論文リスト
(学会発表論文および一部の学術雑誌論文のPDFファイルがDLできます)


著書(分担執筆) 解説記事 学術雑誌論文  国 際学会発表 国内学会発表 翻訳 博士論文


著書(分担執筆)

[1] Shigeru Obayashi and Akira Oyama, “Adaptive Range Genetic Algorithms,” Chapter 5 of “Genetic Algorithms in Aeronautics and Turbomachinery,” editors: Jacques Periaux, Gerard Degrez and Mourad Sefrioui, John Wiley & Sons Limited, Chichester, U.K., 2003.

[2] Akira Oyama, "Constraint Handling in Evolutionary Aerodynamic Design," in "Constraint-Handling in Evolutionary Optimization," editor: Efren Mezura-Montes, Springer-Verlag GmbH, Heidelberg, Germany, ISBN 36420061832009, 2009.

[3] Akira Oyama and Kozo Fujii, "Multiobjective Design Exploration in Space Engineering," in "New Fundamental Technologies in DATA MINING," editor: Kimito Funatsu and Kiyoshi Hasegawa, IN-TECH, Vienna, Austria, 2011.


解説記事

[ 1] 大山聖,藤井孝藏,JAXA/ISASにおけるロケット・宇宙機研究開発へのCFDの活用,ながれ 24巻,第3号 pp.289-296,2005.

[ 2] 大山聖,藤本圭一郎,飯塚宣行,角有司,川添通宏,高木亮治,藤井孝藏,沖田耕一,JAXA基幹ロケットの信頼性向上へ向けたバルブ開発プロセス革新への 取り組み,設計工学(日本設計工学会学会誌),第43巻,第4号,pp.203-210, 2008年4月.

[ 3] 谷直樹,吉田義樹,大山聖,山西伸宏,低比速度インペラにおけるオープン型とクローズド型の最適形状の比較,ターボ機械 2010年04月号,日本工業出版,2010年4月.

[ 4] 大山聖,多目的設計探査と宇宙工学への利用,システム/制御/情報,Vol. 55, No. 9, pp. 374-381, 2011.

[ 5] 大山聖,宇宙工学分野での進化型計算の利用,電気学会誌,Vol. 132 (4), pp. 208-211, 2012.

[ 6] 大山聖,岡田浩一,浅田健吾,野々村拓,宮路幸二,藤井孝藏,シンセティックジェットによる流れの能動制御,日本航空宇宙学会誌,Vol.61(2), pp. 57-63, 2013.

[ 7] 大山聖,ロケット射点形状の空力音響多目的設計探査,CMDニュースレター,第51号,2013.

[ 8] 大山聖,立川智章,野々村拓,藤井孝藏,空力音響多目的設計探査 - ロケット射点形状設計への適用-,ターボ機械,2014年5月号,ターボ機械協会,2014.

[ 9] 大山聖,第45期年会講演会開催報告,日本航空宇宙学会誌,第62巻,第7号,pp.248-249, 2014.


学術雑誌論文

[1] 大山聖, 大林茂, 中橋和博, 中村孝, 遺伝的アルゴリズムを用いた三次元翼の空力最適化,日 本航空宇宙学会誌, 第46巻, 第539号, pp.682-686, 1998年.

[2] Oyama, A., Obayashi, S., Nakahashi, K., and Nakamura, “Euler/Navier-Stokes Optimization of Supersonic Wing Design Based on Evolutionary Algorithm,” AIAA Journal, Vol.37, No.10, pp.1327-1329, October 1999. (10)
An evolutionary algorithm (EA) coupled with a Euler/Navier-Stokes code has been applied to supersonic wing shape design. Aerodynamic evaluations are distributed to the processing elements (PE) of the numerical wind tunnel (NWT) to overcome the enormous computational time necessary for the optimization. The design yields both the minimum drag and the minimum volume wave drag in the given design space. The important features of supersonic wing design as compared with conventional transonic wing design are presented.

[3] Akira Oyama, Shigeru Obayashi, Kazuhiro Nakahashi, and Naoki Hirose, “Aerodynamic Wing Optimization via Evolutionary Algorithms based on structured coding,” CFD Journal, Vol.8, No.4, pp. 570-577, January 2000.
Evolutionary Algorithms (EAs) based on structured coding have been proposed for aerodynamic optimization of wing design. Fractional factorial design is used to investigate interactions of the design variables to determine the appropriate coding structure for EAs in advance. The present EAs is applied to wing design problems where the wing shape is modeled using the parameter set for the extended Joukowski airfoils and the PARSEC airfoils. Aerodynamic optimizations of a transonic wing demonstrated that the structured coding for EAs is a promising approach to find a global optimum in real-world applications. The design results also confirm that the PARSEC is an efficient approach for transonic wing shape parameterization.

