Kazuhisa CHIBA
| Department of Mechanical and Intelligent Systems Engineering | Professor |
| Cluster III (Fundamental Science and Engineering) | Professor |
Researcher Information
Field Of Study
Career
- Apr. 2019 - Present
The University of Electro-Communications, Graduate School of Informatics and Engineering, School of Informatics and Engineering Department of Mechanical and Intelligent Systems Engineering, Cluster III(Fundamental Science and Engineering), Full Professor, Japan - Apr. 2025 - Mar. 2026
The University of Electro-Communications, Graduate School of Informatics and Engineering Department of Mechanical and Intelligent Systems Engineering, 専攻長, Japan - Apr. 2024 - Mar. 2025
The University of Electro-Communications, Graduate School of Informatics and Engineering Department of Mechanical and Intelligent Systems Engineering, 副専攻長, Japan - Apr. 2023 - Mar. 2024
The University of Electro-Communications, School of Informatics and Engineering, III類長, Japan - Apr. 2022 - Mar. 2023
The University of Electro-Communications, School of Informatics and Engineering, III類副類長, Japan - Apr. 2015 - Mar. 2019
The University of Electro-Communications, Graduate School of Informatics and Engineering, Associate Professor - Apr. 2010 - Mar. 2015
Hokkaido University of Science, Associate Professor - Apr. 2008 - Mar. 2009
三菱重工業 名古屋航空宇宙システム製作所 研究部 機体機器研究課, 社員 - Apr. 2005 - Mar. 2008
Japan Aerospace Exploration Agency Aviation Program Group, 宇宙航空プロジェクト研究員 - -
Educational Background
Member History
- Apr. 2025 - Present
ジュニア会員制度推進委員会委員, 日本航空宇宙学会, Society - Oct. 2016 - Present
計算力学部門設計情報駆動学研究会 主査, 日本機械学会, Society - Sep. 2022 - Mar. 2025
ジュニア会員制度推進委員会幹事, 日本航空宇宙学会, Society - Mar. 2021 - Feb. 2023
関東支部商議員, 日本機械学会, Society - Oct. 2017 - Sep. 2021
会計担当理事, 進化計算学会, Society - Mar. 2017 - Feb. 2019
空気力学部門 幹事, 日本航空宇宙学会, Society - Oct. 2011 - Sep. 2016
幹事, 日本機械学会 計算力学部門 設計情報学研究会, Society - Apr. 2015 - Mar. 2016
Associate Editor, Japan Society for Mechanical Engineering, Mechanical Engineering Journal, Computational Mechanics Division, Society - Jun. 2012 - Mar. 2016
委員, JAXA ISAS ハイブリッドロケット研究WG, Others - Mar. 2015 - Sep. 2015
Program committee member, IEEE International Conference on Data Mining, 1st International Workshop on Engineering Data Mining, Society - Feb. 2014 - Jul. 2015
Congress on Evolutionary Computation2015 実行委員, IEEE, Society - Mar. 2013 - Feb. 2015
会員部会 北海道支部 委員, 日本機械学会, Society - Mar. 2013 - Feb. 2015
商議員，会員拡充担当幹事, 日本機械学会北海道支部, Society - Jul. 2013 - Mar. 2014
スペースプレーン技術実証機WG 委員, JAXA ISAS, Society - Apr. 2010 - Mar. 2014
専門委員, 進化計算学会, Society - Oct. 2006 - Sep. 2011
委員, 日本機械学会 計算力学部門 複合領域における設計探査研究会, Society - Apr. 2006 - Mar. 2008
第39期空力部門委員, 日本航空宇宙学会, Society - Apr. 2005 - Sep. 2006
委員, 日本機械学会 計算力学部門 流体と構造の複合問題研究会, Society
Research Activity Information
Award
- Mar. 2024
日本設計工学会
武藤栄次賞優秀学生賞, 小林 英里奈 - Feb. 2024
日本機械学会
フェロー, 千葉 一永 - Dec. 2022
進化計算学会
進化計算コンペティション2022産業応用特別賞, 門馬 圭吾 - Dec. 2022
進化計算学会
進化計算コンペティション2022多目的部門準トップ賞, 門馬 圭吾 - Jul. 2020
The 5th International Conference on Data Mining and Big Data
Hypothesis Verification for Designing Flyback Booster by Analysis of Variance Visualized on Triangular Matrix Representations
Best Paper Award, Chiba, K.;Hatta, T.;Kanazaki, M. - Mar. 2019
The 3rd International Conference on Intelligent Systems, Metaheuristics & Swarm Intelligence
Automated System for Evolutionary Design Optimization with Unstructured Computational Fluid Dynamics
Best Paper Presentation Award, Kazuhisa Chiba;Tsuyoshi Sumimoto;Masataka Sawahara - Sep. 2017
日本機械学会
計算力学部門業績賞, 千葉 一永 - Dec. 2016
進化計算学会
Reebグラフに基づく多数目的パレートフロントのニーポイントの検出法
2016年研究会最優秀論文賞, 濱田 直希;千葉 一永 - Dec. 2014
The Japanese Society for Evolutionary Computation
Evaluation of Multi-Time-Combustion-Type Hybrid Rocket by Means of Genetic Algorithm
The Best Paper Award, Masahiro Kanazaki;Kazuhisa Chiba;Koki Kitagawa;Toru Shimada - Sep. 2003
日本機械学会
非構造N-S計算によるRLVブースター段翼形状の進化的最適設計
設計工学・システム部門講演会優秀発表表彰, 千葉 一永;大林 茂;中橋 和博
Paper
- Quantification for Severe Weather Avoidance Based on Precipitation Data
Kokoro Yokohama; Yoichi Nakamura; Atsushi Senoguchi; Kazuhisa Chiba
Last, JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Japan Society for Aeronautical and Space Sciences, 73, 2, 51-58, Apr. 2025, Peer-reviwed
Scientific journal, Japanese - Aerodynamics on a faithful hindwing model of a migratory dragonfly based on 3D scan data
Narita, Y; Chiba, K
Last, Journal of Fluids and Structures, 125, 104080, Feb. 2024, Peer-reviwed
Scientific journal, English - Feedback-Circulating Desgin Space Exploration by Multi-Sampling Kriging Model: Exploitation for the Lift Rise by an Aircraft Flap with Yaw-Wise Rotation
Chiba, K; Kanazaki, M
Lead, Proceedings of the International Conference on Intelligent Systems, Metaheuristics and Swarm Intelligence, 119-123, May 2023, Peer-reviwed
Scientific journal, English - Pondering Problem Definition for Optimum Orbit Design of Regional Observation Satellite Constellations
町井佳菜子; 川勝康弘; 千葉一永
Corresponding, 進化計算学会論文誌(Web), 12, 2, 37-44, Jan. 2022, Peer-reviwed, Invited
Scientific journal, Japanese - 機械工学とインフォマティックス
大林 茂, 千葉 一永, 下山 幸治, 三坂 孝志
日本設計工学会誌, 日本設計工学会, 56, 10, 1-4, 16 Oct. 2021, Invited, False
Japanese - 進化的ルール学習を用いた遷音速バフェットの解析
中田 雅也, 千葉 一永
可視化情報学会誌, 可視化情報学会, 41, 162, 103-104, 01 Oct. 2021, Invited, False
Japanese - 航空宇宙工学分野の可視化事例
千葉 一永, 金崎 雅博
可視化情報学会誌, 可視化情報学会, 41, 162, 82-82, 01 Oct. 2021, Invited, False
Japanese - Mapperによる航空機設計知識の抽出と可視化 - 位相的データ解析を用いた設計情報学的アプローチ -
濱田 直希, 千葉 一永
可視化情報学会誌, 可視化情報学会, 41, 162, 105-106, 01 Oct. 2021, Invited, False
Japanese - Acquisition of Swept Aerodynamic Data by the Consecutive Changing of Wing Model Configuration in a Wind Tunnel Test Using Remote Feedback Control
Ken Wakimoto; Kazuhisa Chiba; Hiroyuki Kato; Kazuyuki Nakakita
Corresponding, Aerospace, 8, 8, 217:1-217:13, Aug. 2021, Peer-reviwed
Scientific journal, English - Hypothesis derivation and its verification by a wholly automated many-objective evolutionary optimization system
Chiba, K; Sawahara, M; Sumimoto, T; Hatta, T; Kanazaki, M
Lead, Neural Computing and Applications, 33, 1-13, 06 Mar. 2021, Peer-reviwed, Invited
Scientific journal, English - Hypothesis Verification for Designing Flyback Booster by Analysis of Variance Visualized on Triangular Matrix Representations
Chiba, K; Hatta, T; Kanazaki, M
Lead, Communications in Computer and Information Science, 1234, 34-44, Jul. 2020, Peer-reviwed, Invited
English - Remote and Feedback Control of the Flap Angle in a Wind Tunnel Test Model by Optical Measurement
Kazuhisa Chiba; Tatsuro Komatsu; Hiroyuki Kato; Kazuyuki Nakakita
Lead, Aerospace, 7, 2, 1-11, Jan. 2020, Peer-reviwed
Scientific journal, English - Completely automated system for evolutionary design optimization with unstructured computational fluid dynamics
Kazuhisa Chiba; Tsuyoshi Sumimoto; Masataka Sawahara
PervasiveHealth: Pervasive Computing Technologies for Healthcare, ICST, 54-58, 23 Mar. 2019, We have fulfilled a completely automated system of evolutionary design optimization with unstructured computational fluid dynamics. Until now, we cannot automatize aerodynamic design optimization to deal with geometry with high degrees of freedom. However, we achieved to simply iterate large-scale (it takes huge time to evaluate objective functions) and real-world evolutionary multiobjective optimizations. As a result, we efficiently obtained design knowledge for a next-step problem by applying the system to the design problem of a booster stage for two-stage-to-orbit. Moreover, this study yields the hypothesis regarding the appropriate algorithm of evolutionary computation for not only mathematical benchmark but also large-scale real-world problems.
International conference proceedings, English - Elucidation of Influence of Fuels on Hybrid Rocket Using Visualization of Design-Space Structure
Kazuhisa Chiba; Shin’ya Watanabe; Masahiro Kanazaki; Koki Kitagawa; Toru Shimada
Computational Methods in Applied Sciences, 48, 473-488, 2019, The stratum-type association analysis as a new data mining technique has been applied to the conceptual design of a single-stage launch vehicle with hybrid rocket engine. The conceptual design was performed by using design informatics, which has three points of view, i.e., problem definition, optimization, and data mining. The primary objective of the present design is that the down range and the duration time in the lower thermosphere are sufficiently secured for the aurora scientific observation, whereas the initial gross weight is held down to the extent possible. The multidisciplinary design optimization was performed by using a hybrid evolutionary computation. Data mining was also implemented by using the stratum-type association analysis. Consequently, the design information regarding the tradeoffs has been revealed. The hierarchical dendrogram generated by using the stratum-type association analysis indicates the structure of the design space in order to improve the objective functions. Furthermore, the assignments of the stratum-type association analysis have been obtained.
In book - Genetic Algorithm Applied to Design Knowledge Discovery of Launch Vehicle Using Clustered Hybrid Rocket
Masahiro Kanazaki; Kazuhisa Chiba; Shoma Ito; Masashi Nakamiya; Koki Kitagawa; Toru Shimada
Computational Methods in Applied Sciences, 48, 519-535, 2019, The conceptual design of a multi-stage launch vehicle (LV) using a clustered hybrid rocket engine (HRE) is carried out through multi-disciplinary design optimization. This LV designed in this study can deliver micro-satellites to sunsynchronous orbits (SSO). The optimum size of each component, such as an oxidizer tank containing liquid oxidizer, a combustion chamber containing solid fuel, a pressurizing tank, and a nozzle, should be strictly optimized because of the combustion mechanism is different from existent liquid/solid rocket engines. In this study, the semi-empirical based evaluation is applied to the design optimization of the multi-stage LV. For clustered HRE, paraffin (FT-0070) is used as a propellant for the HRE, and three cases are compared to examine the commonization effect of the engine for each stage: In the first case, HREs are optimized for each stage. In the second case, HREs are optimized together for the first and second stages but separately for the third stage. In the third case, HREs are optimized together for each stage. The optimization results show that the performance of the design case that uses the same HREs in all stages is 40% reduced compared with the design case that uses optimized HREs for each stage.
In book - Evolutionary Multidiscipnary Design Optimization of Blended-Wing-Body-Type Flyback Booster
Tsuyoshi Sumimoto; Kazuhisa Chiba; Masahiro Kanazaki; Takahiro Fujikawa; Koichi Yonemoto; Naoki Hamada
Proceedings of the 57th AIAA Aerospace Sciences Meeting, AIAA Paper-2019-0703, Jan. 2019, Peer-reviwed
International conference proceedings, English - 相関ルールに基づく非劣解分析支援システムのオンデマンド化
賀川 祐太朗; 渡邉 真也; 金崎 雅博; 依田 英之; 千葉 一永
進化計算学会論文誌, 8, 2, 75-87, Feb. 2018, Peer-reviwed, Invited
Scientific journal, Japanese - Simple control of oxidizer flux for efficient extinction-reignition on a single-stage hybrid rocket
Kazuhisa Chiba; Masahiro Kanazaki; Toru Shimada
AEROSPACE SCIENCE AND TECHNOLOGY, ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER, 71, 109-118, Dec. 2017, Peer-reviwed, This study aims at revealing the effect of the simple control of oxidizer flux on a hybrid rocket engine for an efficient extinction-reignition sequence to extend the downrange as well as the duration in the lower thermosphere. The data mining result in the prior study achieved a hypothesis that the thrust control between 1st and 2nd combustions spurs improving extinction-reignition performance. Accordingly, this study simply defines two amounts of oxidizer flux for 1st and 2nd combustions; we investigate using the design informatics platform whether this simple control of oxidizer flux is practically effective to improving extinction-reignition performance. Consequently, oxidizer flux control successfully fulfills the downrange extension as well as the duration protraction as we had expected. Furthermore, the evolutionary multiobjective optimization generates non-simple structure of the feasible region in the design space. Trajectory analyses for signature individuals and a data mining have specified detailed design strategies. In addition, they have also explained physical reasons why the non-simple structure is formed. Extinction-reignition with oxidizer flux control is useful for efficient operations of the hybrid rocket system. (C) 2017 Elsevier Masson SAS. All rights reserved.
Scientific journal, English - Aerodynamic influences on a tethered high-altitude lighter-than-air platform system to its behavior
Kazuhisa Chiba; Ryosuke Nishikawa; Masahiko Onda; Shin Satori; Ryojiro Akiba
AEROSPACE SCIENCE AND TECHNOLOGY, ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER, 70, 405-411, Nov. 2017, Peer-reviwed, The goal of this study was to investigate the influence of aerodynamic factors on the static behavior of a tethered high-altitude lighter-than-air platform. The system design comprised a lighter-than-air vehicle and a tether cable, and the conceptual platform configuration of such a system is studied herein. Governing equations were derived to model the static behavior of the system, and the effects of aerodynamic lift and buoyancy were parametrically analyzed based on the advection distance of the platform under storm conditions. The aerodynamic lift and buoyancy of the hull were shown to have nonlinear effects. We further analyzed the influence of the aerodynamic drag created by the tether. Since this was shown to have a significant influence, we concluded that the cable should ideally have a cross-sectional shape resembling the airfoil of a heavier-than-air aircraft. However, it is sufficient to ensure that the drag coefficient is of the order of 10(-1). (C) 2017 Elsevier Masson SAS. All rights reserved.
Scientific journal, English - Cognition of Parameters' Role on Vertical Control Device for Aerodynamic Performances of Aircraft Using Visual Data Mining
Chiba, K; Omori, T; Sunada, Y; Imamura, T
International Journal of Mechanical Systems, 1, 18-31, Oct. 2017, Peer-reviwed, Invited
Scientific journal, English - Conceptual Design Methodology of a Hybrid Rocket Engine-Powered Launch Vehicle for Sub-Orbital Flight.
Kanazaki, M; Yoda, H; Chiba, K; Kitagawa, K; Shimada, T
Journal of Aerospace Engineering, 30, 6, 1-12, Aug. 2017, Peer-reviwed
Scientific journal, English - Design Strategy Generation for a Sounding Hybrid Rocket via Evolutionary Rule-Based Data Mining System
Masaya Nakata; Kazuhisa Chiba
INTELLIGENT AND EVOLUTIONARY SYSTEMS, IES 2016, SPRINGER INT PUBLISHING AG, 8, 305-318, 2017, Peer-reviwed, This paper aims to reveal design strategies of a sounding hybrid rocket to efficiently perform extinction-reignition. On previous studies, we have derived design candidates which each is a solution optimized on a design optimization problem for the sounding hybrid rocket. To extract design strategies from the design candidates, this paper applies an evolutionary mining system to design candidates, considered as a knowledge discovery task. Specifically, we introduce an evolutionary rule-based data mining system for analyzing a set of Pareto optimal solutions. Our system acquires rules indicating local design information and also we intuitively discover anomalous design strategies.
