Kyushu University Academic Staff Educational and Research Activities Database
List of Presentations
Shin-Ichiro Higashino Last modified date:2024.03.26

Professor / Flight Dynamics Lab. / Department of Aeronautics and Astronautics / Faculty of Engineering

1. Yasutaka Kawamoto, Yota Iwatsuki, and Shin-Ichiro Higashino, Study on the Cause of Air Traffic Delay in Fukuoka Approach Control Area Using CARATS Open Data, Asia-Pacific International Symposium on Aerospace Technology 2023 (APISAT2023), 2023.10.
2. Yota Iwatsuki, Yasutaka Kawamoto, and Shin-Ichiro Higashino, Generation of Optimized Trajectories for Congestion Mitigation in Fukuoka Approach Control Area Using Deep Reinforcement Learning, Asia-Pacific International Symposium on Aerospace Technology 2023 (APISAT2023), 2023.10.
3. Masanao TOGUCHI, Iori MIMASAKA, and Shin-Ichiro HIGASHINO, The Development of a Flight Simulator for Automatic Vertical Landing of a UAV Using a Flat Spin, APISAT2022, 2022.10.
4. Masahiko Hayashi, Shin-Ichiro Higashino, Naohiko Hirasawa, Keiichi Ozuka, Establishment of Unmanned aerial vehicle systems for Earth system sciences in the polar region, Polar Science Symposium, 2019.12.
5. Shin-Ichiro Higashino, Kota Nakama, Vertical landing of a fixed-wing UAV using the flat spin, 31st Congress of the International Council of the Aeronautical Sciences, ICAS 2018, 2018.09, This paper studies a feasibility of a novel landing method especially in a limited space for an ordinary Unmanned Aerial Vehicle (UAV) using the flat spin. Use of the combination of an all-flying tail with large deflection angle has been found effective for quick intentional flat spin entry, and the higher propeller rotational speed as well as the high all-flying tail deflection angle has been also found effective for flatter or even positive pitch attitude during the spin. One of the key issues to realize flat-spin landing is to control its descent path toward the desired landing point. The influences of change in pitch attitude on the descent path are examined in flight tests, and the periodic pitch attitude change caused by the deflection of the all-flying tail with full throttle was found effective for the descent path control..
6. Shunsuke Mori and Shi-Ichiro Higashino, The Analysis of Arrival Flow in Fukuoka Airport's Terminal Area, The 9th Kyushu University-KAIST Sympsium on Aerospace Engineering, 2017.12.
7. Hiroyuku Omagari, Shin-Ichiro Higashino, Aspiration-Point-Based Multiple Objective Path Planning Method for an Unmanned Aerial Vehicle, The 2016 Asia-Pacific International Symposium on Aerospace Technology, 2016.10.
8. Takahiro Moriyoshi, Kazuhiko Yamada, Shinichiro Higashino, Hiroyuki Nishida, Flight test results of parafoil-type vehicle with inflatable structure for the martian exploration, 15th International Space Conference of Pacific-basin Societies, ISCOPS 2018, 2018.01, One of the technologies to make the future planetary exploration more flexible and valuable is a vehicle which can fly freely in the Martian atmosphere. Our group proposes a paraglider which has a flexible and inflatable wing. The paraglider has a large and light wing which can be packed compactly in the launch and cruising phase. To realize this idea, free flight test from high altitude by the Atmospheric balloon must be carried out. However, it is difficult to succeed flight test from beginning. Therefore, we’re going to carry out a relatively simple flight test from low altitude. In this study, result of flight test was reported..
9. Kota Nakama and Shin-Ichiro Higashino, Vertical Landing Method Using the Flat Spin for a Fixed-wing UAV, APISAT2017, 2017.10.
10. Shin-Ichiro Higashino, Hiroki Omagari, Evolutionary Multi-objective Optimization Method for Drone Delivery Problem, APISAT2017, 2017.10.
11. Shin-Ichiro Higashino, The Aerosol Sample Return System in Antarctica Using a Balloon and an UAV (招待講演), 2018 KSAS GNC Symposium(招待講演), 2018.02.
