研究者業績
基本情報
- 所属
- 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 教授東京大学大学院 教授東京理科大学 理工学研究科機械工学専攻 客員教授
- 学位
- 博士（工学）(2000年3月 東北大学大学院)
- 研究者番号
- 10373440
- J-GLOBAL ID
- 200901044748363926
- researchmap会員ID
- 5000069161
- 外部リンク
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．
研究キーワード
17研究分野
6経歴
13-
2023年12月 - 現在
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2023年4月 - 現在
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2019年4月 - 現在
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2015年4月 - 2023年11月
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2010年4月 - 2023年3月
学歴
5-
1997年4月 - 2000年3月
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- 2000年
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1995年4月 - 1997年3月
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1991年4月 - 1995年3月
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- 1995年
委員歴
7-
2020年10月 - 現在
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2010年6月 - 現在
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2018年10月 - 2020年9月
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2017年4月 - 2019年3月
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2015年4月 - 2017年3月
受賞
13-
2022年4月
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2021年5月
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2020年11月
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2020年2月
論文
131-
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 67(1) 12-22 2024年
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60(5) 1721-1727 2023年9月
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Journal of Computational Physics 468 111505-111505 2022年11月 査読有り
MISC
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宇宙航空研究開発機構特別資料: 第53回流体力学講演会/第39回航空宇宙数値シミュレーション技術シンポジウム論文集 = JAXA Special Publication: Proceedings of the 53rd Fluid Dynamics Conference / the 39th Aerospace Numerical Simulation Symposium JAXA-SP-21-008 149-155 2022年2月14日第53回流体力学講演会/第39回航空宇宙数値シミュレーション技術シンポジウム (2021年6月30日-7月2日. 日本航空宇宙学会 : 宇宙航空研究開発機構(JAXA)オンライン会議) The 53rd Fluid Dynamics Conference / the 39th Aerospace Numerical Simulation Symposium (June 30 - July 2, 2021. The Japan Society for Aeronautical and Space Sciences : Japan Aerospace Exploration Agency (JAXA), Online meeting) In this paper, aerodynamic characteristics around the blade of the hexacopter ''HAMILTON (HexAcopter for Martian pIt crater exploraTiON)'' for Mars exploration are investigated to obtain design knowledge regarding multicopter drone flying in Martian atmosphere. Reynolds-averaged Navier-Stokes simulation with the moving overlapped grid was employed for aerodynamic evaluation of two cases; one is hexa-rotor case and the other is single rotor case in order to compare single rotor case and hexa-rotor case and reveal unique characteristics of multirotor case. According to computational results, in both cases, hexa-rotor and single rotor, the maximum figure of merit could be observed at higher hovering thrust conditions. It is suggested that the baseline blade geometry could generate thrust efficiently at higher thrust conditions. The flow structure around the hexa-rotor can be classified into three groups; turn-in side where the flow was drawn the inside by blades rotation, turn-out side where the flow was put out to the outside by blades rotation, and the center side which was located between the turn-in and turn-out sides. The rotors of the center side took the low figure of merit compared with the other rotors because of aerodynamic interference from the turn-in side and the turn-out side rotors. Therefore, the total figure of merit of all rotors increased when the distance among rotors is increased. 形態: カラー図版あり Physical characteristics: Original contains color illustrations 資料番号: AA2130027012 レポート番号: JAXA-SP-21-008
書籍等出版物
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Springer Verlag 2009年 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.
講演・口頭発表等
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年次大会 : Mechanical Engineering Congress, Japan 2013年9月8日 一般社団法人日本機械学会To understand the effects of working parameters of the DBD plasma actuator, investigation with a Multi-Objective Design Exploration(MODE) framework is performed. Experiments with a NACA 0015 airfoil fixed to the stall angle of 12 degrees are conducted at Reynolds number of 63,000. The optimization objectives are to maximize the lift coefficient C_l and minimize the power consumption P. The design variables consist of input power parameters. Despite the small population size, an approximate Pareto-optimal front is found. In the objective function space, a region where there exists a linear relationship between C_l and P is found. After a threshold value, the value of C_l seems to saturate. This paper concentrates on this linear region of the objective function space. We use numerical simulation results with similar parameters to several Pareto-optimal experiment cases to compliment our discussion.