International conference proceedings, English - Multiple Additional Sampling by Expected Improvement Maximization in Efficient Global Optimization for Real-World Design Problems
Masahiro Kanazaki; Taro Imamura; Takashi Matsuno; Kazuhisa Chiba
INTELLIGENT AND EVOLUTIONARY SYSTEMS, IES 2016, SPRINGER INT PUBLISHING AG, 8, 183-194, 2017, Peer-reviwed, Efficient global optimization (EGO), based on the expected improvement maximization of the Kriging model, is a suitable optimization method for designs based on time-consuming evaluations such as computational fluid dynamics. However, the original formulation of EGO can find only one additional sample point after an initial sample point is acquired for the initial Kriging model construction. Therefore, the efficiency of EGO is decreased even if the designer is able to evaluate several designs using a large parallel computer because additional samples can only be obtained sequentially through the additional sampling process. In this study, a multiple additional sampling method is proposed to improve the efficiency of the additional sampling process in EGO while maintaining the performance of exploration based on EI maximization. The design performance of EGO with MAS is investigated by solving a test problem first, and then an airfoil design problem, which is a single objective problem. The results are compared with the original EGO in terms of the convergence of the objective function and the diversity of the design variables. According to these problems, the proposed method acquires optimum solutions as effectively as the original EGO, while the diversity of the solutions is improved. In addition, the total design time can be reduced compared with the original EGO in a parallel computational environment.
International conference proceedings, English - Hybrid Propulsion Technology Development in Japan for Economic Space Launch
Toru Shimada; Saburo Yuasa; Harunori Nagata; Shigeru Aso; Ichiro Nakagawa; Keisuke Sawada; Keiichi Hori; Masahiro Kanazaki; Kazuhisa Chiba; Takashi Sakurai; Takakazu Morita; Koki Kitagawa; Yutaka Wada; Daisuke Nakata; Mikiro Motoe; Yuki Funami; Kohei Ozawa; Tomoaki Usuki
CHEMICAL ROCKET PROPULSION: A COMPREHENSIVE SURVEY OF ENERGETIC MATERIALS, SPRINGER-VERLAG BERLIN, 545-575, 2017, Peer-reviwed, Invited, The demand for the economic and dedicated space launchers for vast amount of lightweight, so-called nano-/microsatellites, is now growing rapidly. There is a strong rationale for the usage of the hybrid propulsion for economic space launch as suggested by the assessment conducted here. A typical concept of development of such an economic three-stage launcher, in which clustering unit hybrid rocket engines are employed, is described with a development scenario. Thanks to the benefits of hybrid rocket propulsion, assuring and safe, economic launcher dedicated to lightweight satellites can be developed with a reasonable amount of quality assurance and quality control actions being taken in all aspects of development such as raw material, production, transportation, storage, and operation. By applying a multi-objective optimization technique for such a launch system, examples of possible launch systems are obtained for a typical mission scenario for the launch of lightweight satellites. Furthermore, some important technologies that contribute strongly to economic space launch by hybrid propulsion are described. They are the behavior of fuel regression rate, the swirling-oxidizerflow- type hybrid rocket, the liquid oxygen vaporization, the multi-section swirl injection, the low-temperature melting point thermoplastic fuel, the thrust and O/F simultaneous control by altering-intensity swirl-oxidizer-flow-type (A-SOFT) hybrid, the numerical simulations of the internal ballistics, and so on.
International conference proceedings, English - Extinction-reignition superiority in a single-stage sounding hybrid rocket
Kazuhisa Chiba; Hideyuki Yoda; Masahiro Kanazaki; Toru Shimada
AEROSPACE SCIENCE AND TECHNOLOGY, ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER, 58, 437-444, Nov. 2016, Peer-reviwed, Information visualization has been performed for researching a single-stage sounding launch vehicle with hybrid rocket engine by using design informatics. The primary objective of this study is to reveal extinction-reignition superiority, which is one of the beneficial points of hybrid rocket, for extending the downrange and the duration in the lower thermosphere. In our hybrid rocket, swirling-flow oxidizer is furnished with solid fuel; we adopt polypropylene for solid fuel and liquid oxygen for oxidizer. A multidisciplinary design optimization is implemented by using a hybrid evolutionary computation; data mining is carried out by using a scatter plot matrix to efficiently perceive the entire design space. It is consequently revealed that extinction-reignition prolongs duration although it does not provide any effects on spreading downrange. Scatter plot matrix results indicate physical mechanisms of design variable behaviors for the objective functions and also the roles of the design variables via bird's-eye visualization of the entire design-space constitution. Furthermore, they suggest a hypothesis to extend downrange. (C) 2016 Elsevier Masson SAS. All rights reserved.
Scientific journal, English - Knee Point Detection of Many-Objective Pareto Fronts Based on the Reeb Graph
Naoki Hamada; Kazuhisa Chiba
Proceedings of the JPNSEC 11th Workshop, 121-133, Sep. 2016
Symposium, Japanese - Structurisation and Visualisation of Design Space for Launch Vehicle with Hybrid Rocket Engine
Chiba, K; Kanazaki, M; Watanabe, S; Kitagawa, K; Shimada, T
International Journal of Automation and Logistics, 2, 1, 26-44, Feb. 2016, Peer-reviwed, Invited
Scientific journal, English - Manifestation of ascendancy of extinction-reignition on sounding hybrid rocket using design informatics
Kazuhisa Chiba; Masahiro Kanazaki; Toru Shimada
ECCOMAS Congress 2016 - Proceedings of the 7th European Congress on Computational Methods in Applied Sciences and Engineering, National Technical University of Athens, 4, 8403-8418, 2016, Peer-reviwed, Information visualization have been performed for researching and developing a single-stage sounding launch vehicle with hybrid rocket engine by using design informatics
it has three points of view: problem definition, optimization, and data mining. The primary objective of this study is to reveal extinction-reignition ascendancy, which is one of the beneficial points of hybrid rocket, for expanding downrange and duration in the lower thermosphere. Swirling-flow oxidizer is furnished with solid fuel
we adopt polypropylene for solid fuel and liquid oxygen for oxidizer. A multidisciplinary design optimization was implemented by using a hybrid evolutionary computation
data mining was carried out by using a scatter plot matrix to efficiently perceive the entire design space. It is consequently revealed that extinction-reignition extends duration although it does not provide any effect on expanding downrange. Scatter plot matrix results express physical mechanisms of design-variable behaviors for the objective functions and also the roles of the design variables via bird's-eye visualization of the entire design-space constitution.
International conference proceedings, English - Physical Construction of Local Design Information for Sounding Hybrid Rocket Design via Correlation-based Information Hierarchical Structure
Kazuhisa Chiba; Shinya Watanabe; Masahiro Kanazaki
2016 IEEE CONGRESS ON EVOLUTIONARY COMPUTATION (CEC), IEEE, 2588-2595, 2016, Peer-reviwed, Design information in practical engineering problems is briefly classified into two groups: global and local design information. Global design information is easy to physically construct but mostly trivial. In contrast, local design information is difficult to physically interpret because of mechanical acquisition but potentially worth for innovative design. This research deals with a recent data mining be named Correlation-based Information Hierarchical Structuring Method; we apply it to a practical engineering problem to physically construct local design information. As a result, our approach has successfully functioned as intuitive visual mining to generate latent hierarchical structure of the design space. Moreover, local design information regarding sweet spots was consequently revealed although the former mining techniques did not obtain them; physical construction could be also implemented by handling it.
International conference proceedings, English - On-demand correlation-based information hierarchical structuring method (CIHSM) for non-dominated solutions
Shinya Watanabe; Sho Nakano; Kazuhisa Chiba; Masahiro Kanazaki
2016 IEEE CONGRESS ON EVOLUTIONARY COMPUTATION (CEC), IEEE, 1977-1984, 2016, Peer-reviwed, In this paper, on-demand analysis support system for non-dominated solutions (NDSs) was presented. This proposed system was designed by extending our previous analysis approach, correlation-based information hierarchical structuring method (CIHSM), to correspond with user's demand. Previous version of CIHSM could extract features of NDSs using association rule mining and visually present result of analyses as a hierarchical tree in which each node consists of a subgroup of NDSs. However, this version was not necessarily to extract the feature required by user in the case of weak trend. If it tried to extract every association rule even though their correlation degrees are very weak, the number of the derived association rules is so large that previous CIHSM cannot manage these. Therefore, this paper presents a modified CIHSM corresponding to on-demand requests. In this on-demand CIHSM, users provide their demands in advance. And on-demand CIHSM tries to extract as many as possible association rules and eliminate every association rule not relevant to user's demand. This on-demand CIHSM only provides detailed information consistent with user's demand. Through some test problems, it was verified how accurate information on-demand CIHSM can extract from NDSs.
International conference proceedings, English - 多目的進化計算による多数回燃焼を行うハイブリッドロケットの性能評価
金崎 雅博; 千葉 一永; 北川 幸樹; 嶋田 徹
進化計算学会論文誌, 6, 3, 137-145, Dec. 2015, Peer-reviwed
Scientific journal, Japanese - Development of Spacebone Multi-spectral Camerafor Nanosatellites
SATORI Shin; ITO Tomonori; TAKEUCHI Yusuke; CHIBA Kazuhisa; SASAKI Masami; MITSUHASHI Ryuichi
SPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 14, 179-183, Dec. 2015, Peer-reviwed, We have developed a small size，lightweight 4 bands multi-spectral camera for micro-satellites, nano-satellites and cube-sats and soon. This spectral camera can select several wavelengths required by earth observation experiments, by exchanging the optimum bandpass filter.
Scientific journal, Japanese - Design Optimization of Single-Stage Launch Vehicle Using Hybrid Rocket Engine
Kanazaki, M; Ariyarit, A; Yoda, H; Ito, S; Chiba, K; Kitagawa, K; Shimada, T
International Journal of Aerospace System Engineering, 2, 2, 29-33, Dec. 2015, Peer-reviwed, Invited
Scientific journal, English - Multidisciplinary Design Exploration for Sounding Launch Vehicle using Hybrid Rocket Engine in View of Ballistic Performance
Kazuhisa Chiba; Masahiro Kanazaki; Atthaphon Ariyarit; Hideyuki Yoda; Shoma Ito; Koki Kitagawa; Toru Shimada
INTERNATIONAL JOURNAL OF TURBO & JET-ENGINES, WALTER DE GRUYTER GMBH, 32, 3, 299-304, Sep. 2015, Peer-reviwed, Conceptual design of a launch vehicle with a hybrid rocket engine (HRE) has been implemented using design informatics approach in order to investigate the feasibility of a single-stage hybrid rocket. Two test design problems were formulated by using two objective functions: maximization of downrange and minimization of initial gross weight, seven design variables which describe geometry and initial conditions, and one constraint relative to target altitude. The optimization result reveals the economical performance of hybrid rocket is limited with HRE in terms of the maximum downrange achievable. Moreover, the data-mining result indicates the mechanism of design-variable behavior.
Scientific journal, English - Behavior of tether for captive stratosphere platform using airship
Kazuhisa Chiba; Shin Satori; Ryuichi Mitsuhashi; Jun'ya Sasaki; Ryojiro Akiba
2014 ASIA-PACIFIC INTERNATIONAL SYMPOSIUM ON AEROSPACE TECHNOLOGY, APISAT2014, ELSEVIER SCIENCE BV, 99, 905-910, 2015, Peer-reviwed, The existence of a platform at the stratosphere is expected to be the role to gain a foothold in space. When the platform is employed airship in, it is transported by advection due to its light-weight body. Thereupon, a mooring of platform is reasonable in order to incarnate fixed-point platform. Conception of a captive platform system is similar to the Rockoon one which rendered remarkable services for the space observation of the early days. Therefore, the application of captive platform system to the launch site is highly expected in order to realize the space transportation system with a large quantity and high frequency. In this study, the motion of a captive platform system constructed from an airship and a tether is analyzed in order to ensure that the motion of a captive platform system is practically incarnated. Moreover, the sensitivity of aerodynamic performance of the airship is observed. Consequently, the practically incarnated motion of a captive platform system has been identified under the condition of the storm environment. Furthermore, the reduction of the advection distance driven away by the storm has been quantitatively indicated under the different condition of aerodynamic performance of the airship. (C) 2015 The Authors. Published by Elsevier Ltd.
International conference proceedings, English - Conceptual Design of Single-stage Rocket Using Hybrid Rocket by Means of Genetic Algorithm
Masahiro Kanazaki; Atthaphon Ariyairt; Kazuhisa Chiba; Koki Kitagawa; ToruShimada
2014 ASIA-PACIFIC INTERNATIONAL SYMPOSIUM ON AEROSPACE TECHNOLOGY, APISAT2014, ELSEVIER SCIENCE BV, 99, 198-207, 2015, Peer-reviwed, In this study, a multi-objective genetic algorithm (MOGA) was applied to the multidisciplinary design optimization (MDO) of a hybrid rocket. A swirling-oxidizer-type hybrid rocket engine (HRE) with a single cylindrical grain port was designed. It was considered that this HRE could temporarily stop combustion via oxidizer throttling; this feature is called multi-combustion. The MOGA was applied to solve the multi-objective problem using real-number coding and the Pareto ranking method. In this study, three design problems were considered. First problem was the maximization of the flight altitude and minimization of the gross weight. Second problem was the minimization of the maximum acceleration and minimization of the gross weight. Third problem was the maximization of the duration time over the target flight altitude and minimization of the gross weight. Each objective function was empirically estimated. In addition, this study compared two types of HREs to investigate the emects of the multi-combustion: one type was able to carry out the multi-combustion, and the other was not. Many non-dominated solutions were obtained using the MOGA, and a trade-off was observed between the two objective functions. To understand the design problem, the MOGA results were visualized using a parallel coordinate plot (PCP). (C) 2015 The Authors. Published by Elsevier Ltd.
International conference proceedings, English - Visualization of Design-Space Constitution for Single-Stage Hybrid Rocket with Rigid Body in View of Extinction-Reignition
Kazuhisa Chiba; Hideyuki Yoda; Shoma Ito; Masahiro Kanazaki
2015 IEEE SYMPOSIUM SERIES ON COMPUTATIONAL INTELLIGENCE (IEEE SSCI), IEEE, 933-940, 2015, Peer-reviwed, Visualization of design space has been performed for researching and developing a single-stage launch vehicle with hybrid rocket engine by using design informatics, which has three points of view such as problem definition, optimization, and data mining. The primary objective of the present design is that the ascendancy of extinction-reignition, which is one of the beneficial point of hybrid rocket, for improving the downrange and the duration time in the lower thermosphere. Polypropylene and liquid oxygen with swirling flow are adopted as solid fuel and liquid oxidizer, respectively. The multidisciplinary design optimization was performed by using a hybrid evolutionary computation; data mining was implemented by using a scatterplot matrix in order to efficiently perceive design space. As a result, it is revealed that extinction-reignition extends the duration time though it does not give an effect on improving the downrange. Data-mining results also show the physical mechanism of the design variables to improve the duration time on the visualization of design-space constitution.
International conference proceedings, English - Conceptual Design of Single-Stage Launch Vehicle with Hybrid Rocket Engine Using Design Informatics
Kazuhisa Chiba; Masahiro Kanazaki; Koki Kitagawa; Toru Shimada
ADVANCES IN EVOLUTIONARY AND DETERMINISTIC METHODS FOR DESIGN, OPTIMIZATION AND CONTROL IN ENGINEERING AND SCIENCES, SPRINGER-VERLAG BERLIN, 36, 369-384, 2015, Peer-reviwed, A single-stage launch vehicle with hybrid rocket engine has been conceptually designed by using design informatics, which has three points of view as problem definition, optimization, and data mining. The primary objective of the design in the present study is that the sufficient down range and the duration time in the lower thermosphere are achieved for aurora scientific observation whereas the initial gross weight is held down. Multidisciplinary design optimization and data mining were performed by using evolutionary hybrid computation under the conditions that polypropylene as solid fuel and liquid oxygen as liquid oxidizer were adopted and that single-time ignition is implemented in sequence. Consequently, the design information regarding the tradeoffs and the behaviors of the design variables in the design space was obtained in order to quantitatively differentiate the advantage of hybrid rocket engine.
International conference proceedings, English - Structurization of Design Space for Launch Vehicle with Hybrid Rocket Engine Using Stratum-Type Association Analysis
Kazuhisa Chiba; Masahiro Kanazaki; Shin'ya Watanabe; Koki Kitagawa; Toru Shimada
PROCEEDINGS OF THE 18TH ASIA PACIFIC SYMPOSIUM ON INTELLIGENT AND EVOLUTIONARY SYSTEMS, VOL 1, SPRINGER INT PUBLISHING AG, 509-521, 2015, Peer-reviwed, A single-stage launch vehicle with hybrid rocket engine has been conceptually designed by using design informatics, which has three points of view, i.e., problem definition, optimization, and data mining. The primary objective of the present design is that the down range and the duration time in the lower thermosphere are sufficiently secured for the aurora scientific observation, whereas the initial gross weight is held down to the extent possible. The multidisciplinary design optimization was performed by using a hybrid evolutionary computation. Data mining was also implemented by using the stratum-type association analysis. Consequently, the design information regarding the tradeoffs has been revealed. Furthermore, the hierarchical dendrogram generated by using the stratum-type association analysis indicates the structure of the design space in order to improve the objective functions. Thereupon, it has been revealed the versatility of the synthetic system as design informatics for real-world problems.