12. Masahiko Hayashi, Naohiko HIrasawa, Koki Nakata, Shin-Ichiro Higashino, Aerosol Measurements in Antarctica Using “Kite Plane” in January 2017, 5th Conference of International Society for Atmospheric Research Using Remotely-Piloted Aircraft 2017, 2017.05.
13. Hiroki Omagari, Shin-Ichiro Higashino, Aspiration-point-based multi-objective path planning method for an unmanned aerial vehicle, 2016 Asia-Pacific International Symposium on Aerospace Technology, APISAT 2016, 2016.01, This research presents a new multi-objective path planning method for an unmanned aerial vehicle (UAV) using evolutionary computation. The proposed method searches for a desirable Pareto-optimal solution using an “aspiration point” and an “ideal point.” The aspiration point refers to the preference information for a decision maker (DM), and the ideal point represents a virtual solution that optimizes all objective functions simultaneously. All of the solutions generated in using evolutionary computation evolve toward the aspiration region, which is determined by the aspiration point. If a solution that is closer to the ideal point than the aspiration point is generated in the search process, the aspiration point is moved to the position of the solution point. This process is repeated until specific termination conditions are satisfied. Some results of the benchmark test problems show that the proposed method can efficiently generate the Pareto-optimal solution for the DM and a high probability compared to the existing method called the “weighted-sum method.” The usefulness of the proposed method is also shown by applying it to a multi-objective path planning problem that assumes an aerial photo-shoot mission using a UAV..
14. Shin-Ichiro Higashino, Masahiko Hayashi, Shuji Nagasaki, Shiina Umemoto, Motoki Nishimura, A Balloon-Assisted Gliding UAV for Aerosol Observation in Antarctica, The 2013 Asia-Pacific International Symposium on Aerospace Technology(APISAT-2013), 2013.11.
15. Shin-Ichiro Higashino, Masahiko Hayashi, Shuji Nagasaki, Takuya Okada, Keiichi Ozuka, Aerosol Observation and Sample-Return Using a Balloon-Assisted UAV and Results in Antarctica, 4th Conference of International Society for Atmospheric Research Using Remotely-Piloted Aircraft 2016, 2016.05.
16. Kazuhiko Yamada, Kojiro Suzuki, Takashi Abe, Daisuke Akita, Osamu Imamura, Yasunori Nagata, Yusuke Takahashi, Koju Hiraki, Shin-Ichiro Higashino, Innovative Aerodynamic Techniques using Inflatable Structure for Future Martian EDL Mission, The 2013 Asia-Pacific International Symposium on Aerospace Technology(APISAT-2013), 2013.11.
17. Shin-Ichiro Higashino, Masahiko Hayashi, Shuji Nagasaki, Takuya Okada, Keiichi Ozuka, A Balloon-Assisted Gliding UAV for Stratospheric Aerosol Observation Using Two-Stage Separation Method in Antarctica, 7th Asia-Pacific International Symposium on Aerospace Technology, 2015.11.
18. Shin-Ichiro Higashino, Minoru Funaki, Development and Flights of Ant-Plane UAVs for Aerial Filming and Geomagnetic Survey in Antarctica, 8th International Conference on Intelligent Unmanned Systems 2012, 2012.10.
19. Minoru Funaki, Shin-Ichiro Higashino, Shinya Sakanaka, The aeromagnetic survey of Deception Island, South Shetland Island, by autonomous unmanned aerial vehicle, Ant-Plane 6-3, SCAR Open Science Conference 2012, 2012.07.
20. Annop Ruangwiset, Shin-Ichiro Higashino, Development of an UAV for water surface survey using video images, 2012 IEEE/SICE International Symposium on System Integration, SII 2012, 2012, Water is an important resource especially for agricultural country like Thailand. Hydro and Agro Informatics Institute of Thailand launched a project which introduces UAVs equipped with video cameras for improvement of the efficiency in water resource survey. This paper presents the UAV system that has been developed in this project. The flight data shows the capability of accurate automatic way-point flight. Histogram-based image segmentation was applied to the aerial image for the purpose of estimation of water surface area in order to show the usefulness of the UAV system. The estimation results are evaluated and discussed..