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年次大会 : Mechanical Engineering Congress, Japan 2013年9月8日 一般社団法人日本機械学会In this study, multiobjective design exploration for a rocket launch site is conducted using evolutionary computation with large eddy simulation to understand the acoustic characteristics associated with various launch sites and find design information such as trade-off relation among design objectives. The launch site is described by curved surface. The flat plate inclined with 45 degree is considered as the reference configuration. The objective functions of multiobjective aero-acoustic design optimization are, 1) minimization of averaged sound pressure level near the payload fairing, 2) minimization of maximum pressure on the curved surface of the rocket launch site, and 3) minimization of the change of the curved surface from the reference configuration. The total number of evaluation in multiobjective evolutionary computation is 2500. The analysis of non-dominated solutions clearly show that there are various trade-off relations and correlations among the objective functions.
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AIAA Infotech at Aerospace Conference and Exhibit 2012 2012年Multiobjective design exploration (MODE) framework is used to obtain useful knowledge from the Pareto-optimal solutions of a Solar observatory trajectory design problem. The trajectory design optimization problem is defined as a multiobjective design optimization problem and solved with a multiobjective evolutionary computation. Many designs that are better than the nominal design in all design objectives are found. The obtained Pareto-optimal solutions visualize tradeoff between the design objectives. Some data mining approaches are applied to the database of the obtained Pareto-optimal designs and show useful design information such as sensitivity of the design parameters to the design objectives. The present results shows MODE approach is useful for trajectory design optimization problems. © 2012 by Akira Oyama, Yasuhiro Kawakatsu, and Kazuko Hagiwara.
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Proceedings of the International Astronautical Congress, IAC 2012年Multi-objective design exploration (MODE) is applied to the trajectory design optimization problem for DESTINY mission, whose spacecraft will go to the moon by the ion engine from the large ellipse orbit. This approach revealed some important design knowledge such as tradeoff information among minimization of the operation time of ion engine, maximization of the final orbit energy, and minimization of the transit time under 20000 km altitude. This study also shows possibility of simultaneous design of trajectory and spacecraft. Copyright© (2012) by the International Astronautical Federation.
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Advances in the Astronautical Sciences 2012年Multiobjective design exploration (MODE) framework is applied to the trajectory design optimization problem for SOLAR-C Plan A solar electric propulsion option. Present approach presents many designs that are better than the nominal design in all design objectives. Present approach also revealed some important design knowledge such as tradeoff information among maximization of final mass, maximization of final velocity, and maximization of minimum distance from the Sun. Present study also shows possibility of simultaneous design of trajectory and spacecraft.
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Infotech@Aerospace 2012(Infotech@Aerospace) 2012年
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Lecture Notes in Computer Science (including subseries Lecture Notes in Artificial Intelligence and Lecture Notes in Bioinformatics) 2012年Multi-objective evolutionary algorithms are increasingly being investigated to solve many-objective optimization problems. However, most algorithms recently proposed for many-objective optimization cannot find Pareto optimal solutions with good properties on convergence, spread, and distribution. Often, the algorithms favor one property at the expense of the other. In addition, in some applications it takes a very long time to evaluate solutions, which prohibits running the algorithm for a large number of generations. In this work to obtain good representations of the Pareto optimal set we investigate a large population MOEA, which employs adaptive ε-box dominance for selection and neighborhood recombination for variation, using a very short number of generations to evolve the population. We study the performance of the algorithm on some functions of the DTLZ family, showing the importance of using larger populations to search on many-objective problems and the effectiveness of employing adaptive ε-box dominance with neighborhood recombination that take into account the characteristics of many-objective landscapes. © 2012 Springer-Verlag.