International conference proceedings, English - Multi-Disciplinary Conceptual Design Knowledge of Multi-Stage Hybrid Rocket Using Data Mining Technique
Kanazaki, M; Chiba, K; Kitagawa, K; Shimada, T; Nakamiya, M
Journal of Mechanics Engineering and Automation, 5, 1, 1-9, Jan. 2015, Peer-reviwed
Scientific journal, English - 設計情報学を用いたハイブリッドロケットエンジン搭載単段式宇宙輸送機の概念設計
千葉 一永; 渡邉 真也; 金崎 雅博; 北川 幸樹; 嶋田 徹
日本機械学会論文集, 「設計工学とシステム工学の新展開2014」特集号, 80, 818, 1-13, Oct. 2014, Peer-reviwed, Invited
Scientific journal, Japanese - Conceptual Design of Single-Stage Hybrid Rocket for Scientific Observation in View of Fuels Using Design Informatics
CHIBA Kazuhisa; KANAZAKI Masahiro; NAKAMIYA Masaki; KITAGAWA Koki; SHIMADA Toru
AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 13, 41-50, Jun. 2014, Peer-reviwed, A single-stage launch vehicle with hybrid rocket engine, which uses solid fuel and liquid oxidizer, has been being studied and developed as a next-generation rocket for scientific observation due to the advantages as low cost, safety, re-ignition, and reduced pollution. Therefore, the knowledge regarding hybrid rocket system has been being gained through the forepart of the conceptual design using design informatics. In the present study, the practical problem defined by using three objective functions and seven design variables for aurora observation is treated so as to contribute the real world using evolutionary computation and data mining for the field of aerospace engineering. The primary objective of the design in the present study is that the down range and the duration time in the lower thermosphere are sufficiently obtained for the aurora scientific observation, whereas the initial gross weight is held down. Investigated solid fuels are five, while liquid oxidizer is considered as liquid oxygen. The condition of single-time ignition is assumed in flight sequence in order to quantitatively investigate the ascendancy of multi-time ignition. A hybrid evolutionary computation between the differential evolution and the genetic algorithm is employed for the multidisciplinary design optimization. A self-organizing map is used for the data mining technique in order to extract global design information. Consequently, the design information regarding the tradeoffs among the objective functions, the behaviors of the design variables in the design space to become the nondominated solutions, and the implication of the design variables for the objective functions have been obtained in order to quantitatively differentiate the advantage of hybrid rocket engine in view of the five fuels. Moreover, the next assignments were also revealed.
Japanese - Diversity of design knowledge for launch vehicle in view of fuels on hybrid rocket engine
Kazuhisa Chiba; Masahiro Kanazaki; Masaki Nakamiya; Koki Kitagawa; Toni Shimada
JOURNAL OF ADVANCED MECHANICAL DESIGN SYSTEMS AND MANUFACTURING, JAPAN SOC MECHANICAL ENGINEERS, 8, 3, 1-14, 2014, Peer-reviwed, A single-stage launch vehicle with hybrid rocket engine, which uses solid fuel and liquid oxidizer, has been studied and developed as a next-generation rocket for scientific observation due to the advantages as low cost, safety, re-ignition, and reduced pollution. Thereupon, the knowledge regarding hybrid rocket system has been gained through the forepart of the conceptual design using design informatics. In the present study, the practical problem defined by using three objective functions and seven design variables for aurora observation is treated so as to contribute the real world using evolutionary computation and data mining for the field of aerospace engineering. The primary objective of the design in the present study is that the down range and the duration time in the lower thermosphere are sufficiently obtained for the aurora scientific observation, whereas the initial gross weight is held down. Investigated solid fuels are five, while liquid oxidizer is considered as liquid oxygen. A hybrid rocket uses one of five kinds of fuels. The condition of single-time ignition is assumed in flight sequence in order to quantitatively investigate the ascendancy of multi-time ignition. A hybrid evolutionary computation between the differential evolution and the genetic algorithm is employed for the multidisciplinary design optimization. A self-organizing map is used for the data mining technique in order to extract global design information. Consequently, the design information regarding the tradeoffs among the objective functions, the behaviors of the design variables in the design space to become the nondominated solutions, and the implication of the design variables for the objective functions have been obtained in order to quantitatively differentiate the advantage of hybrid rocket engine in view of the five fuels. Moreover, the next assignments were also revealed.
Scientific journal, English - BIRD'S-EYE VISUALIZATION OF DESIGN-KNOWLEDGE DIVERSITY FOR LAUNCH VEHICLE IN VIEW OF FUELS ON HYBRID ROCKET ENGINE
Kazuhisa Chiba; Masahiro Kanazaki; Masaki Nakamiya; Koki Kitagawa; Toru Shimada
11TH WORLD CONGRESS ON COMPUTATIONAL MECHANICS; 5TH EUROPEAN CONFERENCE ON COMPUTATIONAL MECHANICS; 6TH EUROPEAN CONFERENCE ON COMPUTATIONAL FLUID DYNAMICS, VOLS II - IV, INT CENTER NUMERICAL METHODS ENGINEERING, 3160-3179, 2014, Peer-reviwed, A single-stage launch vehicle with hybrid rocket engine, which uses solid fuel and liquid oxidizer, has been being studied and developed as a next-generation rocket for scientific observation due to the advantages as low cost, safety, re-ignition, and reducing pollution. Thereupon, the knowledge regarding hybrid rocket system has been being gained through the forepart of the conceptual design using design informatics. In the present study, the practical problem defined by using three objective functions and seven design variables for aurora observation is treated so as to contribute the real world using evolutionary computation and data mining for the field of aerospace engineering. The primary objective of the design in the present study is that the down range and the duration time in the lower thermosphere are sufficiently obtained for the aurora scientific observation, whereas the initial gross weight is held down. Investigated solid fuels are five, while liquid oxidizer is considered as liquid oxygen. The condition of single-time ignition is assumed in flight sequence in order to quantitatively investigate the ascendancy of multi-time ignition. A hybrid evolutionary computation between the differential evolution and the genetic algorithm is employed for the multidisciplinary design optimization. A self-organizing map is used for the data mining technique in order to extract global design information. Consequently, the design information regarding the tradeoffs among the objective functions, the behaviors of the design variables in the design space to become the nondominated solutions, and the implication of the design variables for the objective functions have been obtained in order to quantitatively differentiate the advantage of hybrid rocket engine in view of the five fuels. Moreover, the next assignments were also revealed.
International conference proceedings, English - Mapping of Normalized Difference Vegetation Index for Precision Agriculture by Small-Type Unmanned Aerial Vehicle
KAMEI Takuya; ITO Tomonori; SUGAI Shinya; OHTA Satoshi; SATORI Shin; CHIBA Kazuhisa
SPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 12, 111-117, Nov. 2013, Peer-reviwed, Precision agriculture has been being implemented in order environmentally friendly and efficiently to product and manage crops. The remote sensing by satellite and aircraft is employed in order to obtain the information regarding the growth of crops. Although the data from satellites can include wide-range image each time, it is insufficient due to the fixed orbital path of satellites. Therefore, fixed-point observations cannot be sufficiently performed. Moreover, the observations on fixed orbital path cannot be always carried out because of cloud. Although aircrafts are used for the interpolation of the insufficient data by satellites, manned aircrafts need high personnel expenses and maintenance costs. Therefore, unmanned aerial vehicle (UAV) is recently employed. The objective of the present study is the development of the system to generate the interpolated image data by normalized difference vegetation index (NDVI) map taken by small-type UAV (sUAV), which is low-priced and simple system to implement precision agriculture. The following three assignments have been concretely performed in the present study; 1) light-weight four-band multispectral camera carried in sUAV will be developed, 2) sUAV is managed and the image data will be taken, and 3) NDVI map will be generated from the image data by sUAV and interpolated image data will also be developed to contribute precision agriculture. Consequently, the lightest four-band multispectral camera in the world has been developed, and also sUAV has been able to be successfully managed and acquired image data could also generates NDVI maps.
Scientific journal, Japanese - Practical Operation of Design Informatics on Conceptual Design of Single-Stage Hybrid Rocket for Scientific Observation
Chiba Kazuhisa; Kanazaki Masahiro; Nakamiya Masaki; Kitagawa Koki; Shimada Toru
Transaction of the Japanese Society for Evolutionary Computation, The Japanese Society for Evolutionary Computation, 4, 3, 85-95, Nov. 2013, Peer-reviwed, A single-stage launch vehicle with hybrid rocket engine, which uses solid fuel and liquid oxidizer, has been being studied and developed as a next-generation rocket for scientific observation due to the advantages as low cost, safety, re-ignition, and reduced pollution. Therefore, the knowledge regarding hybrid rocket system has been being gained through the forepart of the conceptual design using design informatics. In the present study, the practical problem defined by using three objective functions and seven design variables for the aurora observation is treated so as to contribute the real world using evolutionary computation and data mining for the field of aerospace engineering. The primary objective of the design in the present study is that the sufficient down range and the duration time in the lower thermosphere are sufficiently achieved for the aurora scientific observation whereas the initial gross weight is held down. A hybrid rocket engine uses polypropylene as solid fuel and liquid oxygen as liquid oxidizer, and the condition of single-time ignition is assumed in sequence in order to quantitatively investigate the ascendancy of multi-time ignition. An evolutionary hybrid computation between the differential evolution and the genetic algorithm is employed for the multidisciplinary design optimization. A self-organizing map is used for the data mining technique in order to extract global design information. Consequently, the design information regarding the tradeoffs among the objective functions, the behaviors of the design variables in the design space to become the nondominated solutions, and the implication of the design variables for the objective functions has been obtained in order to quantitatively differentiate the advantage of hybrid rocket engine. Moreover, the next assignments were also revealed.
Scientific journal, Japanese - Conceptual Design of Single-Stage Launch Vehicle with Hybrid Rocket Engine for Scientific Observation Using Design Informatics
Chiba, K; Kanazaki, M; Nakamiya, M; Kitagawa, K; Shimada, T
Journal of Space Engineering, The Japan Society of Mechanical Engineers, 6, 1, 15-27, Sep. 2013, Peer-reviwed, A single-stage launch vehicle with hybrid rocket engine has been conceptually designed by using design informatics, which has three points of view as problem definition, optimization, and data mining. The primary objective of the design in the present study is that the sufficient down range and duration time in the lower thermosphere are achieved for the aurora scientific observation whereas the initial gross weight is held down. The multidisciplinary design optimization and data mining were performed by using evolutionary hybrid computation under the conditions that polypropylene as solid fuel and liquid oxygen as liquid oxidizer were adopted and that single-time ignition is implemented in sequence. Consequently, the design information regarding tradeoffs and the behavior of the design variables was obtained.
Scientific journal, English - Influence of Difference among Evolutionary-Based Optimization Methods for Design Information
Chiba, K
Journal of Computational Science and Technology, The Japan Society of Mechanical Engineers, 7, 2, 184-195, Jun. 2013, Peer-reviwed, Invited, Design informatics, which is the efficient design methodology, has three points of view. The first is the efficient exploration in design space using evolutionary-based optimization methods. The second is the structuring and visualizing of design space using data mining techniques. The third is the application to practical problems. In the present study, the influence of the difference among the seven pure and hybrid optimization methods for design information has been investigated in order to explain the selection manner of optimization methods for data mining. The practical problem of a single-stage hybrid rocket is picked up as the present design object. A functional analysis of variance and a self-organizing map are employed as data mining techniques in order to acquire the global information in design space. As a result, mining result depends on not the number of generation (i.e. convergence) but the optimization methods (i.e. diversity). Consequently, the optimization method with diversity performance is the beneficial selection in order to obtain the global design information in design space.
Scientific journal, English - Influence of Difference among Evolutionary-Based Optimization Methods for Design Information
Kazuhisa Chiba; Masahiro Kanazaki
Transaction of the Japanese Society for Evolutionary Computation, 4, 1, 28-37, May 2013, Peer-reviwed
Scientific journal, Japanese - Evolutionary-Based Hybrid Optimizer Applicable to Large-Scale Design Problems
Chiba, K
Journal of Computational Science and Technology, The Japan Society of Mechanical Engineers, 7, 1, 28-37, Apr. 2013, Peer-reviwed, Design Informatics has three points of view. First point is the efficient exploration in design space using evolutionary computation. Second point is the structuring and visualizing of design space using data mining. Third point is the application to practical problems. The investigation of efficient evolutionary-based optimizer for the above first point is essential in order to generate hypothetical database for data mining. In the present study, the performance regarding diversity and convergence has been compared among pure and their hybrid methods using three standard mathematical test problems with/without noise. The result indicates that the hybrid method between the genetic algorithm based on the elitist non-dominated sorting genetic algorithm and the differential evolution is better performance for efficient exploration in the design space under the condition for large-scale engineering design problems within 102 order evolution at most. Moreover, the comparison among eight crossover indicates that the principal component analysis blended crossover is good performance on the hybrid method between the genetic algorithm and the differential evolution.
Scientific journal, English - 設計情報学に懸ける想い
千葉一永
日本機械学会 計算力学部門 ニュースレター Computational Mechanics, 49, 29-31, Dec. 2012, Invited
Japanese - Design-Informatics Approach for Intimate Configuration of Silent Supersonic Technology Demonstrator
Kazuhisa Chiba; Yoshikazu Makino; Takeshi Takatoya
JOURNAL OF AIRCRAFT, AMER INST AERONAUTICS ASTRONAUTICS, 49, 5, 1200-1211, Sep. 2012, Peer-reviwed, Design informatics has been proposed as a method of achieving efficient design. Design informatics allows efficient exploration of the design space and implements conception support for innovative design concepts. In the present study, this approach was applied to the design of the full configuration of the silent supersonic technology demonstrator. The design-informatics approach involves two steps: optimization and data mining. As a first step, multidisciplinary design optimization with multiple objectives was performed considering aerodynamics, stability, structures, aeroelasticity, and boom noise using an evolutionary algorithm. As a second step, data mining was carried out using a self-organizing map and an analysis of variance to extract design knowledge from the acquired optimization results for determining a conclusive compromise solution. Although the optimization had insufficient convergence due to the constraints of time and computational cost, the data mining brought important design information. Since the design space was consequently clarified, a compromise solution was successfully determined. Thus, design informatics is essential to an efficient design process.
Scientific journal, English - Pure and Hybrid Optimizers Applicable to Large-Scale Design Problem
Kazuhisa Chiba
2012 SIXTH INTERNATIONAL CONFERENCE ON GENETIC AND EVOLUTIONARY COMPUTING (ICGEC), IEEE, 409-412, 2012, Peer-reviwed, Design-Informatics has three points of view. One of these points is the investigation of efficient optimization to generate hypothetical database for a large-scale design problem. The results of the present study indicates the hybrid method between differential evolution and genetic algorithm is better performance for efficient exploration in design space under the condition for large-scale engineering design problem within 10(2) order evolution at most.
International conference proceedings, English - Performance Comparison of Evolutionary Algorithms Applied to Hybrid Rocket Problem
Kazuhisa Chiba
6TH INTERNATIONAL CONFERENCE ON SOFT COMPUTING AND INTELLIGENT SYSTEMS, AND THE 13TH INTERNATIONAL SYMPOSIUM ON ADVANCED INTELLIGENT SYSTEMS, IEEE, 1673-1678, 2012, Peer-reviwed, Optimizer is an essence in design-informatics to efficiently obtain nondominated solutions. In the present study, the best optimizer is decided through the competition for the mathematical standard test functions and is also applied to a conceptual design problem of simple single-stage hybrid rocket as the real-world problem. Consequently, a hybrid method between differential evolution and genetic algorithm has good exploration performance. Moreover, the principal component analysis blended crossover and the confidence interval based crossover have good capability on the hybrid method between differential evolution and genetic algorithm.
International conference proceedings, English - Design-informatics approach applicable to real-world problem
Kazuhisa Chiba; Yoshikazu Makino; Takeshi Takatoya
IEEE SSCI 2011 - Symposium Series on Computational Intelligence - MCDM 2011: 2011 IEEE Symposium on Computational Intelligence in Multicriteria Decision-Making, 167-174, 2011, Peer-reviwed, The design-informatics approach has been proposed for next-generation innovative design methodology. The multi-objective problem should be treated in a real-world engineering problem because of the various design requirements. When a multi-objective optimization is implemented, the obtained result is not a sole solution but a set of optimum solutions due to tradeoff relations among design requirements. Therefore, decision-making process is necessary as a post-process for optimization result. In the present study, the design-informatics approach, which is considered as a sequential process between an optimization and its post-process operations, is suggested and is applied to the large-scale and real-world design problem. Consequently, a compromised solution can be efficiently decided from the non-dominated solutions obtained by multidisciplinary design optimization. This approach would be a new efficient procedure for design manner, and also it would be the methodology that innovative design knowledge can be acquired. © 2011 IEEE.