21. Shin-Ichiro Higashino, Minoru Funaki, Naohiko Hirasawa, Masahiko Hayashi, Shuji Nagasaki, Development and Operational Experiences of UAVs for Scientific Research in Antarctica, International Conference on Intelligent Unmanned Systems 2011, 2011.11.
22. Koju Hiraki, Hidaka Yasutomo, Takashi Abe, Kazuhiko Yamada, Shin-Ichiro Higashino, Aerodynamic Advantages of Compulsively-Inflated Paraglider for Mas Exploration, the Eighth International Conference on Flow Dynamics, 2011.11.
23. Chatree Nilnumpetch, Shin-Ichiro Higashino, 3D Position Identification Using Image Processing for a Mars Exploring UAV, 第49回飛行機シンポジウム, 2011.10.
24. Katsushi Mitsutake, Shin-Ichiro Higashino, An A*-EC hybrid path planning method for waypoint traveling problem considering terrain, AIAA Guidance, Navigation and Control Conference and Exhibit, 2008, This paper proposes an A* algorithm - EC hybrid path planning method which can find out a suboptimal path quickly for a waypoint traveling problem with terrain and obstacles. In this method, A * algorithm searches optimal legs between all two waypoints while avoiding terrain and obstacles, and Evolutionary Computation (EC) tries to combine these legs into an optimal path. The authors apply this method to 30 waypoint traveling problem with terrain and 3 obstacles, and the simulation results show that calculation time is less than 6 seconds on average. Furthermore, we have confirmed that we can use this method in real time by using the real time simulator with the on-board computer for path planning which is planned to be used for flight testing..
25. Shin-Ichiro Higashino, Minoru Funaki, Naohiko Hirasawa, Development of Ant-Plane UAVs for observation and scientific missions in Antarctica, 2007 AIAA InfoTech at Aerospace Conference, 2007, A small low-cost UAV named "Ant-Plane UAV" has developed. It is intended to be used in Antarctica mainly for preliminary route investigation for ground expedition by taking aerial photographs or movies. The UAV system is required to be operated by nonspecialists in low temperature environment down to -20 degrees Celsius. It is also required to carry camera system and to fly more than 100km for route investigation. Development of the hardware and software of an autonomous flight control module and ground station software are emphasized, while off-the-shelf products which meet temperature requirement are used as much as possible for most of the parts to keep the development cost low. This paper shows details of the Ant-Plane UAV and the results of the preliminary demonstration flights in Japan..
26. Dynamic Wind Tunnel Testing for the Small-Sized Aerial Vehicles.
27. Shuji Nagasaki, Shin-Ichiro Higashino, Akira Sakurai, Automatic generation of UAV configuration by using Evolutionary Algorithm, InfoTech at Aerospace: Advancing Contemporary Aerospace Technologies and Their Integration, 2005, This paper presents an automatic design method of UAV configurations using EA (Evolutionary Algorithm). Aerodynamic configuration as well as the design variables which include the parameters necessary for sizing are optimized. In automatic generation of configuration, the four principal components are defined and the combination of them are randomly selected. The design variables are optimized evaluating an objective function which reflects design requirements and the limits. Some examples show that the possibility to design a unique UAV which cannot be designed easily by human designers..
28. Shin-Ichiro Higashino, Jeong Ho Kim, Satoshi Kuroyanagi, Akira Sakurai, Hierarchical flight management and control of autonomous UAVs based on evolutionary coumputation and total energy concept, Collection of Technical Papers - AIAA 3rd "Unmanned-Unlimited" Technical Conference, Workshop, and Exhibit, 2004.12, This paper presents a hierarchical flight management and control system for UAVs. The system composed of three layers, i.e. command interpreter layer, path planner layer, and auto-pilot layer. Path planner layer which plans a UAV's path before flight and during flight is focussed in this paper, and it is done in two steps. Macroscopic path planning is done using evolutionary computation, and microscopic planning is done applying total energy concetp especially in terminal phase and emergency landing. In the former, waypoints are directly determined by evolutionary computaion featuring unified way of handling static and dynamic obstacles, and insertion and deletion of the waypoins. In the latter, microscopic path is determined based on total energy concept which is the sum of the potential and kinetic energy, and remaining fuel as energy. Some example off-line calclation results applying these concepts are also presented..