[4] Akira Oyama, Shigeru Obayashi, and Kazuhiro Nakahashi, “Real-Coded Adaptive Range Genetic Algorithm and Its Application to Aerodynamic Design,” JSME International Journal, Series A, Vol. 43, No. 2, pp. 124-129, February 2000. (13)
Real-coded Adaptive Range Genetic Algorithms (ARGAs) have been developed. The real-coded ARGAs possess both advantages of the binary-coded ARGAs and the use of the floating point representation to overcome the problems of having a large search space that requires continuous sampling. First, the efficiency and the robustness of the proposed approach are demonstrated by test functions. Then the proposed approach is applied to an aerodynamic airfoil shape optimization problem. The results confirm that the real-coded ARGAs consistently find better solutions than the conventional real-coded Genetic Algorithms do. The designed airfoil shape is considered to be the global optimal and thus ensures the feasibility of the real-coded ARGAs in aerodynamic designs.

[5] Akira Oyama, Shigeru Obayashi, and Takashi Nakamura, “Real-Coded Adaptive Range Genetic Algorithm Applied to Transonic Wing Optimization,” Applied Soft Computing, Vol. 1, No. 3, pp. 179-187, 2001. (16)
Real-coded Adaptive Range Genetic Algorithm (ARGA) has been applied to a practical three-dimensional shape optimization for aerodynamic design of an aircraft wing. The real-coded ARGA possesses both advantages of the binary-coded ARGA and the floating-point representation to overcome the problems of having a large search space that requires continuous sampling. The results confirm that the real-coded ARGA consistently finds better solutions than the conventional real-coded Genetic Algorithms do.

[6] 蓮池尚彦, 大山聖, 中橋和博, 大林茂, 2次元翼型失速限界のCFD予測,日本航空宇宙学会論文集, 第50巻, 577号, pp.56-63, 2002年2月.

[7] Akira Oyama, and Meng-Sing Liou, “Multiobjective Optimization of Rocket Engine Pumps Using Evolutionary Algorithm,” AIAA Journal of Propulsion and Power, Vol. 18, No. 3, pp. 528-535, 2002. (6)
A design optimization method for turbopumps of cryogenic rocket engines has been developed. Multiobjective Evolutionary Algorithm is used for multiobjective pump design optimizations. Performances of design candidates are evaluated by using the meanline pump flow-modeling method based on the Euler turbine equation coupled with empirical correlations for rotor efficiency. To demonstrate feasibility of the present approach, single stage centrifugal pump and multistage pump design optimizations are performed. Number of pump performance evaluations necessary to obtain a reasonable Pareto-optimal set for the conceptual rocket engine pump design will be investigated using the single stage centrifugal pump design optimization. In both design optimizations, the present method obtains hundreds of reasonable and uniformly distributed Pareto-optimal solutions that include some designs outperforming the original design in total head while reducing input power by 1%. Detailed observation of the design results also reveals some important design criteria for turbopumps in cryogenic rocket engines. These results demonstrate the feasibility of the evolutionary algorithm-based multiobjective design optimization method in this field.

[8] Akira Oyama, and Meng-Sing Liou, "Design Optimizations of Turbomachines Using Evolutionary Algorithm",” Transactions of the Aeronautical and Astronautical Society of the Republic of China, Vol. 34, No. 2, pp. 528-535, June 87-102, 2002. (1)
Numerical optimization tools based on Evolutionary Algorithm (EA) have been developed for single-objective and multiobjective aerodynamic turbomachinery design optimizations. The present method uses real-coded adaptive range genetic algorithm for single-objective optimization. A standard multiobjective evolutionary algorithm is used for multiobjective optimizations. First, single-objective aerodynamic design optimization of a compressor rotor using a three-dimensional Navier-Stokes code is demonstrated. The optimized design successfully reduced entropy production by more than 19% while satisfying constraints on the mass flow rate and the pressure ratio. This study also showed that parallelization efficiency of EA is almost 100% for three-dimensional Navier-Stokes optimizations. Next, multiobjective preliminary design optimization of a cryogenic rocket engine turbopump is presented. The present method successfully captured reasonable Pareto-optimal solutions that include designs outperforming the baseline design in all objectives. Finally, multiobjective aerodynamic design optimization of a multi-stage compressor using a through-flow code is demonstrated. The present method successfully found numerous designs better than the baseline design in all objectives. These result shows that the present method offers a promising approach to turbomachinery and propulsion system designer to design a better machine, while shortening design cycle and reducing design costs.

