estimate properly the orbital parameters of a broken-up object with the constraint equation..
17.	Yasuhiro Yoshimura, Optimal formation reconfiguration of satellites under attitude constraints using only thrusters, Aerospace Science and Technology, 10.1016/j.ast.2018.03.021, 77, 449-457, 2018.06, [URL], An optimal formation reconfiguration method under the constraints of a satellite attitude with respect to an inertial frame is addressed. Both the satellite position and attitude are controlled by only two body-fixed thrusters for an in-plane maneuver. To tackle the underactuated control problem, an attitude controller for tracking reference accelerations is firstly derived on the basis of Lyapunov approach. This controller allows us to consider the attitude constraints as input directional constraints because the satellite attitude is controlled so that the thrust direction is coincide with the force direction required for the orbit transfer. Secondly, a formation reconfiguration method based on the Fourier series is used as the reference inputs, and boundary conditions that make the resulting input trajectory an ellipse are shown. Such elliptic input trajectory changes the input direction monotonically, which enables bounding it around an desired direction. The proposed underactuated-controller achieves a reconfiguration maneuver while keeping the satellite attitude within a range from a specified direction, and thus is useful when several thrusters of a satellite fail due to malfunctions. Finally, numerical simulation results validate the effectiveness of the proposed relocation method by comparing energy consumptions and bounded satellite attitude angles..
18.	Yasuhiro Yoshimura, Hirohisa Kojima, Optimization of fault-tolerant thruster configurations for satellite control, Advances in Space Research, 10.1016/j.asr.2018.01.014, 61, 6, 1617-1625, 2018.03, [URL], The fault tolerance of spacecraft actuators significantly affects the reliability of satellites and the likelihood of successful missions. To enhance the fault tolerance of the actuators, this study derives optimal fault-tolerant configurations of fixed thrusters that maximize the controllability of a fully-actuated or underactuated satellite. The proposed method optimizes thrust and torque directions generated by the thrusters. Thus a cost function in terms of the thruster locations and directions is defined as the summation of the generated control forces and torques with respect to the body-fixed frame. The optimal configuration is obtained by the successive use of an energy potential method that is motivated by Thomson's problem. Some numerical examples are provided that show the effectiveness of the proposed formulation and optimization method..
19.	Hirohisa Kojima, Kana Hiraiwa, Yasuhiro Yoshimura, Experimental study on line-of-sight (LOS) attitude control using control moment gyros under micro-gravity environment, Acta Astronautica, 10.1016/j.actaastro.2017.11.020, 143, 118-125, 2018.02, [URL], This paper presents the results of line-of-sight (LOS) attitude control using control moment gyros under a micro-gravity environment generated by parabolic flight. The W-Z parameters are used to describe the spacecraft attitude. In order to stabilize the current LOS to the target LOS, backstepping-based feedback control is considered using the W-Z parameters. Numerical simulations and experiments under a micro-gravity environment are carried out, and their results are compared in order to validate the proposed control methods..
20.	Takashi Matsuno, Yasuhiro Yoshimura, Shinji Hokamoto, Consideration of three-dimensional attitude and position control for a free-floating rigid body using three thrusters, International Journal of Aerospace Engineering, 10.1155/2018/2825681, 2018, 2018.01, [URL], The study examines the control algorithm of a three-dimensional attitude and position of a free-floating rigid body with three thruster forces in which the force directions are fixed with respect to the body. This study provides a theory to develop a control method of an underactuated satellite with the minimum thruster number. In the procedure, three switching controllers are used in conjunction with motion planning in the final angular-rate deceleration phase to individually control the six state variables to the target values. The switching controllers have a hierarchical structure by using invariant manifolds as switching surfaces. The state variables in higher class manifolds that include lower class ones are adjusted by repeatedly adding intentional disturbances while the lower class state variables are returned to the original values by using lower class invariant manifolds. This study describes methods to define the invariant manifolds and also the intentional disturbance for achieving the forementioned control strategy. Finally, the motion planning in the angular-rate deceleration phase from a remained single-axis rotation finalizes the six state values of the body to the target values. Numerical simulations verify the proposed method..
21.	Kojima, H, Trivailo, P.M, Yoshimura, Y, Spacecraft Line of Sight Maneuver Control Using Skew-arrayed Two Single-Gimbal Control Moment Gyros, Transactions of JSASS, Aerospace Technology Japan, 10.2322/tastj.14.Pd_31, 14, ists30, Pd_31-Pd_37, 2016.09.