International conference proceedings, English - Multi-Objective Design Exploration and Its Applications
Obayashi, S; Jeong, S; Shimoyama, K; Chiba, K; Morino, H
International Journal of Aeronautical and Space Science, 11, 4, 247-265, 2010, Peer-reviwed, Invited
Scientific journal, English - Knowledge Discovery for Flyback-Booster Aerodynamic Wing Design Using Data Mining
Kazuhisa Chiba; Shigeru Obayashi
JOURNAL OF SPACECRAFT AND ROCKETS, AMER INST AERONAUT ASTRONAUT, 45, 5, 975-987, Sep. 2008, Data mining has been performed on the result,; of an aerodynamic design optimization of a two-stage-to-orbit reusable launch vehicle flyback-booster wing. Three data mining techniques were compared, including selforganizing map, functional analysis of variance, and the rough set theory. The optimization problem had four aerodynamic objective functions and 71 wing shape design variables. The hypothetical design database resulting from the optimization contained a total of 302 solutions which included 102 nondominated solutions. Consequently, the acquired knowledge of the design space consisted of general design characteristics, correlation between objective functions, and the effects of these design variables on the objective functions, for both nondominated as well as all solutions. The comparison also revealed the similarities and differences among the three data mining techniques used in this study. Even though all three techniques discovered detailed design knowledge and the results produced by the combination of all three methods compensated disadvantages of each method when applied individually, it was discovered that the self-organizing map produced the overall best results. Moreover, this study has also shown that the knowledge acquired from both nondominated solutions and from all solutions found was consistent despite the differences between the design spaces. Furthermore, it was shown that data mining is essential for visualizing results of an evolutionary multi-objective optimization problem and extracting useful design knowledge from these results.
Scientific journal, English - Evolutionary-Based Multidisciplinary Design Exploration for the Silent Supersonic Technology Demonstrator Wing
Kazuhisa Chiba; Yoshikazu Makino; Takeshi Takatoya
JOURNAL OF AIRCRAFT, AMER INST AERONAUTICS ASTRONAUTICS, 45, 5, 1481-1494, Sep. 2008, Multidisciplinary design exploration with multiple objectives was performed for the wing shape of a silent supersonic technology demonstrator, considering aerodynamics, structures, and boom noise. Aerodynamic evaluation was carried out by solving Euler equations with computational fluid dynamics, and composite structural evaluation was performed by using Nastran for strength and vibration requirements with computational structural dynamics. The intensity of the sonic boom was evaluated by a modified linear theory. The optimization problem had five objective functions: minimization of the pressure and friction drags, boom intensity at the supersonic condition, and composite structural weight and maximization of the lift at the subsonic low-speed condition. The three-dimensional wing shape defined by 58 design variables was optimized with multi-objective particle swarm optimization and an adaptive-range multi-objective hybrid genetic algorithm method. In the structural evaluation, the combination optimization of stacking sequences of laminated composites was performed for inboard and outboard wings with strength and vibration requirements. Consequently, 75 nondominated solutions were efficiently obtained through 12 generations. Moreover, data mining was performed to obtain the design knowledge for deciding a compromise solution. The data mining revealed useful knowledge in the design space, such as the tradeoff information among the objective functions and the correlations between the objective functions and design variables. A compromise solution was successfully determined by using the obtained physical design knowledge.
Scientific journal, English - PSO/GA Hybrid Method and Its Application to Supersonic-Transport Wing Design
CHIBA Kazuhisa; MAKINO Yoshikazu; TAKATOYA Takeshi
Journal of Computational Science and Technology, The Japan Society of Mechanical Engineers, 2, 1, 268-280, 2008, The hybrid method between multi-objective particle swarm optimization and adaptive range multi-objective genetic algorithm has been developed and its performance has been measured by using three test functions with noise. Moreover, it was applied to a large-scale and real-world engineering design problem. The performance measurement was carried out under the conditions of a small number of population size and generations to apply the practical problem which it needed large computational time for the evaluation. The convergence metric and the cover rate were employed as the measurement manners. Consequently, it revealed that the present hybrid method had similar performance for a simple three-dimensional test problem compared with genetic algorithm in a small number of generations. Moreover, it had the best performance for the test functions with noise. Therefore, the present hybrid method was applied to the wing design of the silent supersonic technology demonstrator. As a result, the efficient design exploration was performed and obtained 75 non-dominated solutions revealed the beneficial knowledge to decide a compromise solution.
English - Knowledge Discovery for Transonic Regional-Jet Wing through Multidisciplinary Design Exploration
Kazuhisa Chiba; Shigeru Obayashi; Hiroyuki Morino
JOURNAL OF ADVANCED MECHANICAL DESIGN SYSTEMS AND MANUFACTURING, JAPAN SOC MECHANICAL ENGINEERS, 2, 3, 396-407, 2008, Data mining is an important facet of solving multi-objective optimization problem. Because it is one of the effective manner to discover the design knowledge in the multi-objective optimization problem which obtains large data. In the present study, data mining has been performed for a large-scale and real-world multidisciplinary design optimization (MDO) to provide knowledge regarding the design space. The MDO among aerodynamics, structures, and aeroelasticity of the regional-jet wing was carried out using high-fidelity evaluation models on the adaptive range multi-objective genetic algorithm. As a result, nine non-dominated solutions were generated and used for tradeoff analysis among three objectives. All solutions evaluated during the evolution were analyzed for the tradeoffs and influence of design variables using a self-organizing map to extract key features of the design space. Although the MDO results showed the inverted gull-wings as non-dominated solutions, one of the key features found by data mining was the non-gull wing geometry. When this knowledge was applied to one optimum solution, the resulting design was found to have better performance compared with the original geometry designed in the conventional manner.
Scientific journal, English - Data mining for multidisciplinary design space of regional-jet wing
Kazuhisa Chiba; Shigeru Obayashi
Journal of Aerospace Computing, Information and Communication, 4, 11, 1019-1036, Nov. 2007, Two data mining techniques have been performed for a large-scale and real-world multidisciplinary design optimization (MDO) results to provide knowledge in design space. The MDO among aerodynamics, structures, and aeroelasticity for a regional-jet wing was carried out using high-fidelity evaluation tools on adaptive range multi-objective genetic algorithm. MDO generated 130 solutions included in nine non-dominated solutions. All solutions were investigated regarding tradeoffs among three objective functions and effects of design variables on objective functions using a self-organizing map (SOM) and a functional analysis of variance (ANOVA) to extract key features of the design space. Consequently, as SOM and ANOVA compensated with respective disadvantages, the design knowledge could be obtained more clearly by the combination between them. Although the MDO result showed the inverted gull-wings as non-dominated solutions, one of the key features revealed by data mining was the non-gull wing geometry. When this knowledge was applied to one optimum solution, the resulting design was found to have better performance compared with the original geometry designed in the conventional manner. Data mining can discover better design due to the salvage of information from design space even when optimization itself does not converge. Copyright © 2007 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
Scientific journal, English - Multidisciplinary design optimization and data mining for transonic regional-jet wing
Kazuhisa Chiba; Akira Oyama; Shigeru Obayashi; Kazuhiro Nakahashi; Hiroyuki Morino
Journal of Aircraft, 44, 4, 1100-1112, Jul. 2007, A large-scale, real-world application of evolutionary multi-objective optimization is reported. The multidisciplinary design optimization among aerodynamics, structures, and aeroelasticity of the wing of a transonic regional-jet aircraft was performed using high-fidelity evaluation models. Euler and Navier-Stokes solvers were employed for aerodynamic evaluation. The commercial software NASTRAN was coupled with a computational fluid dynamics solver for the structural and aeroelastic evaluations. An adaptive range multi-objective genetic algorithm was employed as an optimizer. The objective functions were minimizations of block fuel and maximum takeoff weight in addition to drag divergence between transonic and subsonic flight conditions. As a result, nine nondominated solutions were generated and used for tradeoff analysis among three objectives. Moreover, all solutions evaluated during the evolution were analyzed using a self-organizing map as a data mining technique to extract key features of the design space. One of the key features found by data mining was the nongull wing geometry, although the present multidisciplinary design optimization results showed the inverted gull wings as nondominated solutions. When this knowledge was applied to one optimum solution, the resulting design was found to have better performance and to achieve 3.6% improvement in the block fuel compared to the original geometry designed in the conventional manner. Copyright © 2005 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
International conference proceedings, English - Multi-Objective Design Exploration and its application to regional-jet wing design
Shigeru Obayashi; Shinkyu Jeong; Kazuhisa Chiba; Hiroyuki Morino
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, JAPAN SOC AERONAUT SPACE SCI, 50, 167, 1-8, May 2007, A new approach, Multi-Objective Design Exploration (MODE), is presented to address multidisciplinary design optimization (MDO) problems using computational fluid dynamics-computational structural dynamics (CFD-CSD) coupling. MODE reveals the structure of the design space from the trade-off information and visualizes it as a panorama for Decision Maker. The present form of MODE consists of the Kriging Model, adaptive range multi objective genetic algorithms, analysis of variance and a self-organizing map. The main emphasis of this approach is visual data mining. An MDO system using high-fidelity simulation codes, a Navier-Stokes solver and NASTRAN has been developed and applied to a regional-jet wing design. Because the optimization system becomes very expensive cornputationally, only brief exploration of the design space has been performed. However, visual data mining results demonstrate that design knowledge can produce a good design even after brief design exploration.
Scientific journal, English - Knowledge Discovery in Multidisciplinary Design Space for Regional-Jet Wings Using Data Mining
CHIBA Kazuhisa; JEONG Shinkyu; OBAYASHI Shigeru
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 50, 169, 181-192, 2007, Data mining is an important facet of solving multi-objective optimization problems. In the present study, two data mining techniques were applied to a large-scale, real-world multidisciplinary design optimization (MDO) problem to provide knowledge regarding the design space. The use of MDO in the aerodynamics, structure, and aeroelasticity of a regional-jet wing was carried out using high-fidelity evaluation models with an adaptive range multi-objective genetic algorithm. As a result, nine non-dominated solutions were generated and used for tradeoff analysis of three objectives. All solutions evaluated during the evolution were analyzed for the influence of design variables using a self-organizing map (SOM) and a functional analysis of variance (ANOVA) to extract key features of the design space. As SOM and ANOVA compensate for respective disadvantages, the design knowledge could be obtained more clearly by combinating them. Although the MDO results showed inverted gull-wings as non-dominated solutions, one of the key features found by data mining was a non-gull wing geometry. When this knowledge was applied to one optimum solution, the resulting design was found to have better performance compared with the original geometry designed in the conventional manner.
English - Design Optimization of Shielding Effect for Aircraft Engine Noise
CHIBA Kazuhisa; IMAMURA Taro; AMEMIYA Kazuhisa; YAMAMOTO Kazuomi
JEE, The Japan Society of Mechanical Engineers, 2, 3, 567-577, 2007, The present study is a technical report of the multi-objective design optimization of the two-dimensional shielding effect for the reduction of aircraft engine fan noise. The design optimization has been performed for the simplified cross section of aircraft with fuselage and plane wing. Two objective functions are considered for minimizing the sound pressure level at the side and the bottom locations relative to the fuselage, where standard measuring locations are defined by International Civil Aviation Organization. Those values are evaluated by using the linearized Euler equations. Since a wing, which is defined as a plate without thickness, is assumed as a V-tail wing, it is described by using the length and cant angle relative to the fuselage. The kriging-based response surface model is selected as an optimizer for the reduction of optimization cost. As a result, it is revealed that engine fan noise described by a monopole sound source is reduced by the shielding effect. Moreover, there is no tradeoff between two objective functions, i.e., the sound pressure levels at the side and the bottom measuring locations can be simultaneously reduced. As it is better that the wing length is as long as possible, the cant angle is essential for the shielding effect to reduce engine fan noise.
English - Open-Type Separation on Delta Wings for Leading-Edge Bluntness
CHIBA Kazuhisa; OBAYASHI Shigeru; NAKAHASHI Kazuhiro
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 50, 168, 81-87, 2007, A numerical simulation was carried out corresponding to recent experiments using delta wings with sharp and blunt leading-edges, which indicates the second primary vortex, at NASA Langley Research Center. However, the experimental data did not reveal the detailed physical phenomena regarding the second primary vortex, because the experiment used only on-the-body-surface data. In the present study, the physical phenomena were revealed using Reynolds-averaged Navier-Stokes computations with three one-equation turbulence models on an unstructured hybrid mesh. The adaptive mesh refinement method in the vicinity of the vortex center was also applied to have more mesh resolution. Consequently, the result quantitatively revealed that appropriate modeling regarding turbulent kinematic viscosity was significant. Moreover, the three-dimensional visualization of the computational fluid dynamics results suggested that the second primary vortex was a developing shear layer merging into an open-type separation generated late by the primary vortex.
English - Multidisciplinary design exploration of wing shape for silent supersonic technology demonstrator
Kazuhisa Chiba; Yoshikazu Makino; Takeshi Takatoya
Collection of Technical Papers - AIAA Applied Aerodynamics Conference, American Institute of Aeronautics and Astronautics Inc., 2, 960-978, 2007, Multidisciplinary design exploration with multi-objectives has been performed for the wing shape of a silent supersonic technology demonstrator among aerodynamics, structures, and boom noise. Aerodynamic evaluation was carried out by using Euler computation on computational fluid dynamics, and composite structural evaluation was performed by using NASTRAN for strength and vibration requirements on computational structural dynamics. The intensity of sonic boom was evaluated by a modified linear theory. The optimization problem had five objective functions as the minimizations of the pressure/friction drags and the boom intensity at supersonic condition, and the composite structural weight as well as the maximization of the lift at subsonic condition. The three-dimensional wing shape defined by 58 design variables was optimized on particle swarm optimization and genetic algorithm hybrid method. In the structural evaluation, the combination optimization of stacking sequences of laminated composites was performed for in/outboard wings with strength and vibration requirements, respectively. Moreover, since the result of a multi-objective optimization problem is not a sole solution but an optimum set due to tradeoffs, data mining was performed to decide a compromise solution. Consequently, 75 non-dominated solutions were obtained. The data mining revealed the knowledge in the design space, such as the relations among the objectives, and the correlations among objectives and design variables. A compromise solution was determined through data mining. Copyright © 2007 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
International conference proceedings, English - Design exploration of aerodynamic wing shape for reusable launch vehicle flyback booster
K Chiba; S Obayashi; K Nakahashi
JOURNAL OF AIRCRAFT, AMER INST AERONAUT ASTRONAUT, 43, 3, 832-836, May 2006
Scientific journal, English - Tradeoff Analysis and Data Mining of Aerodynamic Wing Design for RLV Flyback Booster
K.CHIBA; S.OBAYASHI AND; K.NAKAHASHI
REPORTS OF THE INSTITUTE OF FLUID SCIENCE TOHOKU UNIVERSITY, 17, 14 Feb. 2006
Research institution, English - Design Exploration of Aerodynamic Wing Shape for RLV Flyback Booster
CHIBA Kazuhisa; OBAYASHI Shigeru; NAKAHASHI Kazuhiro
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 54, 627, 144-150, 2006, The wing shape of flyback booster for a Two-Stage-To-Orbit reusable launch vehicle has been optimized considering four objectives. The objectives are to minimize the shift of aerodynamic center between supersonic and transonic conditions, transonic pitching moment and transonic drag coefficient, as well as to maximize subsonic lift coefficient. The three-dimensional Reynolds-averaged Navier-Stokes computation using the modified Spalart-Allmaras one-equation model is used in aerodynamic evaluation accounting for possible flow separations. Adaptive range multi-objective genetic algorithm is used for the present study because tradeoff can be obtained using a smaller number of individuals than conventional multi-objective genetic algorithms. Consequently, four-objective optimization has produced 102 non-dominated solutions, which represent tradeoff information among four objective functions. Moreover, Self-Organizing Maps have been used to analyze the present non-dominated solutions and to visualize tradeoffs and influence of design variables to the four objectives. Self-Organizing Maps contoured by the four objective functions and design variables are found to visualize tradeoffs and effects of each design variable.
Japanese - Knowledge discovery in aerodynamic design space for flyback-booster wing using data mining
Kazuhisa Chiba; Shinkyu Jeong; Shigeru Obayashi; Kazuomi Yamamoto
A Collection of Technical Papers - 14th AIAA/AHI International Space Planes and Hypersonic Systems and Technologies Conference, American Institute of Aeronautics and Astronautics Inc., 1, 806-823, 2006, The data mining has been performed for the aerodynamic design optimization result of two-stage-to-orbit reusable launch vehicle flyback booster wing. Three data mining techniques were used such as self-organizing map, functional analysis of variance, and rough set theory. The optimization problem had four aerodynamic objective functions and 71 design variables regarding wing shape. The optimization obtained the result as the hypothetical design database with 302 all solutions including the 102 non-dominated solutions. Consequently, the knowledge in the design space was acquired regarding the correlation between objective functions, and the influence of the design variables to the objective function, for non-dominated and all evaluated solutions, respectively. The features of three data mining techniques were revealed. Although the combination among three techniques discovered detailed design knowledge, self-organizing map was especially a key technique for knowledge discovery. Moreover, design knowledge from all solutions conserved the information from non-dominated solutions. Data mining was essential to solve multi-objective optimization problem. Copyright © 2006 by the American Institute of Aeronautics and Astronautics, Inc. All rignts reserved.
International conference proceedings, English - Data Mining for Aerodynamic Design Space
JEONG S.