[9] Shigeru Obayashi, Daisuke Sasaki, and Akira Oyama, "Finding Tradeoffs by Using Multiobjective Optimization Algorithms," Transactions of the Japan Society for Aeronautical and Space Sciences, Vol. 47, No. 155, pp. 51-58, May 2004. (8)
The objective of the present study is to demonstrate performances of Evolutionary Algorithms (EAs) and conventional gradient-based methods for finding Pareto fronts. The multiobjective optimization algorithms are applied to analytical test problems as well as to the real-world problems of a compressor design. The comparison results clearly indicate the superiority of EAs in finding tradeoffs.

[10] Akira Oyama, Meng-Sing Liou, and Shigeru Obayashi, "Transonic Axial-Flow Blade Optimization Using Evolutionary Algorithms and a Three-Dimensional Navier-Stokes Solver," AIAA Journal of Propulsion and Power, Vol. 20, No. 4, pp. 612-619, July-August, 2004. (10)
The objective of this study was to develop a high-fidelity aerodynamic design optimization tool based on evolutionary algorithms for turbomachinery. A three-dimensional Navier-Stokes solver was used for aerodynamic analysis so that flow fields would be represented accurately and that realistic and reliable designs would be produced. For efficient and robust design optimization, the real-coded adaptive range genetic algorithm was adopted, and the computation was parallelized and performed on an SGI Origin 2000 cluster to reduce turnaround time. The aerodynamic redesign of the NASA rotor 67 blade demonstrated the superiority of the present method over the conventional design approach, increasing adiabatic efficiency by 2 percent over the original design, not only at the design condition but over the entire operating range. This design optimization method has proven to be suitable for parallel computing. This study shows that this promising tool can help turbomachinery designers to design higher performance machines, while shortening the design cycle and reducing design costs.

[11] Akira Oyama, Koji Shimoyama, and Kozo Fujii, “New Constraint-Handling Method for Multi-Objective and Multi-Constraint Evolutionary Optimization,” Transactions of the Japan Society for Aeronautical and Space Sciences, Vol. 50, No. 167, pp. 56-62, May 2007.
A new constraint-handling method based on Pareto-optimality and niching concepts for multi-objective multi-constraint evolutionary optimization is proposed. The proposed method does not require any constants to be tuned for constraint-handling. In addition, the present method does not use the weighted-sum of constraints and thus does not require tuning of weight coefficients and is efficient even when all individuals in the initial population are infeasible or the amount of violation of each constraint is significantly different. The proposed approach is demonstrated to be remarkably more robust than the dynamic penalty approach and other dominance-based approaches through the optimal design of a welded beam and conceptual design optimization of a two-stage-to-orbit spaceplane.

[12] Kazuhisa Chiba, Akira Oyama, Shigeru Obayashi, Kazuhiro Nakahashi, and Hiroyuki Morino, “Multidisciplinary Design Optimization and Data Mining for Transonic Regional-Jet Wing,” Journal of Aircraft, Vol. 44, No. 4, pp. 1100-1112, 2007. (3)
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. Adaptive Range Multi-Objective Genetic Algorithm was employed as an optimizer. The objective functions were minimizations of block fuel and maximum take off weight in addition to drag divergence between transonic and subsonic fight conditions. As a result, nine non-dominated 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 non-gull wing geometry, although the present MDO results showed the inverted gull-wings as non-dominated solutions. When this knowledge was applied to one optimum solution, the resulting design was found to have better performance and to achieve 3.6 percent improvement in the block fuel compared to the original geometry designed in the conventional manner.

