Curriculum Vitaes
Profile Information
- Affiliation
- Professor, Institute of Space and Astronautical Science, Japan Aerospace Exploration AgencyThe University of TokyoTokyo University of Science
- Degree
- Ph.D. in Engineering(Mar, 2000, Tohoku University)
- Researcher number
- 10373440
- J-GLOBAL ID
- 200901044748363926
- researchmap Member ID
- 5000069161
- External link
宇宙科学航空研究開発機構宇宙科学研究所の大山です．
自分の研究分野にとらわれず，新しい研究分野にも挑戦していきたいと考えています．
自分の研究分野にとらわれず，新しい研究分野にも挑戦していきたいと考えています．
Research Interests
17Research Areas
6Research History
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Dec, 2023 - Present
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Apr, 2019 - Present
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Apr, 2015 - Nov, 2023
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Apr, 2010 - Mar, 2023
Education
5-
Apr, 1997 - Mar, 2000
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Apr, 1995 - Mar, 1997
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Apr, 1991 - Mar, 1995
Committee Memberships
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Oct, 2020 - Present
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Jun, 2010 - Present
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Oct, 2018 - Sep, 2020
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Apr, 2017 - Mar, 2019
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Apr, 2015 - Mar, 2017
Awards
15-
Apr, 2022
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May, 2021
Papers
139-
IEEE Access, 12 73839-73848, May, 2024 Peer-reviewedCorresponding author
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15(1) 20-30, Jan, 2024 Peer-reviewedCorresponding author
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 67(1) 12-22, 2024
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Journal of Mechanical Design, 146(4), Nov 7, 2023Abstract Solving a multiple-criteria optimization problem with severe constraints remains a significant issue in multi-objective evolutionary algorithms. The problem primarily stems from the need for a suitable constraint handling technique. One potential approach is balancing the search in feasible and infeasible regions to find the Pareto front efficiently. The justification for such a strategy is that the infeasible region also provides valuable information, especially in problems with a small percentage of feasibility areas. To that end, this paper investigates the potential of the infeasibility-driven principle based on multiple constraint ranking-based techniques to solve a multi-objective problem with a small feasibility ratio. By analyzing the results from intensive experiments on a set of test problems, including the realistic multi-objective car structure design and actuator design problem, it is shown that there is a significant improvement gained in terms of convergence by utilizing the generalized version of the multiple constraint ranking techniques.
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Journal of Aircraft, 60(5) 1721-1727, Sep, 2023
Misc.
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205-208, 2007In order to improve an efficiency of failure analysis process by using failure mode and effect analysis (FMEA) and failure tree analysis (FTA), detailed FMEA/FTA support tool is developed. By using this tool, failure mechanisms can be analyzed with FMEA approach as well as FTA approach. In order to improve coverage of the extracted failure modes, new failure analysis approach is proposed, which is based on the interface N2 chart. Interface N2 chart is N2 chart which is extended to express the interface of mechanical system. Interface N2 chart can also be used to visualize the failure analysis result to describe system structure based on the knowledge obtained in failure analysis such as causal relationship of fault propagation. New schematic visualization method is discussed to realize useful visualization tool which promotes comprehensive understanding of failure mechanism.
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The Computational Mechanics Conference, 2006(19) 189-190, Nov 2, 2006
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Fluids engineering conference ..., 2006 "910-a", Oct 28, 2006
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Fluids engineering conference ..., 2006 "910-1"-"910-4", Oct 28, 2006Flow fields of the supersonic jets impinging on an inclined flat plate at high plate-angles are experimentally investigated using surface pressure measurement with pressure sensitive paint and Schlieren flow visualization. While Type I flow type is dominant at high plate angles, the present research found a new flow type "TYPE I with bubble" at plate angle between 60 and 80 degrees. The flow classification according to L/L_s' and plate angle indicated that the constant x/L'_s curve doesn't represent the boundary of Type I and Type II anymore at high plate angles between 60 and 90 probably because Type II flows at low plate angles and high plate angles is different phenomena. This study also indicates that the curve dividing Type I and Type I with bubble regions is same as the curve dividing Type II and Type II with bubble regions.
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Fluids engineering conference ..., 2005 144-144, Oct 28, 2005
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2005(15) 237-240, Aug 2, 2005An efficient and useful robust optimization approach, design for multi-objective six sigma (DFMOSS), has been developed. The DFMOSS couples the ideas of design for six sigma (DFSS) and multi-objective genetic algorithm (MOGA) to solve drawbacks of DFSS. DFMOSS obtains trade-off solutions between optimality and robustness in one optimization. In addition, it does not need careful parameter tuning. Robust optimizations of a test function and welded beam design problem demonstrated that DFMOSS is more effective and more useful than DFSS.
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Journal of Japan Society of Fluid Mechanics, 24(3) 289-296, Jun 25, 2005
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Journal of the Visualization Society of Japan, 25(1) 313-316, Mar 15, 2005
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Journal of the Visualization Society of Japan, 25(1) 317-320, Mar 15, 2005
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Fluids engineering conference ..., 301-301, 2005
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2004 84-85, 2004Low Reynolds number airfoil design optimization is demonstrated. A two-dimensional Navier-Stokes solver is used for aerodynamic performance estimation of the airfoil design candidates because the viscosity effect is not negligible at low Reynolds number flight condition. An evolutionary computation is used for robust airfoil design optimization. The result demonstrated that the optimized airfoil is a very thin airfoil with significant camber. The result also showed that the low Reynolds number airfoil has time variation in its lift and drag.
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Proceedings of the conference on computational engineering and science, 4(1) 475-478, May 26, 1999
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Special publication of National Aerospace Laboratory : SP, 34 107-112, 1997
Books and Other Publications
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Springer Verlag, 2009 RefereedConstraint-handling techniques for evolutionary multiobjective aerodynamic and multidisciplinary designs are focused. Because number of evaluations is strictly limited in aerodynamic or multidisciplinary design optimization due to expensive computational fluid dynamics (CFD) simulations for aerodynamic evaluations, very efficient and robust constraint-handling technique is required for aerodynamic and multidisciplinary design optimizations. First, in Section 2, features of aerodynamic design optimization problems are discussed. Then, in Section 3 constraint-handling techniques used for aerodynamic and multidisciplinary designs are overviewed. Then, an efficient constraint-handling technique suitable to aerodynamic and multidisciplinary designs is introduced with real-world aerodynamic and multidisciplinary applications. Finally, an efficient geometry-constraint-handling technique commonly used for aerodynamic design optimizations is presented. © 2009 Springer-Verlag Berlin Heidelberg.
Presentations
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AIAA SCITECH 2025 Forum, Jan 7, 2025
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AIAA SCITECH 2025 Invited
Professional Memberships
6Research Projects
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科学研究費補助金, 日本学術振興会, Apr, 2014 - Mar, 2017
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科学研究費補助金, 日本学術会議, Apr, 2012 - Mar, 2015
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科学研究費補助金, 日本学術振興会, Apr, 2011 - Mar, 2013
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科学研究費補助金, 日本学術会議, Apr, 2008 - Mar, 2011
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科学研究費補助金, 日本学術振興会, Apr, 2008 - Mar, 2010