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Lecture Notes in Computer Science (including subseries Lecture Notes in Artificial Intelligence and Lecture Notes in Bioinformatics) 2012年This work analyzes population size and neighborhood recombination in the context of many-objective optimization. Large populations might support better the evolutionary search to deal with the increased complexity inherent to high dimensional spaces, whereas neighborhood recombination can reduce dissimilarity between crossing individuals and would allow us to understand better the implications of a large number of solutions that are Pareto-optimal from the perspective of decision space and the operator of variation. Our aim is to understand why and how they improve the effectiveness of a dominance-based many-objective optimizer. To do that, we vary population size and analyze in detail convergence, front distribution, the distance between individuals that undergo crossover, and the distribution of solutions in objective space. We use DTLZ2 problem with m = 5 objectives in our study, revealing important properties of large populations, recombination in general, and neighborhood recombination in particular, related to convergence and distribution of solutions. © 2012 Springer-Verlag.
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ASTRODYNAMICS 2011, PTS I - IV 2012年 UNIVELT INCMultiobjective design exploration (MODE) framework is applied to the trajectory design optimization problem for SOLAR-C Plan A solar electric propulsion option. Present approach presents many designs that are better than the nominal design in all design objectives. Present approach also revealed some important design knowledge such as tradeoff information among maximization of final mass, maximization of final velocity, and maximization of minimum distance from the Sun. Present study also shows possibility of simultaneous design of trajectory and spacecraft.
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PROCEEDINGS OF THE ASME/JSME/KSME JOINT FLUIDS ENGINEERING CONFERENCE 2011, VOL 1, PTS A-D 2012年 AMER SOC MECHANICAL ENGINEERSThe flow fields around NACA0012 and NACA0002 at Reynolds number of 23,000, and their aerodynamic characteristics are analyzed. Computations are conducted with implicit large-eddy simulation solver and Reynolds-averaged-Navier-Stokes solver Around this Reynolds number the flow over an airfoil separates, transits and reattaches, resulting in generation of a laminar separation bubble at angle of attack in the range of certain degrees. Over a NACA0012 airfoil a separation point moves toward its leading edge with increasing angle of attack, and a separated flow may transit to create a short bubble. On the other hand, over a NACA0002 airfoil a separation point is kept at its leading edge, and a separated flow may transit to create a long bubble. Moreover there appears nonlinearity in lift curve for NACA0012 airfoil, but does not appear in that for NACA0002 in spite of existence of a laminar separation bubble.
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AERODYNAMIC DESIGN EXPLORATION FOR REUSABLE LAUNCH VEHICLE USING MULTI-OBJECTIVE GENETIC PROGRAMMINGPROCEEDINGS OF THE ASME INTERNATIONAL DESIGN ENGINEERING TECHNICAL CONFERENCES AND COMPUTERS AND INFORMATION IN ENGINEERING CONFERENCE, 2011, VOL 2, PTS A AND B 2012年 AMER SOC MECHANICAL ENGINEERSA new type of multi-objective genetic programming (MOGP) for design exploration is proposed. The feature of the new MOGP is the simultaneous symbolic regression to multiple variables using correlation coefficients. This methodology is applied to Pareto-optimal solutions of the multi-objective aerodynamic design optimization problem of a bi-conical shape reusable launch vehicle. The MOGP presents symbolic equations which have high correlations to zero-lift drag at supersonic condition, maximum lift-to-drag at supersonic condition and volume of shape through single MOGP run. These equations also have high correlation to another parameter of the body geometry. These results indicate that MOGP is capable of finding composite more efficient design parameters from original design parameters.