[13] Koji Shimoyama, Akira Oyama, and Kozo Fujii, “Development of Multi-Objective Six-Sigma Approach for Robust Design Optimization,” Journal of Aerospace Computing, Information, and Communication, Vol. 5, August 2008.
In this study, a new optimization approach for robust design, design for multi-objective six sigma, has been developed and applied to three robust optimization problems. The design for multiobjective six sigma build s on the ideas of design for six sigma, coupled with multi-objective evolutionary algorithm, for an enhanced capability to reveal trade off information considering both optimality and robustness of design. While design for six sigma require careful input parameter setting, design for multi-objective six sigma needs no such prior tuning, plus it can reveal the tradeoff information in a single optimization run. Three robust optimization problems were taken as to demonstrate the capabilities of design for multi-objective six sigma. Results indicate that design for multi-objective six sigma has a more practical and more efficient capability than the design for six sigma to reveal tradeoff design information considering both optimality and robustness of design.

[14] Akira Oyama, Yoshiyuki Okabe, Koji Shimoyama, and Kozo Fujii, "Aerodynamic Multiobjective Design Exploration of a Flapping Airfoil Using a Navier-Stokes Solver," Journal of Aerospace Computing, Information, and Communication, Vol. 6, No. 3, pp. 256-270, doi:10.2514/1.35992, 2009.
Aerodynamic knowledge for flapping airfoil is obtained by application of the multi-objective design exploration framework to a multi-objective aerodynamic flapping airfoil design optimization problem. The objectives of the design optimization problem are 1)time-averaged lift coefficient maximization, 2)time-averaged drag coefficient minimization, and 3)time-averaged required power coefficient where the airfoil oscillates in plunging and pitching modes. Pareto-optimal solutions are obtained by a multi-objective evolutionary optimization and analyzed with the self-organizing map. Aerodynamic performance of each flapping airfoil is evaluated by a two-dimensional Navier-Stokes solver. Analysis of the flow over the extreme Pareto-optimal flapping airfoils provides insights into flow mechanism for thrust maximization, lift maximization, and required power minimization. Analysis of the design objectives and design parameters with the self-organizing map leads to useful guidelines for practical flapping-wing micro air vehicles. The present result ensures that the multi-objective design exploration framework is useful approach for real world design optimization problems.

[15] 久保田 孝,尾川 順子,藤田 和央,大山 聖,藤井 孝蔵, MELOSのミッション検討と工学的チャレンジ,日本惑星科学会学会誌「遊・星・人」,Vol.18, No.2, 2009.

[16] Yongsheng Lian, Akira Oyama, and Meng-Sing Liou "Progress in design optimization using evolutionary algorithms for aerodynamic problems ," Progress in Aerospace Sciences (Online publication), JPAS235, DOI:10.1016/j.paerosci.2009.08.003, September 24, 2009,
Evolutionary 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.

[17] Koichi Okada, Akira Oyama, Kozo Fujii, and Koji Miyaji, “Computational Study on Effect of Synthetic Jet Design Parameters,” International Journal of Aerospace Engineering, Volume 2010, ID 364859, doi:10.1155/2010/364859, online journal, 2010.
Effects of amplitude and frequency of synthetic jet on the characteristics of induced jet are investigated. To estimate effects of the parameters, flow inside the synthetic jet cavity and orifice and the outer flow is simultaneously simulated using large-eddy simulation (LES). Comparison of the present LES result with the experimental data shows that three-dimensional LES of the flow inside the cavity is essential for accurate estimation of the velocity and velocity fluctuation of the synthetic jet. Comparison of the present results under various flow conditions shows that amplitude and frequency can control profiles of time-averaged vertical velocity and fluctuation of the vertical velocity as well as damping rate of the induced velocity and fluctuation.

[18] Akira Oyama, Taku Nonomura, and Kozo Fujii, “Data Mining of Pareto-Optimal Transonic Airfoil Shapes Using Proper Orthogonal Decomposition,” Journal of Aircraft, Vol.47, No. 5, pp.1756-1762, doi:10.2514/1.52081, 2010.
A new approach to extract useful design information from shape data of Pareto-optimal solutions of an optimization problem is proposed and applied to the optimization of airfoil shapes for good aerodynamic performance at transonic speed. The proposed approach decomposes shape data into principal modes and corresponding base vectors using proper orthogonal decomposition (POD). Advantage of the proposed approach is that the knowledge one can obtain does not depend on how the shape is parameterized for design optimization. Analysis of the airfoil shapes obtained as the Pareto-optimal solutions for aerodynamic performance at transonic speeds shows that the optimized airfoils can be categorized into three families (low drag designs, high lift-to-drag designs, and high lift designs), where the lift is increased by changing the camber near the trailing edge among the low drag designs while the lift is increased by moving the lower surface upward among the high lift designs.