J. Aerospace Comput. Inform. Commun., 2, 11, 452-469, 2005 - 613 Multidisciplinary Design Optimization for Transonic Regional Jet Aircraft
CHIBA Kazuhisa; OBAYASHI Shigeru; NAKAHASHI Kazuhiro; MORINO Hiroyuki
The proceedings of the JSME annual meeting, The Japan Society of Mechanical Engineers, 2005, 51-52, 2005, A large-scale, real-world application of Evolutionary Multi-Objective Optimization is reported. The Multidisciplinary Design Optimization among aerodynamics, structures, and aeroelasticity of the transonic regional-jet wing was performed using high-fidelity evaluation models. Euler and Navier-Stokes solvers were employed for aerodynamic evaluation. The commercial software NASTRAN was coupled with a Computational Fluid Dynamics solver for the structural and aeroelastic evaluations. Adaptive Range Multi-Objective Genetic Algorithm was employed as an optimizer. The objective functions were minimizations of block fuel and maximum takeoff weight in addition to drag divergence between transonic and subsonic flight conditions. As a result, nine non-dominated solutions were generated and tradeoff information among three objectives was revealed.
Japanese - Tradeoff analysis of aerodynamic wing design for RLV
K Chiba; S Obayashi; K Nakahashi
Parallel Computational Fluid Dynamics: Multidisciplinary Applications, ELSEVIER SCIENCE BV, 129-136, 2005, Peer-reviwed, The wing shape of flyback booster for a Two-Stage-To-Orbit reusable launch vehicle has been optimized considering four objectives. The objectives are to minimize the shift of aerodynamic center between supersonic and transonic conditions, transonic pitching moment. and transonic drag coefficient, as well as to maximize subsonic lift coefficient. The three-dimensional Reynolds-averaged Navier-Stokes computation using the modified Spalart-Allmaras one-equation model is used in aerodynamic evaluation accounting for possible flow separations. Adaptive range multi-objective genetic algorithm is used for the present study because tradeoff can be obtained using a smaller number of individuals than conventional multi-objective genetic algorithms. Consequently, four-objective optimization has produced 102 non-dominated solutions, which represent tradeoff information among four objective functions. Moreover, Self-Organizing Maps have been used to analyze the present non-dominated solutions and to visualize tradeoffs and influence of design variables to the four objectives. Self-Organizing Maps contoured by the foul. objective functions and design variables are found to visualize tradeoffs and effects of each design variable.
International conference proceedings, English - High-fidelity Multidisciplinary design optimization of wing shape for regional jet aircraft
K Chiba; S Obayashi; K Nakahashi; H Morino
EVOLUTIONARY MULTI-CRITERION OPTIMIZATION, SPRINGER-VERLAG BERLIN, 3410, 621-635, 2005, A large-scale, real-world application of Evolutionary Multi-Criterion Optimization (EMO) is reported in this paper. The Multidisciplinary Design Optimization among aerodynamics, structures and aeroelasticity for the wing of a transonic regional jet aircraft has been performed using high-fidelity models. An Euler/Navier-Stokes (N-S) Computational Fluid Dynamics (CFD) solver is employed for the aerodynamic evaluation. The NASTRAN, a commercial software, is coupled with a CFD solver for the structural and aeroelastic evaluations. Adaptive Range Multi-Objective Genetic Algorithm is employed as an optimizer. The objective functions are minimizations of block fuel and maximum takeoff weight in addition to difference in the drag between transonic and subsonic flight conditions. As a result, nine non-dominated solutions have been generated. They are used for tradeoff analysis among three objectives. One solution is found to have one percent improvement in the block fuel compared to the original geometry designed in the conventional manner. All the solutions evaluated during the evolution are analyzed by Self-Organizing Map to extract key features of the design space.
Scientific journal, English - CFD Visualization of Second Primary Vortex Structure on a 65-Degree Delta Wing
K.CHIBA; S.OBAYASHI; K.NAKAHASHI
REPORTS OF THE INSTITUTE OF FLUID SCIENCE TOHOKU UNVERSITY, 16, 1-10, Jun. 2004
Research institution, English - Visual Data Mining for Vortex Structure of Leading-Edge Separation at High Reynolds Numbers
Chiba Kazuhisa; Obayashi Shigeru
The proceedings of the JSME annual meeting, The Japan Society of Mechanical Engineers, 2003, 217-218, 2003, Unstructured hybrid grids with 3 turbulence models are applied to simulate experiment about flows around delta wings with a blunt leading edge at Reynolds number of 6 millions. The modified S-A turbulence model is found effective to capture complex vortex structure. The second primary vortex at the inboard of the first primary vortex is captured numerically as reported in the experiment. Its structure is investigated by using CFD visualization.
Japanese
MISC
- Aerodynamic discrepancies of an aircraft considering the running engine
Mueller, J; Chiba, K; Oba, Y; Obayashi, S
Corresponding, Nov. 2024, English, Invited - Multi-wingletのcant角変更による空力変化メカニズム
小林 英里奈; 千葉 一永; 金崎 雅博
Corresponding, Jul. 2024, 第56回流体力学講演会/第42回航空宇宙数値シミュレーション技術シンポジウム, Japanese, Summary national conference - Identification of Losses from Engine-Airframe Interaction for a Passenger Aircraft through Integrated Simulation
Mueller, J; Chiba, K; Oba, Y
Corresponding, Jun. 2024, The 9th European Congress on Computational Methods in Applied Sciences and Engineering, English, Peer-reviwed, Summary international conference - Influences of Multiple Winglets on the Aerodynamic Performance and Flow Field of an Aircraft
Kobayashi, E; Chiba, K; Kanazaki, M
Corresponding, Jun. 2024, The 9th European Congress on Computational Methods in Applied Sciences and Engineering, English, Peer-reviwed, Summary international conference - Multi-wingletによる航空機の空力性能および流れ場への影響
小林 英里奈; 千葉 一永; 金崎 雅博
Corresponding, Apr. 2024, 日本航空宇宙学会第55期年会講演会, Japanese, Summary national conference - Sliding mesh法による稼働エンジンと機体の統合解析
千葉 一永; Mueller, Jan; 大庭 芳則
Lead, 19 Jan. 2024, 令和5年度航空宇宙空力シンポジウム, Japanese, Summary national conference - 設計変数空間での非劣解の多様性を確保する交叉の開発
門馬 圭吾; 大山 聖; 千葉 一永
Last, 22 Dec. 2023, 進化計算学会進化計算シンポジウム2023, Japanese, Summary national conference - Sliding mesh法による航空機体と稼働エンジンの統合解析
Mueller, Jan; 千葉 一永; 大庭 芳則
Corresponding, 15 Dec. 2023, 第37回数値流体力学シンポジウム, Japanese, Summary national conference - 悪天候回避時における航空機の飛行経路と気象データの相関分析
横濱 こころ; 中村 陽一; 瀬之口 敦; 千葉 一永
Last, 15 Nov. 2023, 第61回飛行機シンポジウム, Japanese, Summary national conference - Aerodynamic Effect of Engine Exhaust on Aircraft Whole Body - Integrated Analysis of Airframe and Running Engine Using Sliding-Mesh Method
Mueller, J; Chiba, K; Oba, Y; Obayashi, S
Corresponding, 08 Nov. 2023, Proceedings on 20th International Conference on Flow Dynamics, English, Invited, Summary international conference - Aerodynamic Efficacy of Changing the Chordwise Installation Position of Multi-Winglet on Commercial Aircraft
Kobayashi, E; Chiba, K
Last, 16 Oct. 2023, Proceedings on Asia-Pacific International Symposium on Aerospace Technology, English, Peer-reviwed, Summary international conference - Influence of the Engine Exhaust on the Wing Pressure Distribution Computed with an Integrated Simulation of Airframe and Running Engine
Mueller, J; Chiba, K; Oba, Y
Corresponding, Jun. 2023, AIAA AVIATION 2023, 1, 1, English, Peer-reviwed, Summary international conference - Influence of Engine Exhaust on Wing Underside Flow for a Passanger Aircraft
Mueller, J; Chiba, K; Oba, Y
Corresponding, IACM, 25 Apr. 2023, 22nd Computational Fluids Conference, 1, 1-8, English, Peer-reviwed, Summary international conference, True - Feedback-Circulating Desgin Space Exploration by Multi-Sampling Kriging Model: Exploitation for the Lift Rise by an Aircraft Flap with Yaw-Wise Rotation
Chiba, K; Kanazaki, M
Lead, 24 Apr. 2023, 7th International Conference on Intelligent Systems, Metaheuristics & Swarm Intelligence, 1, 1-5, English, Peer-reviwed, Summary international conference - 複数枚ウィングレット取付位置変更による民間航空機の空力性能向上効果
小林 英里奈; 千葉 一永
Last, 14 Apr. 2023, 日本航空宇宙学会第54期年会講演会, Japanese, Summary national conference - 航空機の悪天回避経路予測に向けた乱気流指数の有用性検討
横濱 こころ; 中村 陽一; 瀬之口 敦; 千葉 一永
Last, 13 Apr. 2023, 日本航空宇宙学会第54期年会講演会, Japanese, Summary national conference - 航空機の悪天回避経路生成に向けた乱気流指数の活用の検討—Application of Turbulence Index for Generating Severe Weather Avoidance Routes of Aircraft
横濱 こころ; 中村 陽一; 瀬之口 敦; 千葉 一永
[東京] : 日本航空宇宙学会, Apr. 2023, 年会講演会 = JSASS annual meeting, 54, 6p, Japanese, AA12394237 - 航空機の作動エンジンとエアフレームの統合解析
千葉 一永; Mueller Jan; 大庭 芳則
Lead, 06 Jan. 2023, 2023年度航空宇宙空力シンポジウム, Japanese, Invited, Lecture materials - 航空機翼面圧力分布に対する作動エンジンの空力的影響
千葉 一永; Mueller Jan; 大庭 芳則
Lead, 14 Dec. 2022, 第36回数値流体力学シンポジウム, Japanese, Summary national conference - Effect of Pressure Recovery on the Lower Surfaces of Multiple Winglets by Changing the Main Wing Airfoil of an Aircraft
Kobayashi, E; Chiba, K
Last, 28 Nov. 2022, AIAA 2022 Region VII Student Conference, 1-10, English, Peer-reviwed, Summary international conference, True - 航空機主翼の翼型変更による複数枚ウィングレット下面の圧力回復効果
小林 英里奈; 千葉 一永
Last, 13 Nov. 2022, 日本機械学会第100期流体工学部門講演会, Japanese, Summary national conference - Influences of Changing the Installing Positions of Multiple Winglets on Aerodynamic Characteristics
Kobayashi, E; Chiba, K
Last, 04 Sep. 2022, 33rd Congress of the International Council of the Aeronautical Sciences, 1-10, English, Peer-reviwed, Summary international conference, True - Integrated Analysis of Operating Engine and Airframe for High-Fidelity Wing Load Estimation
Chiba, K; Oba, Y
Lead, 31 Jul. 2022, 15th World Congress on Computational Mechanics, 1-2, English, Peer-reviwed, Invited, Summary international conference, False - 設計変数空間における非劣解の多様性に対する交叉の影響
門馬 圭吾; 佐藤 元紀; 大山 聖; 海野 大; 千葉 一永
Last, 17 Mar. 2022, 進化計算学会第21回研究会, Japanese, Summary national conference - Feedback-Circulating Optimum Design for Perceiving Constellation Principle of Regional Observation Satellites
Machii, K; Chiba, K; Kawakatsu, Y
Corresponding, IEEE, 04 Dec. 2021, IEEE Symposium Series on Computational Intelligence, 1-8, English, Peer-reviwed, Summary international conference, True - 遠隔フィードバック制御による風洞試験翼模型形態連続変更での空力データの掃引取得
脇本 研; 千葉 一永; 加藤 裕之; 中北 和之
Corresponding, 30 Nov. 2021, 第59回飛行機シンポジウム, Japanese, Summary national conference - Acquisition of Swept Aerodynamic Data by Consecutive Change of Wing Model Configuration in Wind Tunnel Tests Using Remote and Feedback Control
Wakimoto, K; Chiba, K; Kato, H; Nakakita, K
Corresponding, 23 Nov. 2021, Aerospace Europe Conference 2021, 1-11, English, Peer-reviwed, Summary international conference, True - Influence of Crewed Mars Ascent Vehicle Auxiliary Member on Aerodynamic Drag in Numerical Analysis
Kubota, I; Chiba, K
Last, 15 Nov. 2021, 2021 Asia-Pacific International Symposium on Aerospace Technology, 1-4, English, Peer-reviwed, Summary international conference, True - 複数標本点追加型Krigingモデルによる航空機yaw方向回転付加フラップの揚力向上域探査
千葉 一永; 金崎 雅博
Lead, 21 Sep. 2021, 日本機械学会第34回計算力学講演会, Japanese, Summary national conference - 地域観測衛星コンステレーションのフィードバック循環型最適軌道設計
町井 佳菜子; 千葉 一永; 川勝 康弘
Corresponding, 15 Sep. 2021, 日本機械学会第31回設計工学・システム部門講演会, Japanese, Summary national conference - Lift Rise Spots Exploration of a Yaw-wise Rotational Flap by Enhanced-Kriging-based Efficient Global Optimization
Chiba, K; Kanazaki, M
Lead, Springer, 21 Jun. 2021, International Conference on Optimization and Learning, English, Peer-reviwed, Summary international conference, True - Satellite Constellation Orbit Design to Observe Regional Coverage by Metaheuristics
Machii, K., Chiba, K., and Kawakatsu, Y.