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PROCEEDINGS OF THE ASME INTERNATIONAL MECHANICAL ENGINEERING CONGRESS AND EXPOSITION - 2010, VOL 7, PTS A AND B 2012年 AMER SOC MECHANICAL ENGINEERSFrequency effects of the synthetic jet on the flow field over a backward facing step are investigated using numerical analysis. Three-dimensional Navier-Stokes equations are solved. Implicit large-eddy simulation using high-order compact difference scheme is conducted. The present analysis is addressed on the frequency characteristics of the synthetic jet for understanding frequency characteristics and flow filed. Three cases are analyzed; the case computing flow over backward facing step without control, the case computing flow with synthetic jet control at F-h(+) =0.2, and the case computing flow with synthetic jet control at F-h(+) =2.0, where non-dimensional frequency F-h(+) is normalized with the height of backward-facing step and the freestream velocity. The present computation shows that separation length in the case of the flow controlled at F-h(+) =0.2 is 20 percent shorter than the case without control. Strong two-dimensional vortices generated from the synthetic jet interact with the shear layer, which results in the increase of the Reynolds stress in the shear layer region. These vortices are deformed into three-dimensional structures, which make Reynolds stress stronger in the recirculation region. Size of the separation length in the case of the flow controlled at F-h(+) =2.0 is almost the same as the case without control because the mixing between the synthetic jet and the shear layer is not enhanced. Weak and short periodic vortices induced from the synthetic jet do not interacts with the shear layer very much and diffuse in the recirculation region.
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Civil-Comp Proceedings 2012年A numerical study of the effects of airfoil shape on low Reynolds number aerodynamics is presented. The large-eddy simulations are performed with 6 th-order compact finite difference scheme and 10th-order low pass filter, and 2nd-order backward implicit time integration with inner iterations. Systematic numerical excesses show the feasibility of the current simulations to predict flow fields around fixed-wing configurations involving a laminar separation and laminar-to-turbulence transition at low Reynolds number. At the Reynolds number of 2.3×104, two types of thin and asymmetric airfoils as a target airfoil shape of micro-size air vehicle are considered. The results show that the airfoil cross section affects the formation of a laminar separation bubble and the transition to turbulence in the three-dimensional flow around the wings at low angle of attack and hence significant influence on the aerodynamic performance. © Civil-Comp Press, 2012.
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年次大会 : Mechanical Engineering Congress, Japan 2011年9月11日 一般社団法人日本機械学会This paper presents applications of multiobjective design optimization (MDO) and multiobjective design exploration (MODE) in space engineering. These applications include hybrid rocket conceptual design, spacecraft trajectory design, rocket engine design and aerodynamic reusable sounding rocket design. This paper also discusses limitations of current MDO and MODE and presents real-world design optimization test problems and a new approach to extract useful design information from non-dominated solutions of optimization problems.
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年次大会 : Mechanical Engineering Congress, Japan 2011年9月11日 一般社団法人日本機械学会The dielectric barrier electric discharge plasma actuator is expected as a new technology which can make the design of an aerofoil etc. unnecessary. The boundary layer control might be able to be performed by induced velocity in the boundary layer as an effect of the dielectric substance barrier electrical discharge plasma actuator. Moreover, it also turns out that the control effectiveness increases by repeating ON and OFF of the applied voltage, which is called burst. In this study, separation control on an airfoil by a plasma actuator was performed, and its control effectiveness was evaluated. This paper showed the effective mechanism of burst control by PIV.
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Proceedings of ECCOMAS Thematic Conference on CFD and Optimization 2011年5月
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41st AIAA Fluid Dynamics Conference and Exhibit 2011年Appropriate frequencies for burst wave of a dielectric barrier discharge plasma actuator at a reference voltage are investigated by the low speed wind tunnel experiment for the airfoil separation control. Here, a reference voltage is defined as the minimum voltage for controlling a reference condition, and the reference voltage is adopted for each experimental conditions to eliminate errors caused by the degradation effect of the plasma actuator and individual variability. All the experiments are conducted with the flow condition Rec = 6.3 × 104 and α=12. Time-averaged pressure around the surface of the actuator- applied NACA0015 is measured. The results show that F+ of higher than 1 is more effective for separation control and appropriate F+ region considerably changes when BR and n are changed. © 2011 by Satoshi Sekimoto, Kengo Asada, Tatsuya Usami, Shinichiro Ito, Taku Nonomura, Akira Oyama, Kozo Fujii.