29. Jeong Ho Kim, Norifumi Ikeda, Daisuke Morita, Tomohiro Narumi, Shin-Ichiro Higashino, Akira Sakurai, Development of the distributed onboard system for UAVs, Collection of Technical Papers - AIAA 3rd "Unmanned-Unlimited" Technical Conference, Workshop, and Exhibit, 2004.12, A new avionic system for research UAVs has been developed. It incorporates a hierarchical distributed system in which miniature modules each with a Hitachi H8 single-chip computer are connected by the CAN bus. It was found that such a system is uniquely suitable for research UAVs which are limited in weight, size, and budget. Also a new method of attitude estimation has been proposed. In this method, the attitude data from miniature angular-rate sensors which are accurate in high frequency domain and those from alternative information such as the magnetic azimuth or gravitational acceleration which are accurate in low frequency domain are combined by a specially designed filter (HL filter)..
30. Koji Fukami, Shin-Ichiro Higashino, Akira Sakurai, Dynamic wind-tunnel testing using captive flight method, Collection of Technical Papers - AIAA Atmospheric Flight Mechanics Conference, 2004, This paper presents the concept of dynamic wind tunnel testing using captive flight method, in which the airplane is supported by three elastic lines mainly in the vertical direction, and given oscillatory motions by an external actuator. This experimental method is designed for the aerodynamic parameter estimation. All of the captive flight modes are second-order systems. Longitudinal and lateral dynamic tests are carried out sweeping driving frequency, and every mode except surging motion, of which damping is weak, was excited. This experiment method has the advantages of the experimental simplicity, quite small aerodynamic interference, stable flight and the capability of excitation of motion necessary for the estimation..
31. Shin-Ichiro Higashino, Akira Sakurai, A UAV flight-experiment system for the estimation of aerodynamic characteristics, 2nd AIAA "Unmanned Unlimited" Conference and Workshop and Exhibit 2003, 2003, A flight-experiment system including the test-bed vehicle, the ground station, and the catapult has been developed at Kyushu University, the purpose of which is to estimate aerodynamic characteristics of airplanes from flight data. Most of the sensors onboard are inexpensive and off-the-shelf ones in order to maintain the cost as low as possible, while the outputs of the sensors are carefully calibrated to assure data acquisition with high accuracy. The strong correlation among the variables which describes the change in a dependent aerodynamic variable is known as multicolinearity in regression analysis, which degrades the estimation accuracy. It is shown that this multicolinearity, which usually occurs among longitudinal variables due to elevator deflection is avoidable using an additional tail surface named a Flying Sting Balance..
32. Uy Loi Ly, Shin-Ichiro Higashino, Development of a UAV flight-test vehicle at the University of Washington, 2nd AIAA "Unmanned Unlimited" Conference and Workshop and Exhibit 2003, 2003, Development of UAV technologies has been the focus of many advanced programs in both military and commercial applications. This paper describes the UAV development plan at the University of Washington and its implementation. A method for extracting aerodynamic stability derivatives from flight-test data is presented. Estimates of lift coefficient derivatives compare well with those obtained in wind-tunnel tests. Future improvements envisionned for the flight-test vehicle and potential follow-on UAV projects are presented..
33. The Flying Sting Balance : A Novel Method of Flight Testing.
34. Shin-Ichiro Higashino, Masayoshi Okuda, Shuji Nagasaki, Akira Sakurai, Estimation of the Aerodynamic Characteristics of an RPRV by Flight Tests Using an Additional Tail Surface, the Asian-Pacific Conference on Aerospace Technology and Science 1997, 1997.10.
35. Akira Sakurai, Shin-Ichiro Higashino, The Analysis of the Aerodynamic Characteristics Using an RPRV Flight Experiment Data, the Asian-Pacific Conference on Aerospace Technology and Science 1994, 1994.11.
36. Toshiyuki Itoko, Shin-Ichiro Higashino, Yoshio Yamagami, Tetsuro Ikebuchi, The Development of an Automatic Control System for a Submerged Hull and Foil Fybrid Super-High-Speed Liner, FAST'91, 1991.06.