10 Apr. 2021, 5th International Conference on Intelligent Systems, Metaheuristics & Swarm Intelligence, 1, 1, English, Peer-reviwed, True - 設計情報学を利用した航空宇宙分野での非定常データ解析に向けた新たな試み
千葉一永; 梅田裕平; 濱田直希; 保江かな子
Sep. 2019, 計測と制御, 58, 9, 699‐702(J‐STAGE), Japanese, Peer-reviwed, Introduction scientific journal, 0453-4662, 201902261261688722 - Hypervolume-Based Evolutionary Many-Disciplinary Design Optimization of Blended-Wing-Body-Type Flyback Booster
Tsuyoshi Sumimoto; Kazuhisa Chiba; Masahiro Kanazaki
We have implemented the design optimization of the three-dimensional geometry for a two-stage-to-orbit flyback booster under six objective functions regarding aerodynamics, aerodynamic heating, and structures to obtain the knowledge for designing reusable launch vehicle. It is important to view the relationship among the objective functions of other fields with aerodynamic heating under designing spacecraft. We defined many-objective problem to execute more realistic configuration design based on WIRES of Kyushu Institute of Technology and feedback the design knowledge. Accordingly, we used evolutionary computation as the optimization method and applied IBEA as evolutionary algorithm, which has appropriate result in many-objective optimization for searching design variables space and getting design information. Moreover, data analysis was carried out for the optimization result to reveal information in the design space. Consequently, we need to consider the strictly different design strategy for the speed range between the transonic and the supersonic as well as hypersonic conditions. We also revealed that the design strategy of configuration which improve each objective functions., IEEE, 2018, 2018 IEEE SYMPOSIUM SERIES ON COMPUTATIONAL INTELLIGENCE (IEEE SSCI), 1331-1338, English, WOS:000459238800182 - Aerodynamic effect of aircraft flap with yaw-rotational degree of freedom
Tatsuro Komatsu; Kazuhisa Chiba
In this paper, fluid numerical calculations were carried out to investigate the aerodynamic performance when yaw rotational degree of freedom is added to the flap. First, I made three meshes and discussed from a comparison of aerodynamic coefficients and visualization result of pressure coefficient distribution to investigate the influence of the mesh density on aerodynamic characteristics. since the same results was showed as mesh with the finest mesh density, we used medium mesh for the investigation of the aerodynamic performance when yaw rotational degree of freedom is added to the flap. Next, I created four models with different yaw-rotational angles of flap and performed calculation assuming uniform flow to investigate the effect of flap with rotational angle. The aerodynamic coefficient and the visualization result were similarly compared and discussed. As a result, lift coefficient is increased by setting appropriate yaw rotational angle to flap., American Institute of Aeronautics and Astronautics Inc, AIAA, 2018, AIAA Aerospace Sciences Meeting, 2018, 210059, English, Peer-reviwed, 85044387688 - Determination of temporal and spatial origination of transonic buffet via unsteady data mining
Kazuhisa Chiba; Yuhei Umeda; Naoki Hamada; Shinya Watanabe; Masaya Nakata; Kanako Yasue; Koji Suzuki; Takashi Atobe; Shigeru Kuchi-Ishi; Kazuyuki Nakakita; Takeshi Ito
The Betti sequence which is one of the topological data analysis has been applied to the time series dataset in which a transonic buffet occurred. In this project, we aim to find temporal and spatial originations of transonic buffet by data analyses, therefore, numerical fluid analysis is performed by unsteady detached eddy simulation which sweeps angle of attack, then datasets are created. In this paper, as the first trial, we set up six monitoring points in the vicinity where the transonic buffet passes on the wing upper surface
the Betti sequence was applied to the x-directional velocity and the pressure. As a result, on the wing surface, the Betti sequence only responded to the pulse of the physical quantity, as the disturbance of the physical quantities by the separation behind the shockwave and that by the transonic buffet are similar. Other monitoring points should be provided outside the separation region., American Institute of Aeronautics and Astronautics Inc, AIAA, 2018, AIAA Aerospace Sciences Meeting, 2018, 210059, AIAA Paper-2018-0036, English, Peer-reviwed, 85044379012 - A scatterplots selection technique for multi-dimensional data visualization combining with parallel coordinate plots
Ayaka Watanabe; Takayuki Itoh; Kazuhisa Chiba; Masahiro Kanazaki
We have previously presented a visualization technique which represents multi-dimensional data as collection of lowdimensional parallel coordinate plots. This paper presents a general-purpose extension of the visualization technique which represents multi-dimensional data as a combination of the scatterplots with parallel coordinate plots. We aim to automatically select a small number of pairs of variables which are estimated that they bring interesting visualization by scatterplots. This paper also presents an application of this visualization technique to Multi-objective optimization of manufacturing design. Our multi-dimensional data visualization technique effectively assists us to understand the distribution and correlation of design variables and objective functions in multi-objective optimization processes., Institute of Electrical and Electronics Engineers Inc., 14 Nov. 2017, Proceedings - 2017 21st International Conference Information Visualisation, iV 2017, 78-83, English, Peer-reviwed, 85040571508, WOS:000419271000012 - Design informatics and its drive:Toward clarifying unsteady physical phenomena
CHIBA Kazuhisa; ITO Takeshi; WATANABE Shinya; NAKATA Masaya; UMEDA Yuhei; HAMADA Naoki; YASUE Kanako; SUZUKI Koji; KUCHI-ISHI Shigeru; NAKAKITA Kazuyuki
<p>The transonic buffet degrades the aerodynamic performance of the aircraft during cruise. It is a phenomenon that should be avoided absolutely as it may lead to accidents. However, the mechanism of occurrence has yet to be elucidated. To understand this phenomenon, large-scale unsteady data is accumulated using computational fluid dynamics. In contrast, data mining of time series data such as unsteady data is a topic of the future in that field. In this study, we attempted mining unsteady data with capacity exceeding Tera's order. As a result, the behavior of the physical quantity is suggested to be different from the data just before the transonic buffet occurs. Based on this result, we visualized the data over time, and found that the characteristic change of the viscosity distribution of the wing surface can be seen. This should be a clue to elucidate this phenomenon.</p>, 一般社団法人 日本機械学会, Sep. 2017, The Proceedings of Mechanical Engineering Congress, Japan, 2017, 0, ROMBUNNO.F011002, Japanese, 201802223721128847, 130006549800 - Knee point analysis of many-objective Pareto fronts based on Reeb graph
Naoki Hamada; Kazuhisa Chiba
In many-objective optimization, the dimensionality of Pareto fronts becomes higher than three, and extracting preferable points for the decision maker is a key issue in the post-optimal analysis. The aim of this study is to develop a method to detect and visualize high-dimensional knee points. We propose a new definition of knee point and a graph-based approach to detect our knee points with a visualization of the geometry of the whole Pareto front. Our method is examined via Pareto front samples of synthetic problems and a real-world airplane design., Institute of Electrical and Electronics Engineers Inc., 05 Jul. 2017, 2017 IEEE Congress on Evolutionary Computation, CEC 2017 - Proceedings, 1603-1612, English, Peer-reviwed, 85028502815 - An Attempt for Detecting Transonic Buffet Signature via Unsteady Data Mining
Kazuhisa Chiba; Shinya Watanabe; Masaya Nakata; Yuhei Umeda; Naoki Hamada; Kanako Yasue; Koji Suzuki; Shigeru Kuchi-ishi; Kazuyuki Nakakita; Takeshi Ito
Jul. 2017, Proceedings of the 2017 World Congress in Computer Science, Computer Engineering, and Applied Computing, The 13th International Conference on Data Mining, English, Peer-reviwed - 非定常空力現象兆候検出へのデータマイニング試行
Kazuhisa Chiba; Shinya Watanabe; Masaya Nakata; Yuhei Umeda; Naoki Hamada; Kanako Yasue; Koji Suzuki; Shigeru Kuchi-ishi; Kazuyuki Nakakita; Takeshi Ito
Jun. 2017, 第49回流体力学講演会/第35回航空宇宙数値シミュレーション技術シンポジウム, Japanese - Stability measurement of mooring hybrid airship by image processing
柳田 大輝; 池田 悠登; 佐鳥 新; 千葉 一永; 三橋 龍一
日本航空宇宙学会, 13 Apr. 2017, 年会講演会講演集, 48, 4p, Japanese, 40021165203, AA12394237 - From Extraction to Generation of Design Information Paradigm Shift in Data Mining via Evolutionary Learning Classifier System
Kazuhisa Chiba; Masaya Nakata
This paper aims at generating as well as extracting design strategies for a real world problem using an evolutionary learning classifier system. Data mining for a design optimization result as a virtual database specifies design information and discovers latent design knowledge. It is essential for decision making in real world problems. Although we employed several methods from classic statistics to artificial intelligence to obtain design information from optimization results, we may not cognize anything beyond a prepared database. In this study, we have applied an evolutionary learning classifier system as a data mining technique to a real world engineering problem. Consequently, not only it extracted known design information but also it successfully generated design strategies not to extract from the database. The generated design rules do not physically become innovative knowledge because the prepared dataset include Pareto solutions owing to complete exploration to the edge of the feasible region in the optimization. However, this problem is independent of the method, our evolutionary learning classifier system is a useful method for incomplete datasets. (C) 2017 The Authors. Published by Elsevier B.V., ELSEVIER SCIENCE BV, 2017, INTERNATIONAL CONFERENCE ON COMPUTATIONAL SCIENCE (ICCS 2017), 108, 1662-1671, English, Peer-reviwed, 1877-0509, WOS:000404959000170 - Feasibility Studies for Fulfillment of Captive High-Altitude Lighter-Than-Air Platform System
NISHIKAWA Ryosuke; CHIBA Kazuhisa; ONDA Masahiko; SATORI Shin; AKIBA Ryojiro
日本航空宇宙学会, 06 Sep. 2016, 宇宙科学技術連合講演会講演集, 60, 3p, Japanese, 1884-1945, 40020932926, AA11800503 - The Space Business Model of Small Satellite Launch By Aerial Launch Platform System
柳田 大輝; 佐鳥 新; 三橋 龍一; 千葉 一永; 伊藤 那知
日本航空宇宙学会, 06 Sep. 2016, 宇宙科学技術連合講演会講演集, 60, 5p, Japanese, 1884-1945, 40020932915, AA11800503 - Multidimensional data visualization for plane design optimization
渡邉 彩華; 伊藤 貴之; 金崎 雅博; 宇津木 基弘; 千葉 一永
日本航空宇宙学会, 14 Apr. 2016, 年会講演会講演集, 47, 6p, Japanese, 40020819413, AA12394237 - Influence of Chordwise Location on the Aerodynamic Performance of Fins Vertically Mounted over the Wing
高梨 聡; 大森 太加; 砂田 保人; 今村 太郎; 金崎 雅博; 千葉 一永; 松野 隆
日本航空宇宙学会, 14 Apr. 2016, 年会講演会講演集, 47, 7p, Japanese, 40020818736, AA12394237 - Climbing trajectory prediction of high-altitude captive LTA Platform System
NISHIKAWA Ryosuke; CHIBA Kazuhisa; ONDA Masahiko; SATORI Shin; AKIBA Ryojiro
日本航空宇宙学会, 14 Apr. 2016, 年会講演会講演集, 47, 7p, Japanese, 40020819546, AA12394237 - Ascendancy of extinction-reignition on single-stage hybrid sounding rocket in view of fuels
Kazuhisa Chiba; Hideyuki Yoda; Shoma Ito; Masahiro Kanazaki; Shin’ya Watanabe; Koki Kitagawa; Toru Shimada
© 2016 by Authors.A single-stage launch vehicle with hybrid rocket engine has been conceptually designed by using design informatics, which has three points of view, i.e., problem definition, optimization, and data mining. The primary objective of the present design is that the downrange and the duration time in the lower thermosphere are sufficiently secured for the aurora scientific observation, whereas the initial gross weight is held down to the extent possible. The multidisciplinary design optimization was performed by using a hybrid evolutionary computation. Data mining was also implemented by using a scatter plot matrix. Polypropylene and liquid oxygen with swirling flow are adopted as solid fuel and liquid oxidizer, respectively. The condition of two-time ignitions is assumed in fight sequence on the equation of motion for the three degree of freedom rigid body. Consequently, the design information regarding the tradeoffs, the behaviors of the design variables in the design space to become the nondominated solutions, and the implication of the design variables for the objective functions have been obtained quantitatively. The structurization and visualization of the design space has been implemented in order to observe the effectiveness of the local regions of each design variable. The advantage of extinction-reignition has been indicated., 01 Jan. 2016, 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 84958559299 - 設計者の要求に基づく非劣解分析支援システムの提案
中野 翔; 渡邉 真也; 千葉 一永; 金崎 雅博; 棟朝 雅晴
多目的最適化によって得られた非劣解集合に対して設計者側の要求に基づいた傾向分析を実現する新たな分析支援システムの提案を行う．本システムは，従来までの相関ルールに基づく分析アプローチを改良したものであり，設計者側からの要求に即したルール抽出に特化することで，設計者の知りたい傾向をピンポイントで抽出することが可能となっている．, 計測自動制御学会, 18 Nov. 2015, 計測自動制御学会システム・情報部門学術講演会講演論文集, 2015, 631-635, Japanese, 120006671865 - アンライセンスバンドを用いた係留式高層プラットフォームとの通信
三橋龍一; 高嶋竜也; 佐鳥新; 佐々木正巳; 平元理峰; 千葉一永; 佐々木順也; 秋葉鐐二郎
07 Nov. 2015, 電気・情報関係学会北海道支部連合大会講演論文集(CD-ROM), 2015, ROMBUNNO.42, Japanese, 201502212136544818 - 係留式高層プラットフォームシステムが持つ空力性能の系挙動に対する感度
CHIBA Kazuhisa; ONDA Masahiko; SATORI Shin
日本航空宇宙学会, 07 Oct. 2015, 宇宙科学技術連合講演会講演集, 59, 6p, English, 1884-1945, 40020616478, AA11800503 - J0440305 Hardware-based Correction of Inclination on Multi-Spectral Image for Precision Agriculture by Small-Type Unmanned Arial Vehicle
SAITO Shin-nosuke; ITO Tomonori; SATORI Shin; CHIBA Kazuhisa
This paper describes the development of the correction system for multi-spectral image inclination on a small-type unmanned aerial vehicle; the correction system was demonstrated. The present system performed the attitude control of vehicle on the computation for its easy operation using State Regulator Control. The results indicate that the limitation of feasibility for control on the present system; the next assignments can be revealed. The cause that a vehicle becomes unstable has been revealed in the equations of motion., The Japan Society of Mechanical Engineers, 13 Sep. 2015, Mechanical Engineering Congress, Japan, 2015, "J0440305-1"-"J0440305-5", Japanese, 110010048838, AA12588255 - B-2-27 Conceptual Design of Hybrid Mooring Flying Balloon
Mitsuhashi Ryuichi; Hayasaka Ryosuke; Satori Shin; Hiramoto Riho; Chiba Kazuhisa; Kase Satoshi; Sasaki Junya; Akiba Ryojiro
一般社団法人電子情報通信学会, 24 Feb. 2015, Proceedings of the IEICE General Conference, 2015, 1, 250-250, Japanese, 110009927346, AN10471452 - 主翼上垂直舵翼の平面形と空力特性の関係性に関する実験的研究
高梨聡; 大森太加; 砂田保人; 今村太郎; 金崎雅博; 千葉一永; 松野隆
2015, 流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM), 47th-33rd, 201502214546674622 - 新しい空力デバイスとしての主翼上垂直フィンの可能性について
今村太郎; 大森太加; 高梨聡; 砂田保人; 金崎雅博; 千葉一永; 松野隆
2015, 飛行機シンポジウム講演集(CD-ROM), 53rd, 201502201874992238 - 航空機の突風応答緩和に向けた主翼上垂直舵面の利用に関する実験的研究
大森太加; 高梨聡; 砂田保人; 今村太郎; 松野隆; 千葉一永; 金崎雅博
2015, 飛行機シンポジウム講演集(CD-ROM), 53rd, 201502216609163910 - 将来輸送の持続的開発に向けたAerial Launch Platform/System
山田哲哉; 丸祐介; 佐藤哲也; 佐鳥新; 千葉一永
2015, 宇宙科学技術連合講演会講演集(CD-ROM), 59th, 1884-1945, 201502205703052739 - Motion analysis of captive platform system constructed from airship and tether
Kazuhisa Chiba; Shin Satori; Ryuichi Mitsuhashi; Jun'Ya Sasaki; Ryojiro Akiba
© 2015, American Institute of Aeronautics and Astronautics Inc. All rights received.The existence of a platform at the stratosphere is expected to be the role to gain a foothold in space. When the platform is employed airship in, it is transported by advection due to its lighter-than-air body. Thereupon, a mooring of platform is reasonable in order to incarnate _xed-point platform. Conception of a captive platform system is similar to the Rockoon one which rendered remarkable services for the space observation of the early days. Therefore, the application of captive platform system to the launch site is highly expected in order to realize the space transportation system with a large quantity and high frequency. In this study, the motion of a captive platform system constructed from an airship and tethers is analyzed in order to ensure that the motion of a captive platform system is practically incarnated. Moreover, the sensitivities of aerodynamic performance and buoyancy of the airship is observed. Consequently, the practically incarnated motion of a captive platform system has been identi_ed under the condition of the storm environment. Furthermore, the reduction of the advection distance driven away by the storm has been quantitatively indicated under the different conditions of aerodynamic performance and buoyancy of the airship. The sensitivities of the lift and buoyancy of the airship for the motion of a system has been revealed in order to conceptually design airship geometry., 01 Jan. 2015, AIAA Infotech at Aerospace, 84937819304 - Evolutionary Algorithm Applied to Ballistic Launch Vehicle Design Using Hybrid Rocket Engine Evaluated by Enhanced Flight Simulation
Hideyuki Yoda; Shoma Ito; Masahiro Kanazaki; Kazuhisa Chiba; Koki Kitagawa; Toru Shimada
A multi-objective genetic algorithm (MOGA) has been applied to the multidisciplinary design optimization (MDO) of a launch vehicle (LV) with a hybrid rocket engine (HRE) to investigate the ability of an HRE to serve as a sounding rocket from various perspectives. In this study, the flight evaluation was enhanced to 3-degree-of-freedom (3DoF) in order to consider the equations of motion for horizontal and vertical motion and rotation of the LV. In the consideration of the rotation of the LV, the time variation of the center of gravity due to the fuel burn was estimated. The non-dominated sorting genetic algorithm-II (NSGA-II) was used to solve multi-objective problems (MoPs). Four design problems were examined in order to understand the practical physics of hybrid rocket. As a result, tradeoff information was observed for all design problems. The results for the present four design problems indicate that economical performance of LV is limited with the HRE in terms of the maximum altitude and maximum downrange distances achievable. The hypervolume, which was used as the metric to evaluate the difficulty of the design problems, reveals that the convergence of the solutions for not only altitude maximization in the case of a vertical launch but also the maximization of downrange at higher target altitudes was affected by the severe limitation. To observe the dependence of the design problems on the constraint, the design problems were visualized using a colored parallel coordinates plot (PCP), and the LV geometries determined from the nondominated solutions were successfully examined., IEEE, 2015, 2015 IEEE CONGRESS ON EVOLUTIONARY COMPUTATION (CEC), 618-625, English, 84963567634, WOS:000380444800082 - 523 TeleCommunication of Large-size Data Using Visble Light for Nano-Satellites
SAITO Shin-nosuke; ITOU Tomonori; SATORI Shin; CHIBA Kazuhisa
The Japan Society of Mechanical Engineers, 27 Sep. 2014, 北海道支部講演会講演概要集, 2014, 53, 135-136, Japanese, 110009950453, AA11902059 - 243 Parameter Identification for Aerodynamic Performance of Alsomitra-macrocarpa Seed
Sakata Kazuhiro; Saito Shin-nosuke; Chiba Kazuhisa
The Japan Society of Mechanical Engineers, 27 Sep. 2014, 北海道支部講演会講演概要集, 2014, 53, 63-64, Japanese, 110009950417, AA11902059 - 524 Correction of Aerial-Image Inclination for Precision Agricuture
SAITO Shin-nosuke; ITOU Tomonori; SATORI Shin; CHIBA Kazuhisa
The Japan Society of Mechanical Engineers, 27 Sep. 2014, 北海道支部講演会講演概要集, 2014, 53, 137-138, Japanese, 110009950454, AA11902059 - 213 Study on fluid dynamic force and wake of columnar objects having axes in the follow direction
Hiramoto Riho; Sasaki Junya; Satori Shin; Mitsuhashi Ryuichi; Chiba Kazuhisa; Akiba Ryojiro
一般社団法人日本機械学会, 27 Sep. 2014, 北海道支部講演会講演概要集, 2014, 53, 37-38, Japanese, 110009950404, AA11902059 - S1920104 Feasibility Study of a Mooring Hybrid Airship System
SATORI Shin; SASAKI Junya; CHIBA Kazuhisa; MITSUHASHI Ryuichi; HIRAMOTO Riho; TAKEUCHI Yusuke; Akiba Ryojiro
Recently, it is possible to moor a balloon and airship at high altitude because of the development of high-specific strength material. The mooring hybrid airship will become a multi-purpose platform such as the local communication infrastructure in emergency and remote sensing. It is also expected to use as a new space launch platform as known rockoon. The recent hybrid airship has an advantage of not only using the force of buoyancy but also the aerodynamic lifting force. The attitude stability is expected be more than the conventional balloon system. The feasibility and application of the mooring of the hybrid airship is investigated in this study., 一般社団法人日本機械学会, 07 Sep. 2014, Mechanical Engineering Congress, Japan, 2014, "S1920104-1"-"S1920104-2", Japanese, 110009945386, AA12588255 - Conception of Captive Airship Project
千葉 一永; 佐鳥 新; 三橋 龍一
日本航空宇宙学会, 10 Apr. 2014, 年会講演会講演集, 45, 4p, Japanese, 40020063335 - B-2-47 Development of Avionics for Preliminary Experimental of Airship mooring
Oguro Yuta; Hayasaka Ryosuke; Mitsuhashi Ryuichi; Satori Shin; Sasaki Masami; Hiramoto Riho; Chiba Kazuhisa; Sasaki Junya; Akiba Ryojiro
一般社団法人電子情報通信学会, 04 Mar. 2014, Proceedings of the IEICE General Conference, 2014, 1, 289-289, Japanese, 110009848975, AN10471452 - 燃料種を考慮したハイブリッドロケット概念設計における階層型相関分析
千葉一永; 渡邉真也; 金崎雅博; 北川幸樹; 嶋田徹
2014, 宇宙科学技術連合講演会講演集(CD-ROM), 58th, ROMBUNNO.3K16, Japanese, 1884-1945, 201402219586295210 - D02 Development of multi spectral camera for CubeSat
Ito Tomonori; Ota Satoshi; Kamei Takuya; Sugai Shinya; Takeuchi Yusuke; Satori Shin; Chiba Kazuhisa; Sasaki Masami; Mitsuhashi Ryuichi
北海道工業大学では,CubeSatへ搭載するためのマルチスペクトルカメラを製作している.NIRバンドパスフィルタを取り付けたモノクロイメージセンサと,RGBマルチバンドフィルタを取り付けたRGBイメージセンサを使用し,計2台のイメージセンサで4バンドのマルチスペクトルカメラを構成している.データ処理装置(MDHU)は放射線試験を行わないこととし,軌道上での利用実績や放射線試験データのあるCPLDとPICマイコンを使用する.データ処理用PICには,制御用PICとFRAMによるシステムプログラムのペリファイを行うことで放射線対策とした.制御用PICが衛星バス部からコマンドを受信し,CPLDとデータ処理用PICで,撮影した画像をSDカードへ保存する.本稿では,システム仕様、製作したデータ処理基板について説明し,分光感度特性を評価した., 一般社団法人日本機械学会, 20 Dec. 2013, スペース・エンジニアリング・コンファレンス講演論文集 : Space Engineering Conference, 2013, 22, "D02-1"-"D02-4", Japanese, 0918-9238, 110009934306, AA1190222X - Implication of Fuels in Performance of Single-stage Launch Vehicle with Hybrid Rocket Engine.