[19] 滑慶則,高木亮治,大山聖,藤井孝藏,山本誠,再使用観測ロケット空力形状に関する設計探査 ,日本機械学会論文集C編,第76巻,第771号,pp.2811-2818, 2010.
Aerodynamic characteristics of a reusable observation vehicle are computationally investigated under subsonic and supersonic flight conditions as a preliminary study for the concept design using a design exploration method and a light CFD tool. The results show that the simulations with a coarse grid can accurately estimate the aerodynamic characteristics like axial force coefficient and the lift to drag ratio. The results of the aerodynamic shape exploration indicate tradeoff information among objective functions, and the correlation between design variables and objective functions. The preliminary knowledge for the aerodynamic shape design is obtained.

[20] Koichi Okada, Akira Oyama, Kozo Fujii, and Koji Miyaji, "Computational Study of Effects of Nondimensional Parameters on Synthetic Jets," Transactions of the Japan Society for Aeronautical and Space Sciences, Vol. 55, No. 1, pp. 1-11, January, 2012.

[21] Ittetsu Kaneda, Satoshi Sekimoto, Taku Nonomura, Kengo Asada, Akira Oyama, and Kozo Fujii, "An Effective Three-Dimensional Layout of Actuation Body Force for Separation Control," International Journal of Aerospace Engineering, Vol.2012, Article ID 786960, 2012.

[22] 立川智章,大山聖,藤井孝藏,GPを用いた非劣解からの設計情報の抽出,進化計算学会論文誌,Vol. 3 (3), pp.133-142, 2012.

[23] Weipeng Li, Taku Nonomura, Akira Oyama, Kozo Fujii, “Feedback Mechanism in Supersonic Lminar Cavity Flows,” AIAA Journal, Vol.51, pp.253-257, 2013.

[24] Ryoji Kojima, Taku Nonomura, Akira Oyama, Kozo Fujii, “Large-Eddy Simulation of Low-Reynolds-Number Flow Over Thick and Thin NACA Airfoils,” Journal of Aircraft, Vol. 50, pp. 187-196, 2013.

[25] Tomoaki Tatsukawa, Taku Nonomura, Akira Oyama, Kozo Fujii, “Aerodynamic Design Exploration for Resusable Launch Vehicle Using Genetic Algorithm with Navier-Stokes Solver,” Transactions of the Japan Society for Aeronautical and Space Sciences, Vol. 6182, pp. 57-63, 2013.

[26] Tianshu Liu, Akira Oyama, and Kozo Fujii, “Scaling Analysis of Propeller-Driven Aircraft for Mars Exploration,” Journal of Aircraft, Vol.50, No. 5, 2013.

The scaling relations between the performance parameters of propeller-driven aircraft flying on Mars and Earth are discussed, including the cruising velocity, power required for cruising flight, and propulsive power generated by propellers. The power ratio criterion for feasible cruising flight of propeller-driven aircraft on Mars is proposed, and the relevant design parameters are identified. This criterion is first used to examine the feasibility of typical and nontypical aircraft for cruising flight on Mars, and then applied as a guideline to the preliminary design of the sample Martian aircraft. In addition, the constraints on the rotational speed of a propeller in cruising flight onMars are given, which should be considered in the design of propellers. The methods developed in this paper are also applicable to other space exploration aircraft for Venus and Titan.

[27] Masayuki Anyoji, Masato Okamoto, Hidenori Hidaka, Katsutoshi Kondo, Akira Oyama, Hiroki Nagai, Kozo Fujii, "Control surface effectiveness of low Reynolds number flight vehicles," Journal of Fluid Science and Technology, Vol. 9, No. 5, 2014.

[28] Masayuki Anyoji, Taku Nonomura, Hikaru Aono, Akira Oyama, Kozo Fujii, Hiroki Nagai, Keisuke Asai, "Computational and Experimental Analysis of a High Performance Airfoil under Low-Reynolds-Number Flow Condition," Journal of Aircraft, Vol.51, No.6, pp.1864-1872, doi: 10.2514/1.C032553, 2014.

[29] Masayuki Anyoji, Masato Okamoto, M Higaka, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Planetary Atmosphere Wind Tunnel Tests on Aerodynamic Characteristics of a Mars Airplane Scale Model," Transactions of JSASS Aerospace, Technology Japan, Vol.12, No. ists29, pp. Tk_7-Tk_12, 2014.