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ASME-JSME-KSME 2011 Joint Fluids Engineering Conference, AJK 2011 2011年The effects of aspect ratio and Reynolds number on aerodynamic characteristics of three-dimensional rectangular wing at low Reynolds number of 103 to 105, are investigated with Reynolds-averaged Navier-Stokes solver with the Baldwin-Lomax model. Present results show that lift coefficient decreases drastically at lower aspect ratio than 4. Besides, the much larger viscous drag coefficient is obtained at the lower Reynolds number, especially lower than 104. In order to focus on designing practical wings, the particular cases under the condition of fixed wing-surface area and fixed main stream velocity are conducted. The results show that there is trade-off between the decrease in viscous drag coefficient with increasing Reynolds number and the increase in lift coefficient with increasing aspect ratio. At the lower Reynolds number condition, as the former effect is stronger than the latter one, maximum lift-to-drag ratio is obtained at lower aspect ratio. Copyright © 2011 by ASME.
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ASME-JSME-KSME 2011 Joint Fluids Engineering Conference, AJK 2011 2011年An experimental study of plasma actuator on separation control is conducted. The plasma actuator is used for control of separated flow around NACA0015 airfoil. The Reynolds number based on chord length is set to 60, 000 and the angle of attack is set to 12[deg]. The plasma actuator is applied with normal mode and burst mode, where normal mode denotes continuous actuation and burst mode denotes temporary intermittent actuation. Also, actuations for co-flow blowing and counter blowing are conducted. The averaged pressure coefficients of wing surface and velocity fields are measured. For velocity fields, PIV measurement is adopted. Comparing counter and co-flow blowings of plasma actuator, the effects of counter blowing is investigated. Also, for both co-flow and counter blowing cases, we investigate the effects of burst mode. Through the series of experiments, following two types of mechanism for separation control will be discussed. One type is considered to be directly giving momentum in the boundary layer which seems to be more active in co-flow blowing with normal mode. The other type is considered to be enhancement of the mixing, leading to increase in momentum thickness of the boundary layer. The latter mechanism seems to be active in the burst mode with both co-flow and counter blowing. Copyright © 2011 by ASME.
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The 40th International Congress and Exposition on Control Engineering 2011年
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PROGRESS IN AEROSPACE SCIENCES 2010年7月 PERGAMON-ELSEVIER SCIENCE LTDEvolutionary algorithms (EAs) are useful tools in design optimization. Due to their simplicity, ease of use, and suitability for multi-objective design optimization problems, EAs have been applied to design optimization problems from various areas. In this paper we review the recent progress in design optimization using evolutionary algorithms to solve real-world aerodynamic problems. Examples are given in the design of turbo pump, compressor, and micro-air vehicles. The paper covers the following topics that are deemed important to solve a large optimization problem from a practical viewpoint: (1) hybridized approaches to speed up the convergence rate of EAs; (2) the use of surrogate model to reduce the computational cost stemmed from EAs; (3) reliability based design optimization using EAs; and (4) data mining of Pareto-optimal solutions. Published by Elsevier Ltd.
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年次大会講演論文集 2010年 一般社団法人日本機械学会The dielectric barrier electric discharge plasma actuator is expected as a new technology which can make the design of an aerofoil etc. unnecessary. The boundary layer control might be able to be performed by induced velocity in the boundary layer as an effect of the dielectric substance barrier electrical discharge plasma actuator. Moreover, it also turns out that the control effectiveness increases by repeating ON and OFF of the applied voltage, which is called burst. But, the control mechanism is unknown. In this study, separation control on an airfoil by a plasma actuator was performed, and its control effectiveness was evaluated. The result showed a possibility to change the control effectiveness with the burst frequency mainly.