Kazuhisa Chiba; Masahiro Kanazaki; Koki Kitagawa; Toru Shimada
A single-stage hybrid rocket is necessary in order to efficiently perform the scientific observations and experiments. The primary objective of the present conceptual design is that the sufficient downrange and duration time in the low thermosphere is obtained in order to efficiently observe aurora, which is one of the recent topics in the scientific area, as well as holding down initial gross weight. The achievement of the mission as the observation of aurora using single-stage launch vehicle with hybrid rocket engine has been investigated by using design informatics. Moreover, the implication of fuels for the design requirements has also been investigated. As a result, the design information regarding the relationship among the design requirements, the influence regarding design variables for design requirements, and also implications of solid fuels for the performance were revealed., SciTePress, 03 Dec. 2013, SIMULTECH 2013 - Proceedings of the 3rd International Conference on Simulation and Modeling Methodologies, Technologies and Applications, Reykjavík, Iceland, 29-31 July, 2013, 777-784, Peer-reviwed, conf/simultech/ChibaKKS13, 84888398019 - 1110 Principal Component Analysis for Optimization Result of Single-Stage Hybrid Rocket
SUGAI Shinya; CHIBA Kazuhisa
It is necessary to trade-off is present in the objective function, to select a compromise solution to multi-objective optimization results. In order to select a compromise solution, the goal is to extract information from the database using the data mining. Check information that is visualized and quantified by selecting a principal component analysis from the data mining, to executed on a single-stage hybrid rocket optimization results are retrieved from the database is valid or not. Results of the principal component analysis, was achieved visualization and quantifying the correlation coefficients between parameters including the design variables and objective function., The Japan Society of Mechanical Engineers, 23 Oct. 2013, 設計工学・システム部門講演会講演論文集, 2013, 23, "1110-1"-"1110-3", Japanese, 1348-0286, 110009934324, AA11901475 - 1212 Failure analysis for launch experiments of CAMUI-Avionics
SAITO Shin-nosuke; ITO Tomonori; IINO Takayuki; HASEGAWS Takayuki; Mitsuhashi Ryuichi; Satori Shin; NAGATA Harunori; CHIBA Kazuhisa
A students group Hokkaido Space Union had been to space development for nine years. HSU made data handling unit named Sprit-nexus. It has been mounted on the CAMUI hybrid rocket. The objective obtain a telemetry data of the Sprit-nexus for the CAMUI hybrid rocket recovery. Telemetry data is composed of position coordinates and altitude and acceleration and attitude. CAMUI hybrid rocket is being developed by professor Harunori Nagata in Hokkaido University. CAMUI hybrid rocket was launched in Taiki Aerospace Research Field on July 28 2012. It was to go recovery by the ships from the sea after launch but, Sprit-nexus could not obtained a telemetry data. I will tried to find the cause of failure. As a result, the visual observation proved simple faulty electrical wiring., The Japan Society of Mechanical Engineers, 23 Oct. 2013, 設計工学・システム部門講演会講演論文集, 2013, 23, "1212-1"-"1212-5", Japanese, 1348-0286, 110009934340, AA11901475 - 3303 Mapping normalized vegetation index for precision agriculture by small unmanned aircraft
KAMEI Takuya; ITOH Tomonori; OHTA Satoshi; SATORI Shin; CHIBA Kazuhisa
Precision agriculture has been being implemented in order environmentally friendly and efficiently to product and manage crops. The remote sensing by satellite and aircraft is employed in order to obtain the information regarding the growth of crops. Although the data from satellites can include wide-range image each time, it is insufficient due to the fixed orbital path of satellites. Therefore, fixed-point observations cannot be sufficiently performed. Moreover, the observations on fixed orbital path cannot be always carried out because of cloud. Although aircrafts are used for the interpolation of the insufficient data by satellites, manned aircrafts need high personnel expenses and maintenance costs. Therefore, unmanned aerial vehicle (UAV) is recently employed. The objective of the present study is the development of the system to generate the interpolated image data by normalized difference vegetation index (NDVI) map taken by small-type UAV (sUAV), which is low-priced and simple system to implement precision agriculture. The following three assignments have been concretely performed in the present study; 1) light-weight four-band multispectral camera carried in sUAV will be developed, 2) sUAV is managed and the image data will be taken, and 3) NDVI map will be generated from the image data by sUAV and interpolated image data will also be developed to contribute precision agriculture. Consequently, the lightest four-band multispectral camera in the world has been developed, and also sUAV has been able to be successfully managed and acquired image data could also generates NDVI maps., The Japan Society of Mechanical Engineers, 23 Oct. 2013, 設計工学・システム部門講演会講演論文集, 2013, 23, "3303-1"-"3303-8", Japanese, 1348-0286, 110009934453, AA11901475 - 3304 Real-time acquisition of flight data for small unmanned aerial vehicle using GPS
KAMEI Takuya; TAKANO Tetsuya; CHIBA Kazuhisa
Aerial photography taken by using unmanned aerial vehicle can interpolate the image data obtained with satellite or manned aircraft. In past studies, we have succeeded in mounting a lightweight four-band multispectral camera with small-type unmanned aerial vehicle. However, this small-type unmanned aerial vehicle for photographing is conducted management of flight information only visually. Therefore, it is not sure where the photo was taken, and operates only in the visible range. In this study, as the next step, for correction of images taken, and flight information management of the aircraft, we have built a real-time operational environment with support for data management and small-type unmanned aerial vehicle with GPS. We confirmed the developed system can manage the small-type unmanned aerial vehicle real-time flight information on a PC by the flight experiment., The Japan Society of Mechanical Engineers, 23 Oct. 2013, 設計工学・システム部門講演会講演論文集, 2013, 23, "3304-1"-"3304-4", Japanese, 1348-0286, 110009934454, AA11901475 - 2401 Parametric Study of Paper Planes for Improvement of Flight Performance
SUGAI Shinya; SUZUKI Jyunichi; SAKUMA Shin; CHIBA Kazuhisa
Distance and duration of flight for paper planes exist in guinness record and the world tournament. Throwing method and flight are significantly different in the competition of distance and duration of flight. Tournament Participants get the best throwing technique by experience. The experiment was based on the rules of the world tournament by changing the parameters by prepare a plurality of airframe and quality of paper for the purpose of flight performance improvement. Consequently, paper quality and airframe required for flight duration improvement and flight distance extension are the direct contrast, that the strategy is different has been discovered., The Japan Society of Mechanical Engineers, 23 Oct. 2013, 設計工学・システム部門講演会講演論文集, 2013, 23, "2401-1"-"2401-4", Japanese, 1348-0286, 110009934413, AA11901475 - 設計情報学を用いた単段式ハイブリッドロケットの概念設計
千葉一永; 金崎雅博; 北川幸樹; 嶋田徹
22 Oct. 2013, 日本機械学会設計工学・システム部門講演会論文集(CD-ROM), 23rd, ROMBUNNO.1109, Japanese, 201502258958175635 - 設計情報学による科学観測用単段式ハイブリッドロケットの概念設計—Conceptual Design of Single-Stage Hybrid Rocket Using Design Informatics
千葉 一永; 金崎 雅博; 中宮 賢樹
日本航空宇宙学会, Oct. 2013, 宇宙科学技術連合講演会講演集, 57, 6p, Japanese, 1884-1945, 40020224679, AA11800503 - 415 Real-time acquisition of flight data for small unmanned aerial vehicle with GPS
KAMEI Takuya; TAKANO Tetsuya; CHIBA Kazuhisa
The Japan Society of Mechanical Engineers, 28 Sep. 2013, 北海道支部講演会講演概要集, 2013, 52, 117-118, Japanese, 110009955875, AA11902059 - 208 Normalized vegetation index map created by small unmanned aerial vehicle for application to precision agriculture
KAMEI Takuya; ITO Tomonori; Ohta Satoshi; SATORI Shin; CHIBA Kazuhisa
The Japan Society of Mechanical Engineers, 28 Sep. 2013, 北海道支部講演会講演概要集, 2013, 52, 47-48, Japanese, 110009955840, AA11902059 - 414 Data Mining for Optimization Result of Single-Stage Hybrid Rocket by Principal Component Analysis
SUGAI Shinya; CHIBA Kazuhisa
The Japan Society of Mechanical Engineers, 28 Sep. 2013, 北海道支部講演会講演概要集, 2013, 52, 115-116, Japanese, 110009955874, AA11902059 - 605 Difference of Strategy between Distance and Duration of Flight for Paper Planes
SUGAI Shinya; SUZUKI Jyunichi; SAKUMA Shin; CHIBA Kazuhisa
The Japan Society of Mechanical Engineers, 28 Sep. 2013, 北海道支部講演会講演概要集, 2013, 52, 159-160, Japanese, 110009955896, AA11902059 - 設計情報学による科学観測用単段式ハイブリッドロケットの概念設計
千葉一永; 金崎雅博; 中宮賢樹; 北川幸樹; 嶋田徹
2013, 宇宙科学技術連合講演会講演集(CD-ROM), 57th, ROMBUNNO.3A05, Japanese, 1884-1945, 201302257218788705 - F011001 Creation and Prospect of Design-Informatics
Chiba Kazuhisa
Design-informatics has been proposed for efficient design,namely,it performs efficient exploration for design space and also implements conception support for innovative hypothesis.The results produced by evolutionary multi-objective optimizations are not individual optimal solution but rather an entire set of optimal solutions.That is,the result of a multi-objective optimization is not the end of the process while from a practical point of view the designers need a conclusive shape or few candidates of a conclusive shape.Therefore,multi-objective design exploration was performed as a next step in order to overlook design space.This approach is a stance to passively construct an obtained design knowledge while comparing with design space.On the other hand,design-informatics actively systematizes design information in order to perform conception support for designer.In the present paper,the recent results of optimization and design information using data mining are surveyed so that efficient approach is investigated for conception support., The Japan Society of Mechanical Engineers, 09 Sep. 2012, Mechanical Engineering Congress, Japan, 2012, "F011001-1"-"F011001-3", Japanese, 110009993953, AA12588255 - Multidisciplinary Design Exploration for Transonic Regional-Jet Wing Shape :
CHIBA Kazuhisa; JEONG Shinkyu; OBAYASHI Shigeru; MORINO Hiroyuki
日本機械学会, 2006, Proceedings of International Workshop on Multidisciplinary Design Exploration in …, 2006, 1-8, English, 110006676638, AA12251116 - Efficient Data Mining for Multi-Objective Design Exploration Regarding Aerospace Vehicle
K. Chiba; S. Jeong; K. Yamamoto
2006, Proceedings of International Conference on Nonlinear Problems in Aviation and Aerospace 2006 - Design Exploration of Shielding Effect for Aircraft Engine Noise
K.Chiba; T. Imamura; K. Amemiya; S. Jeong; K. Yamamoto
The multi-objective design exploration of the two-dimensional shielding effect for engine noise using V-tale wing has been performed. Two objective functions are considered as the minimization of the sound pressure level at the side and bottom locations relative to the fuselage, which values are evaluated by using the linearized Euler equation. Two design variables are defined as the wing length and the wing cant angle to set on the fuselage. The response surface method based on the kriging model is employed as the optimizer to reduce the time required for design exploration. As a result, there is no tradeoff between two objective functions, i.e., the sound pressure level at the side and bottom measuring locations can be reduced, simultaneously. The wing cant angle which is set at roughly 65 deg is most effective to shield the noise. It is justly the necessary condition to reduce the sound pressure level that the wing length becomes long. Moreover, a self-organizing map as a data mining technique reveals the knowledge in the design space regarding the correlation among the objective functions and the design variables., The Japan Society of Mechanical Engineers, 2006, The European Community on Computational Methods in Applied Science CFD 2006, 2006, 281-282, Japanese, 110006635981, AA11461871 - Multi-Objective Design Exploration for Aerodynamic Configurations
S. Obayashi; S. Jeong; K. Chiba
2005, Proceedings of 23rd AIAA Applied Aerodynamics Conference - Data mining for multidisciplinary design space of regional-jet wing
K Chiba; S Jeong; S Obayashi; H Morino
The Data Mining technique is an important facet of solving multi-objective optimization problem. Because it is one of the effective manner to discover the design knowledge in the multi-objective optimization problem which obtains large data. In the present study, two Data Mining techniques have been performed for a large-scale, real-world Multidisciplinary Design Optimization (MDO) to provide knowledge regarding the design space. The MDO among aerodynamics, structures, and aeroelasticity of the regional-jet wing was carried out using high-fidelity evaluation models on Adaptive Range Multi-Objective Genetic Algorithm. As a result, nine non-dominated solutions were generated and used for tradeoff analysis among three objectives. All solutions evaluated during the evolution were analyzed for the influence of design variables using a Self-Organizing Map (SOM) and a functional Analysis of Variance (ANOVA) to extract key features of the design space. SOM and ANOVA compensated with the respective disadvantages, then the design knowledge could be obtained more clearly by the combination between them. Although the MDO results showed the inverted gull-wings as non-dominated solutions, one of the key features found by Data Mining was the non-gull wing geometry. When this knowledge was applied to one optimum solution, the resulting design was found to have better performance compared with the original geometry designed in the conventional manner., IEEE, 2005, 2005 IEEE CONGRESS ON EVOLUTIONARY COMPUTATION, VOLS 1-3, PROCEEDINGS, 3, 2333-2340, English, WOS:000232173100310 - Evolutionary Design Optimization of Wing Shape for RLV Booster Stage Using Unstructured Navier-Stokes Computation
CHIBA Kazuhisa; OBAYASHI Shigeru; NAKAHASHI Kazuhiro
The wing shape of booster stage for Two-Stage-To-Orbit Reusable Launch Vehicle is optimized in consideration of supersonic region, transonic cruise and subsonic landing. Navier-Stokes computation is used for aerodynamic evaluation because transonic cruise and subsonic landing have flow condition that vorticity dominants. ARMOGA is used for aerodynamic optimization problem with four objective functions because it is expected that tradeoff can be obtained using low individual numbers. The results show the relationship of each objective functions., The Japan Society of Mechanical Engineers, 30 Oct. 2003, 設計工学・システム部門講演会講演論文集, 2003, 13, 303-304, Japanese, 1348-0286, 110002481434, AA11901475 - レイノルズ数6×106域での前縁剥離渦の挙動に関する数値的研究
千葉 一永; 大林 茂; 中橋 和博
東北大学流体科学研究所, 2003, 東北大学流体科学研究所報告, 14, 31-37, Japanese, 0916-2860, 80016226108, AN10181088
Lectures, oral presentations, etc.