[30] Katsutoshi Kondo, Hikaru Aono, Taku Nonomura, Masayuki Anyoji, Tianshu Liu, Akira Oyama, Kozo Fujii, and Makoto Yamamoto, "Analysis of Owl-like Airfoil Aerodynamics at Low Reynolds Number Flow," Transactions of JSASS Aerospace, Technology Japan, Vol.12, No. ists29, pp. Tk_35-Tk_40, 2014.

[31] Naoya Fujioka, Taku Nonomura, Akira Oyama, Kozo Fujii, and Makoto Yamamoto, "Computational Analysis of Aerodynamics Performance of Mars Airplane," Transactions of JSASS Aerospace, Technology Japan, Vol.12, No. ists29, pp. Tk_1-Tk_5, 2014.

[32] DongHwi Lee, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Comparison of Numerical Methods Evaluating Airfoil Aerodynamic Characteristics at Low Reynolds Number," Journal of Aircraft, Vol.52, No.1, pp.296-306, doi: 10.2514/1.C032721, 2015.

[33] Donghwi Lee, Soshi Kawai, Taku Nonomura, Masayuki Anyoji, Hikaru Aono, Akira Oyama, Keisuke Asai, and Kozo Fujii, "Mechanisms of Surface Pressure Distribution within a Laminer Separation Bubble at Different Reynolds Numbers," Physics of Fluids, Vol. 27, 023602, doi: 10.1063/1.49135000, 2015.



招待講演/基調講演

[1] 大山聖,多目的設計最適化による設計探査と火星航空機の設計への応用多目的最適化設計,第6回多目的最適化ワークショップ,神奈川県横浜市,2006.

[2] Akira Oyama, Yoshiyuki Okabe, Koji Shimoyama, and Kozo Fujii, "MULTIOBJECTIVE DESIGN EXPLORATION AND ITS APPLICATION TO AN AERODYNAMIC FLAPPING AIRFOIL DESIGN," The International Symposium on Advanced Technology for High Performance Aircraft Core Parts Design 2008," Gyeongsang National University, Jinju, Korea, May 29-30, 2008.
Aerodynamic knowledge for flapping airfoil is obtained by application of the multi-objective design exploration framework to a multiobjective aerodynamic flapping airfoil design optimization problem, where the airfoil oscillates in plunging and pitching modes. Pareto-optimal solutions are obtained by a multiobjective evolutionary optimization and analyzed with the self-organizing map. Aerodynamic performance of each flapping airfoil is evaluated by a two-dimensional Navier-Stokes solver.  Analysis of the flow over the extreme Pareto-optimal flapping airfoils provides insights into flow mechanism for thrust maximization, lift maximization, and required power minimization. Analysis of the design objectives and design parameters with the self-organizing map leads to useful guidelines for practical flapping-wing micro air vehicles.

[3] Akira Oyama, Koji Shimoyama, and Kozo Fujii, "AN APPROACH FOR ROBUST DESIGN: MULTI-OBJECTIVE SIX SIGMA APPROACH," The International Symposium on Advanced Technology for High Performance Aircraft Core Parts Design 2008," Gyeongsang National University, Jinju, Korea, May 29-30, 2008.
A new optimization approach for robust design, design for multi-objective six sigma (DFMOSS) has been developed and applied to a robust aerodynamic airfoil design for Mars exploratory airplane. The present robust aerodynamic airfoil design optimization using DFMOSS successfully showed the trade-off information between maximization and robustness improvement in aerodynamic performance in a single optimization run without careful input parameter tuning. The obtained trade-off information indicated that an airfoil with a smaller maximum camber improves robustness in terms of lift to drag ratio against the variation of flight Mach number.

[4] Akira Oyama, "POD-based data mining for Multi-Objective Design Exploration," International Workshop on Multi-Objective Design Exploration for Aerospace Engineering, Sendai, Japan, March 19, 2009.

[5] 大 山聖,パレート最適解のもつデー タからの設計知識の抽出法,第34回関西設計工学研究会,大阪府大阪市,3月,2010.

[6] 大山聖,宇宙科学分野における最適化問題について ーハイブリッドロケットエンジンの 概念設計最適化ー,第35回関西設計工学研究会,大阪府大阪市,8月,2010.