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40th AIAA Fluid Dynamics Conference 2010年Supersonic flow over a three-dimensional rectangular cavity with length-to-depth ratio of 2 is numerically studied by implicit large-eddy simulation to clarify the feedback-loop mechanism. A feedback-loop cycle is described and visualized with phase-averaged analysis of simulation results. Causality between the feedback acoustic wave and leading-edge shedding vortex is clearly demonstrated. Mach wave reflection at trailing edge is turned out to be the generation mechanism of feedback acoustic wave. It is convinced by investigating time-series instantaneous flowfields and auto-correlation coefficients of three simulation cases with different convective Mach number. Components of compression waves in supersonic cavity flows are summarized and their features are discussed. Proper orthogonal Decomposition (POD) in frequency domain is firstly employed to analyze wave propagations inside cavity. Results statistically show the propagation traces of notable compression waves inside cavity which are affected by high-speed recirculation flows. © 2010 by the American Institute of Aeronautics and Astronautics, Inc.
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Proceedings of the 11th Annual Genetic and Evolutionary Computation Conference, GECCO-2009 2009年A new approach to extract useful design information from non-dominated solutions of real-world multiobjective optimization problems is proposed. The proposed approach enables an analysis of line, face, or volume data that Pareto-optimal solutions have such as flow field and stress distribution by decomposing the data into principal modes using proper orthogonal decomposition. Analysis of the shape and surface pressure data of the non-dominated solutions of an aerodynamic transonic airfoil shape optimization problem shows capability of the proposed approach for design knowledge extraction for real-world design optimization problems.
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DETC 2008: PROCEEDINGS OF THE ASME INTERNATIONAL DESIGN ENGINEERING TECHNICAL CONFERENCES AND COMPUTERS AND INFORMATIONAL IN ENGINEERING CONFERENCE, VOL 3, PTS A AND B 2009年 AMER SOC MECHANICAL ENGINEERSComprehensive failure network analysis method was studied for liquid rocket engine development which includes failure propagation through various types of component interfaces in order to achieve exhaustive enumeration of possible failures and to identify actions to eliminate or reduce the potential failure. New failure network visualization method was developed in order to make it easier to understand complicated failure propagation mechanism among multiple system levels. Verification analysis method is developed in which it is verified all of user-specified component interfaces are contained in the failure network analysis result. The perceived component interface is specified by the analyzer and the failure propagation in the result of failure analysis is summarized in two separate N2 charts. By comparing with these two N2 charts, unperceived component interface and the unconsidered failure propagation can be found. It is found to be promising approach to achieve exhaustive enumeration especially for forgettable component interface.
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the International Symposium on Advanced Technology for High Performance Aircraft Core Parts Design 2008 2008年5月29日 招待有り
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Proceedings of the ASME Fluids Engineering Division Summer Conference - 2005, Vol 1, Pts A and B 2005年 AMER SOC MECHANICAL ENGINEERSFlow fields of Mach number 2.2 jet impinging on an inclined flat plate are experimentally investigated using the Pressure Sensitive Paints (PSP) and Schlieren flow visualization. The flow filed structure is mainly determined by two geometrical parameters (nozzle-plate distance and plate angle against the jet) and one flow parameter (pressure ratio). The results suggest that all the observed flow fields can actually be classified into three types of flow structure based on the three parameters above. As an extension of the authors' earlier work, experiments are carried out for higher plate angles. The new results show the effectiveness and limitation of the classification that we proposed. To find out the flow structure, some of the flow fields are computationally simulated. Good agreement of the pressure distributions with the experiment validates the simulation. Although analysis so far is limited, the result reveals three dimensional complex flow structure that created pressure peaks over the plate surface.
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2005 IEEE CONGRESS ON EVOLUTIONARY COMPUTATION, VOLS 1-3, PROCEEDINGS 2005年 IEEEAn 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.
共同研究・競争的資金等の研究課題
7-
日本学術振興会 科学研究費補助金 2014年4月 - 2017年3月
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日本学術会議 科学研究費補助金 2012年4月 - 2015年3月
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日本学術振興会 科学研究費補助金 2011年4月 - 2013年3月
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日本学術会議 科学研究費補助金 2008年4月 - 2011年3月
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日本学術振興会 科学研究費補助金 2008年4月 - 2010年3月