- エンジンとエアフレームの統合解析は何をもたらすのか
千葉 一永; Mueller, J.; 大庭 芳則
Oral presentation, Japanese, 令和6年度航空宇宙空力シンポジウム
24 Jan. 2025
24 Jan. 2025- 25 Jan. 2025 - Multi-wingletによる離着陸時の後方乱気流抑制効果
小林英里奈; 千葉一永
Poster presentation, Japanese, 航空宇宙流体科学サマースクール2024
19 Sep. 2024
17 Sep. 2024- 19 Sep. 2024 - Integrated simulation of airframe and running engine to examine their aerodynamic interaction effects
Mueller, J; Chiba, K; Oba, Y
Invited oral presentation, English, KSME-JSME Joint Symposium on Computational Mechanics & CAE 2024, Invited
02 Sep. 2024
01 Sep. 2024- 03 Sep. 2024 - Multi-wingletのcant角変更による空力変化メカニズム
小林 英里奈; 千葉 一永; 金崎 雅博
Oral presentation, Japanese, 第56回流体力学講演会/第42回航空宇宙数値シミュレーション技術シンポジウム
03 Jul. 2024
03 Jul. 2024- 05 Jul. 2024 - Identification of Losses from Engine-Airframe Interaction for a Passenger Aircraft through Integrated Simulation
Mueller, J; Chiba, K; Oba, Y
Invited oral presentation, English, The 9th European Congress on Computational Methods in;Applied Sciences;Engineering, Invited, Peer-reviewed
04 Jun. 2024
03 Jun. 2024- 07 Jun. 2024 - Influences of Multiple Winglets on the Aerodynamic Performance and Flow Field of an Aircraft
Kobayashi, E; Chiba, K; Kanazaki, M
Oral presentation, English, The 9th European Congress on Computational Methods in Applied Sciences and Engineering, Peer-reviewed
04 Jun. 2024
03 Jun. 2024- 07 Jun. 2024 - Multi-wingletによる航空機の空力性能および流れ場への影響
小林 英里奈; 千葉 一永; 金崎 雅博
Oral presentation, Japanese, 日本航空宇宙学会第55期年会講演会
19 Apr. 2024
18 Apr. 2024- 19 Apr. 2024 - Sliding mesh法による稼働エンジンと機体の統合解析
千葉 一永; Mueller, Jan; 大庭 芳則
Oral presentation, Japanese, 令和5年度航空宇宙空力シンポジウム
19 Jan. 2024
19 Jan. 2024- 20 Jan. 2024 - 設計変数空間での非劣解の多様性を確保する交叉の開発
門馬 圭吾; 大山 聖; 千葉 一永
Poster presentation, Japanese, 進化計算学会進化計算シンポジウム2023
22 Dec. 2023
22 Dec. 2023- 23 Dec. 2023 - Sliding mesh法による航空機体と稼働エンジンの統合解析
Mueller, Jan; 千葉 一永; 大庭 芳則
Oral presentation, Japanese, 第37回数値流体力学シンポジウム
15 Dec. 2023
15 Dec. 2023- 17 Dec. 2023 - 悪天候回避時における航空機の飛行経路と気象データの相関分析
横濱 こころ; 中村 陽一; 瀬之口 敦; 千葉 一永
Oral presentation, Japanese, 第61回飛行機シンポジウム
16 Nov. 2023
15 Nov. 2023- 17 Nov. 2023 - Aerodynamic Effect of Engine Exhaust on Aircraft Whole Body - Integrated Analysis of Airframe and Running Engine Using Sliding-Mesh Method
Mueller, J; Chiba, K; Oba, Y; Obayashi, S
Poster presentation, English, 20th International Conference on Flow Dynamics
08 Nov. 2023
06 Nov. 2023- 08 Nov. 2023 - Aerodynamic Efficacy of Changing the Chordwise Installation Position of Multi-Winglet on Commercial Aircraft
Kobayashi, E; Chiba, K
Oral presentation, English, Asia-Pacific International Symposium on Aerospace Technology, Peer-reviewed
16 Oct. 2023
16 Oct. 2023- 18 Oct. 2023 - 航空機経路と気象データの相関分析 - パイロットの悪天回避行動に基づく経路の事前生成に向けて
横濱 こころ
Poster presentation, Japanese, 航空宇宙流体科学サマースクール2023
09 Sep. 2023
07 Sep. 2023- 09 Sep. 2023 - 亜音速・遷音速条件におけるマルチウィングレット付航空機の空力解析
小林 英里奈
Poster presentation, Japanese, 航空宇宙流体科学サマースクール2023
07 Sep. 2023
07 Sep. 2023- 09 Sep. 2023 - Influence of the Engine Exhaust on the Wing Pressure Distrubution Computed with an Integrated Simulation of Airframe and Running Engine
Mueller, J; Chiba, K; Oba, Y
Oral presentation, English, AIAA AVIATION 2023, Peer-reviewed
13 Jun. 2023
12 Jun. 2023- 16 Jun. 2023 - Influence of Engine Exhaust on Wing Underside Flow for a Passanger Aircraft
Mueller, J., Chiba, K., Oba, Y.
Oral presentation, English, 22nd Computational Fluids Conference, IACM, Cannes, France, Peer-reviewed
28 Apr. 2023
25 Apr. 2023- 28 Apr. 2023 - Feedback-Circulating Desgin Space Exploration by Multi-Sampling Kriging Model: Exploitation for the Lift Rise by an Aircraft Flap with Yaw-Wise Rotation
Chiba, K; Kanazaki, M
Oral presentation, English, 7th International Conference on Intelligent Systems, Metaheuristics & Swarm Intelligence, Peer-reviewed
24 Apr. 2023
23 Apr. 2023- 24 Apr. 2023 - 複数枚ウィングレット取付位置変更による民間航空機の空力性能向上効果
小林 英里奈; 千葉 一永
Oral presentation, Japanese, 日本航空宇宙学会第54期年会講演会
14 Apr. 2023
13 Apr. 2023- 14 Apr. 2023 - 航空機の悪天回避経路予測に向けた乱気流指数の有用性検討
横濱 こころ; 中村 陽一; 瀬之口 敦; 千葉 一永
Oral presentation, Japanese, 日本航空宇宙学会第54期年会講演会
13 Apr. 2023
13 Apr. 2023- 14 Apr. 2023 - 航空機の作動エンジンとエアフレームの統合解析
千葉 一永; Mueller Jan; 大庭 芳則
Oral presentation, Japanese, 2023年度航空宇宙空力シンポジウム
06 Jan. 2023
06 Jan. 2023- 07 Jan. 2023 - 航空機の作動エンジンとエアフレームの統合解析
千葉 一永; Mueller Jan; 大庭 芳則
Oral presentation, Japanese, 第36回数値流体力学シンポジウム
14 Dec. 2022
14 Dec. 2022- 16 Dec. 2022 - Effect of Pressure Recovery on the Lower Surfaces of Multiple Winglets by Changing the Main Wing Airfoil of an Aircraft
Kobayashi, E. and Chiba, K.
Oral presentation, English, AIAA 2022 Region VII Student Conference, AIAA: American Institute of Aeronautics and Astronautics, Adelaide, Australia, Peer-reviewed
28 Nov. 2022
28 Nov. 2022- 29 Nov. 2022 - 航空機主翼の翼型変更による複数枚ウィングレット下面の圧力回復効果
小林 英里奈, 千葉 一永
Oral presentation, Japanese, 日本機械学会第100期流体工学部門講演会, 日本機械学会, 熊本, 優秀学生論文賞候補者に採択済
13 Nov. 2022
12 Nov. 2022- 13 Nov. 2022 - Influences of Changing the Installing Positions of Multiple Winglets on Aerodynamic Characteristics
Kobayashi, E. and Chiba, K.
Oral presentation, English, 33rd Congress of the INternational Council of the Aeronautical Sciences, ICAS, Stockholm, Sweden, Peer-reviewed
08 Sep. 2022
04 Sep. 2022- 08 Sep. 2022 - Integrated Analysis of Operating Engine and Airframe for High-Fidelity Wing Load Estimation
Chiba, K. and Oba, Y.
Invited oral presentation, English, 15th World Congress on Computational Mechanics, Yokohama, Japan, 31 July-5 August, 2022, Invited, IACM, online, Peer-reviewed, https://www.wccm2022.org/, International conference
01 Aug. 2022
31 Jul. 2022- 05 Aug. 2022 - 設計変数空間での解分布の多様性を評価するための新しい指標の提案とそれに基づいた交叉法の実問 題における特性評価
門馬 圭吾, 佐藤 元紀, 大山 聖, 海野 大, 千葉 一永
Oral presentation, Japanese, 進化計算学会第21回研究会,
17 Mar. 2022 - 実問題の最適設計 - その思想と応用
千葉 一永
Invited oral presentation, Japanese, ニュートンワークス株式会社, 非線形解析フォーラム, Invited
12 Nov. 2021
12 Nov. 2021 - 設計情報学の本質 - フィードバック循環型最適設計
千葉 一永
Keynote oral presentation, Japanese, 日本機械学会第31回設計工学・システム部門講演会, Invited
15 Sep. 2021
15 Sep. 2021- 17 Sep. 2021 - 進化計算のランデヴー
千葉 一永
Invited oral presentation, Japanese, 進化計算学会第20回研究会, Invited
08 Sep. 2021
08 Sep. 2021- 09 Sep. 2021 - Optimum Design for Real-world Problems in Aerospace Engineering
Chiba, K
Invited oral presentation, English, Multidisciplinary Optimization & Machine Learning for Engineering Design, International Virtual Course, Invited
23 Jul. 2021
19 Jul. 2021- 05 Aug. 2021
Affiliated academic society
Research Themes
- 燃費向上を目指したプロップファンエンジン搭載航空機の統合解析
千葉 一永; 阿部 圭晃
東北大学流体科学研究所, 公募共同研究, 共同研究, Principal investigator, J25I083
Apr. 2025 - Mar. 2026 - サブオービタルスペースプレーンの最適なシステム及び軌道探索の研究
株式会社SPACE WALKER, 共同研究, Coinvestigator
Oct. 2024 - Mar. 2026 - スライディングメッシュ法による稼働エンジンと機体の統合解析
千葉一永
東北大学流体科学研究所, 公募共同研究, Principal investigator, J24I094
Apr. 2024 - Mar. 2025 - 航空機遷音速バフェットの時間的起点規定のための進化的学習分類子システム
千葉 一永
日本学術振興会, 科学研究費助成事業, 電気通信大学, Scientific research (C), general, Principal investigator, 22K12164
Apr. 2022 - Mar. 2025 - 複合材時代の理想機体構造を実現する機体設計技術の開発
国立研究開発法人 新エネルギー・産業技術総合開発機構, 委託研究
Jul. 2020 - Feb. 2025 - スライディングメッシュ法による稼働エンジンと機体の統合解析
千葉一永
東北大学流体科学研究所, 公募共同研究, Principal investigator, J23L051
Apr. 2023 - Mar. 2024 - 航空機体と稼働エンジンとの統合解析
東北大学流体科学研究所, Principal investigator
01 Apr. 2022 - 31 Mar. 2023 - 多目的最適化アルゴリズムCHEETAR-Rの宇宙工学分野実問題への実践的応用
大山聖
国立研究開発法人 宇宙航空研究開発機構 宇宙科学研究所, Principal investigator
2022 - 2023 - Topology data analysis to elucidate occuring mechanism of unsteady phenomena on aircraft
千葉 一永
Japan Society for the Promotion of Science, Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (C), The University of Electro-Communications, Grant-in-Aid for Scientific Research (C), Principal investigator, 本研究では，カオス的挙動を取る航空機遷音速バフェット現象データを解析するため，位相的データ解析法の一種であるパーシステントホモロジーを導入し，適用可否や課題点を詳らかにした．具体的な実績を以下にまとめる． 宇宙航空研究開発機構で解析を進めるOAT15A超臨界圧翼における遷音速バフェット非定常データセットにパーシステントホモロジーを適用することで，遷音速バフェット強度を検出し，定量化する新たな方法を導いた．航空機の設計・開発において重要な非定常現象である遷音速バフェットの定量化は，通常，表面積や体積の積分で表現される．しかし，この方法では現象の時間的な起源や空間的な発生を明らかにすることはできていないため，その発生メカニズムは未だ不明である．また，この診断方法を実機に適用することは困難である．そこで，計算流体力学においてNavier-Stokes方程式で扱われる物理量を，パーシステントホモロジーにより間接的に数学空間で扱い，数学的アプローチによって遷音速バフェットの強度を定量化することを試みた．その結果，翼表面の衝撃波移動領域内の任意の点のデータからバフェットを検出できることを定量的に明らかにした．圧力係数と一様流速度の2階偏導関数は，共にバフェットを検出できたが，公社は，その強度に顕著な差を見出した．本手法の適用により，実機で取得されたセンサーデータからリアルタイムに航空機遷音速バフェットを識別することができるようになる． 本成果により，遷音速バフェットの強度を定量的に表現する方法論が提示され，現象を追究する道具ができた．, 19K12095
Apr. 2019 - Mar. 2022 - 乱気流に基づく軌道ベース運用に資する検討
中村陽一
国立研究開発法人 会場・港湾・航空技術研究所 電子航法研究所, Principal investigator
2022 - エンジン-機体統合性能予測CFD解析技術
千葉一永
国立研究開発法人新エネルギー・産業技術総合開発機構, 研究開発項目5 航空機用構造設計シミュレーション技術開発に係る委託業務6, Principal investigator
Apr. 2018 - Mar. 2020 - 大域/局所設計情報間の潜在構造の可視化と数理モデル化 - 現象理解と仮説導出に向けて
千葉一永
日本学術振興会, 科学研究費補助金 基盤研究(C), Principal investigator
Apr. 2016 - Mar. 2019 - 非定常兆候検出のためのデータマイニング手法の検討（統計解析・ニューラルネットワークの適用）
千葉一永
国立研究開発法人 宇宙航空研究開発機構, 委託研究, Principal investigator
Apr. 2017 - Mar. 2018 - 係留式高層プラットフォームシステムのためのLTA機体空力設計
千葉一永
東北大学流体科学研究所, リーダーシップ共同研究, Principal investigator
Apr. 2017 - Mar. 2018 - 非定常兆候検出のためのデータマイニング手法の検討
千葉一永
国立研究開発法人 宇宙航空研究開発機構, 委託研究, Principal investigator
Oct. 2016 - Mar. 2017 - 係留式高層プラットフォームシステムのためのLTA機体空力設計
千葉一永
東北大学流体科学研究所, 一般公募共同研究, Principal investigator
Apr. 2016 - Mar. 2017 - Aerial Launch Platform / Systemの研究
千葉一永
国立研究開発法人 宇宙航空研究開発機構 宇宙工学委員会, 戦略的開発研究費, Principal investigator
Aug. 2016 - Jan. 2017 - 飛行船および索が有する空力性能の係留式高層プラットフォームシステム挙動に対する影響性
千葉一永
東北大学流体科学研究所, 一般公募共同研究, Principal investigator
Apr. 2015 - Mar. 2016 - Ground experiment of the innovative sonic boom reduction technology
OBAYASHI Shigeru; KOBAYASHI Hideaki; ASAI Keisuke; NAGAI Hiroki; OGAWA Toshihiro; SAITO Tsutomu; KAWAZOE Hiromitsu; CHIBA Kazuhisa; NUMATA Daiju
Japan Society for the Promotion of Science, Grants-in-Aid for Scientific Research, Tohoku University, Grant-in-Aid for Scientific Research (A), Design and evaluation systems for supersonic vehicles are constructed in this research to develop a low-boom supersonic vehicle based on Supersonic Biplane Theory. The following experimental and numerical simulation techniques were developed: free flight experiment of three-dimensional projectiles, surface pressure distribution measurement using ultrafast response pressure-sensitive paint, a calibration technique of pressure waveforms by the multipole method, a force balance measurement system in a supersonic wind tunnel, sonic boom estimation with consideration of the real atmospheric conditions, and design optimization and exploration for unsteady phenomena., 23246144
01 Apr. 2011 - 31 Mar. 2015 - 非定常現象を伴う航空宇宙機に対する設計情報学の拡張
千葉一永
東北大学流体科学研究所, 一般公募共同研究, Principal investigator
Apr. 2014 - Mar. 2015 - 設計情報学の創出-次代を担う航空宇宙機の実現を目指して
千葉一永
文部科学省, 科学研究費補助金若手研究(B), Principal investigator
Apr. 2010 - Mar. 2012 - 革新航空宇宙機開発のための設計空間に対する俯瞰的アプローチによる設計知識獲得法
千葉一永
文部科学省, 科学研究費補助金若手研究(B), Principal investigator
Apr. 2008 - Mar. 2010 - 超音速研究機主翼形状の多分野融合最適設計
総合研究, 超音速巡航性能，低速性能を確保し，ブーム強度を抑制し，且つ構造要求を満たす最軽量な複合材重量の機体設計に多分野融合最適化を適用している．
2006