[7] 大山聖,宇宙工学分野における進化計算の適用事例紹介,計測制御システム分野における産学若手交流セミナー,静岡県熱海市,9月,2010.

[8] 藤井孝藏,大山聖,低騒音・低エネルギを実現するプラズマ利用の流体制御,第71回秋季応用物理学会学術講演会特別シンポジウム,長崎県長崎市,9月14 日〜17日,2010.

[9] 大山聖,次期太陽観測衛星軌道の多目的設計探査,第127回NEC C&CシステムSP研究会,2月,2011.

[10] 大山聖,他,火星探査用小型飛行機の検討,日 本航空宇宙学会第42期講演会,4月14日-4月15日,2011.

[11] 大山聖,ハイブリッドロケットの概念設計検討法と非劣解データのモード解析法,日本機械学会2011年度年次大会「先端技術フォーラム」,目黒区,東京 都,9月,2011.

[12] Akira Oyama, Data Mining of Pareto-Optimal Solutions Using Proper Orthogonal Decomposition,"  International Workshop on Future of CFD and Aerospace Sciences, May 23-25, Kobe, Japan, 2012.

[13] 大山聖 ,宇宙工学分野における多目的設計探査の活用事例 ,第56回システム制御情報学会研究発表講演会,京都市,京都府,5月21-23日,2012.

[14] Akira Oyama,"Applications of Multiobjective Design Exploration in JAXA," Workshop on Multi-Objective Design Exploration for Real-World Design Optimization Problems 2012, Karuizawa, Nagano, Japan, Dec. 16-17, 2012.

[15] 大山聖,火星探査航空機ワーキンググループ,世界初の火星飛行機の実現を目指して,第13回宇宙科学シンポジウム,神奈川県相模原市,1月8日9日, 2013.

[16] 大山聖,火星飛行機,日本航空宇宙学会北部支部2013年講演会ならびに第14回再使用型宇宙推進系シンポジウム,仙台市,宮城県,3月14日15日, 2013

[17] 大山聖,多目的設計探査による設計知見の抽出,統計数理研究所研究会シミュレーション科学と統計科学の間,東京都立川市,3月18日,2012.

[18] 大山聖,スーパーコンピュータ「京」を用いた多目的設計探査による設計手法の革新とJAXAでの試み,システム制御情報学会セミナー2013,2013.

[19] 大山聖,LESを用いたロケット射点形状の多目的空力音響設計探査,第4回分野4次世代ものづくりシンポジウム,2013.

[20] 大山聖,京コンピュータで可能になった多目的設計探査の新展開 - 空力音響多目的設計最適化と多数目的設計最適化 - ,ターボ機械協会第112回セミナー「CFD最新動向と最適化技術の新展開」,2014年2月14日.

[21] 大山聖,多数の目的関数を持つ設計最適化手法の効率的解法,文部科学省「HPCI戦略プログラム」分野4次世代ものづくり第1回統合ワークショップ「共通基盤・先端アプリ・PF」部門 ,東京大学生産技術研究所,2014年3月13日.

[22] 大山聖,スーパーコンピュータ「京」を用いた多目的設計探査の革新,第4回知能工学部会研究会「賢さの先端研究会」 / 第51回システム工学部会研究会,近畿大学東大阪キャンパス,2014年8月29日.

[23] 竹内伸介,佐藤英一,大山聖,永井大樹,LPSO型Mg合金を用いた火星探査航空機用軽量翼構造の試作,第58回日本学術会議材料工学連合講演会,京都府京都市,2014年10月27-28日.

[24] 大山聖,「京」を利用した多目的設計探査の事例紹介,第5回分野4次世代ものづくりシンポジウム,兵庫県神戸市,2014年12月5日.

[25] 大山聖,ものづくりのための多目的設計探査,文部科学省「HPCI戦略プログラム」分野4次世代ものづくり第2回統合ワークショップ,兵庫県神戸市,2014年12月5日.

[26] 小野謙二,大山聖,ポスト京に向けた取り組みについて,文部科学省「HPCI戦略プログラム」分野4次世代ものづくり第2回統合ワークショップ,兵庫県神戸市,2014年12月5日.

[27] 大山聖,小野謙二,上流設計プラットフォーム,第1回ポスト「京」重点課題E・G合同シンポジウム,東京大学生産技術研究所,2015年3月20日.