22.	Yasuhiro Yoshimura, Takashi Matsuno, Shinji Hokamoto, Global trajectory design for position and attitude control of an underactuated satellite, Transactions of the Japan Society for Aeronautical and Space Sciences, 10.2322/tjsass.59.107, 59, 3, 107-114, 2016.01, [URL], Underactuated control offers fault-tolerance for satellite systems, which not only enables the position and attitude control of a satellite with fewer thrusters, but also can reduce the number of thrusters equipped on the satellite even when considering the need for backups. Due to having fewer thrusters, the coupling effect between the translational motion and rotational motion of the satellite cannot be avoided, and the coupled motion must be considered in control procedures. This paper presents a global trajectory design procedure required for the position and attitude control of an underactuated satellite. The satellite has four thrusters with constant thrust magnitudes on one plane of the satellite body. Then, an analytical solution for coupled motion between the rotation and translation of the satellite is obtained using three-step maneuvers of attitude control. The trajectory design based on the analytical solution is shown for the control of translational and rotational motion in three dimensions. Finally, a numerical simulation is performed to verify the effectiveness of the proposed design procedure..
23.	Yasuhiro Yoshimura, Optimal Fault-Tolerant Configurations of Control Moment Gyros, JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 10.2514/1.G001249, 38, 12, 2460-2466, 2015.12, [URL], an optimization method for fault-tolerant control moment gyros (CMG) configurations, which maximizes the angular momentum envelope of the CMGs even after a portion of CMGs has failed. To incorporate weighting according to the number of available CMGs, the optimization problem is formulated as a min?max problem and reduced to Thomson's problem under appropriate constraints. Using different weights enables the determination of optimal CMG configurations that take into account a maximization of the angular momentum that admits the possibility of CMG failure. Therefore, the resulting configuration is both optimal and fault tolerant, and maintains satellite attitude controllability in underactuated conditions. Furthermore, reliability-based weighting is shown as one possible criterion for determining the appropriate weights. By adding constraints to the azimuth angles of the gimbal axes, it is shown that the zero-momentum condition of CMG configurations can be satisfied using the proposed optimization method. The proposed method enables calculating various types of optimal CMG configurations without providing initial estimations..
24.	Yasuhiro Yoshimura, Suboptimal formation reconfiguration of satellites under input directional constraints, ADVANCES IN SPACE RESEARCH, 10.1016/j.asr.2015.07.037, 56, 10, 2130-2140, 2015.11, [URL], Proximity operations of satellites such as formation flying and on-orbit servicing offer more advanced missions than missions achieved by a single satellite. In a practical situation of formation flying, thrust directions for keeping and controlling a relative orbit is limited, e.g., for astronomical observation and plume impingement avoidance. The aim of this paper is to provide an energy efficient control method for a formation reconfiguration under input directional constraints with respect to both an inertial and a leader-fixed frames. The proposed controller is designed consisting of two parts: (1) guaranteeing a formation reconfiguration to a desirable formation on the basis of an energy optimal controller and (2) satisfying the input directional constraints by superimposing additional inputs. The analytical form of the control input shows that the input direction forms an ellipse in the leader-fixed frame when a particular boundary condition is satisfied, which is exploited as a nominal controller to take into account the input directional constraints. Due to the singularity avoidance of the nominal controller, the additional inputs can be analytically obtained. The effect on the follower trajectory due to the additional inputs is compensated by setting a virtual target orbit, and thus the successful formation reconfiguration is still guaranteed. Some numerical simulation results verify the effectiveness of the proposed method and compare the energy efficiency. (C) 2015 COSPAR. Published by Elsevier Ltd. All rights reserved..
25.	Takashi Matsuno, Yasuhiro Yoshimura, Shinji Hokamoto, Attitude and position control for under actuated satellite by ON/OFF thrusters, Nihon Kikai Gakkai Ronbunshu, C Hen/Transactions of the Japan Society of Mechanical Engineers, Part C, 10.1299/kikaic.79.225, 79, 798, 225-235, 2013.05, [URL], This study proposes a new control method for under-actuated planar satellites having body-fixed thrusters that can generate unilateral and constant forces. The proposed method is applicable when the thrusters are not balanced, which means a rotational motion is inevitably induced whenever the thrusters are turned on. By applying the method, the position and attitude of any planar satellite can be controlled to arbitrary target states so long as a controllability condition is satisfied. The control logic is based on a switching control using plural manifolds. First, the satellite is transferred to an initial manifold, and then it moves to another manifold while decreasing its velocity and approaching the target states. The ON/OFF timing of the thrusters to transfer among the manifolds is explicitly specified in this paper. A numerical simulation validates the proposed control logic..
26.	Yasuhiro Yoshimura, Takashi Matsuno, Shinji Hokamoto, Three dimensional attitude control of an underactuated satellite with thrusters, International Journal of Automation Technology, 10.20965/ijat.2011.p0892, 5, 6, 892-899, 2011.01, [URL], This paper deals with the three-dimensional attitude control of an underactuated satellite equipped with thrusters whose force directions are fixed to the satellite. First, the necessary number of thrusters for the satellite's attitude control is discussed utilizing the Minkowski-Farkas theorem. Then, using the wz parameters for a satellite's attitude expression, this paper proposes a non holonomic attitude controller which is effective for any satellite regardless of its moment of inertia. Numerical simulation demonstrates the effectiveness of the proposed controller. Furthermore, the efficiency of the controller for different thruster positions is also discussed..

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