国際会議

[1] Shigeru Obayashi, and Akira Oyama, “Three-dimensional Aerodynamic Optimization with Genetic Algorithm,” Proceedings of the Third ECCOMAS Computational Fluid Dynamics Conference, John Wiley & Sons Ltd, Chichester, the Third ECCOMAS Computational Fluid Dynamics Conference, Paris, France, September 9-13, 1996.
A Genetic Algorithm has been applied to optimize a wing shape for generic subsonic transportation aircraft by using Navier-Stokes computations. To overcome enormous computational time necessary for this optimization, Numerical Wind tunnel at National Aerospace Laboratory, a parallel vector machine with 166 processing elements, was used. Design results indicate feasibility of the present approach for the aerodynamic optimization in advanced computational environments.

[2] Akira Oyama, Shigeru Obayashi, Kazuhiro Nakahashi, and Takashi Nakamura, “Transonic Wing Optimization Using Genetic Algorithm,” AIAA Paper 97-1854, AIAA 13th Computational Fluid Dynamics Conference, Snow mass, Colorado, June 1997.
A Genetic Algorithm (GA) has been applied to optimize a transonic wing shape for generic transport aircraft. A three-dimensional compressible Navier-Stokes (N-S) solver is used to evaluate aerodynamic performance. Designed wings show a tradeoff between an increase of the airfoil thickness driven by a structural constraint and a reduction of the wave drag produced by a shock wave. The present result indicates that GA has found a best feasible solution in the given design constraints.

[3] Akira Oyama, Shigeru Obayashi, Kazuhiro Nakahashi, and Takashi Nakamura, “Euler/Navier-Stokes Optimization of Supersonic Wing Design Based on Evolutionary Algorithm,” Proceedings of the 10th International Conference on Parallel CFD, Hsinchu, Taiwan, May 1998.
This paper presents aerodynamic shape optimization of a supersonic wing for supersonic civil transportation (SST) using an Evolutionary Algorithm (EA) coupled with an Euler/Navier-Stokes code. To overcome enormous computational time necessary for the design, aerodynamic evaluations are parallelized on Numerical Wind Tunnel (NWT) at National Aerospace Laboratory, a parallel vector machine with 166 processing elements. Parallelization of function evaluations in EA is straightforward and its performance is extremely good since most of computational time is used by flow computations. The design result indicates that the present EA successfully minimizes both the induced drag and the volume wave drag in the given design space.

[4] Akira Oyama, Shigeru Obayashi, Kazuhiro Nakahashi, and Naoki Hirose, “Coding by Taguchi Method for Evolutionary Algorithms Applied to Aerodynamic Optimization,” Proceedings of the Fourth ECCOMAS Computational Fluid Dynamics Conference, John Wiley & Sons Ltd, Chichester, the Fourth ECCOMAS Computational Fluid Dynamics Conference, Athens, Greece, September 1998.
A new coding technique using Taguchi method is proposed for Evolutionary Algorithm (EA) applied to an aerodynamic optimization. Taguchi method is used to investigate interactions of design variables and to determine the appropriate coding structure for EA in advance. EA coupled with the new coding technique is then applied to aerodynamic design of a transonic wing. Three-dimensional Navier-Stokes calculation is used for estimation of wing performance.

[5] Shigeru Obayashi, Kazuhiro Nakahashi, Akira Oyama, and Nobuhisa Yoshino, “Design Optimization of Supersonic Wings Using Evolutionary Algorithms,” Proceedings of the Fourth ECCOMAS Computational Fluid Dynamics Conference, John Wiley & Sons Ltd, Chichester, the Fourth ECCOMAS Computational Fluid Dynamics Conference, Athens, Greece, September 1998.
Feasibility of evolutionary computations for supersonic wing design optimization was demonstrated by the single-objective aerodynamic optimization and multiobjective, multidisciplinary optimization. The aerodynamic optimization problem seeks an optimal supersonic wing shape using the Euler equations. The multidisciplinary optimization problem seeks an optimal supersonic wing planform shape using linearized aerodynamics and wing weight algebraic estimation.

[6] Akira Oyama, Shigeru Obayashi, and Kazuhiro Nakahashi, “Encoding Wing Design Parameters for Evolutionary Optimization,” the 36th Aircraft Symposium, International Session, Yokohama, Japan, Proceedings of Aircraft Symposium, pp. 757-760, October 1998.
A new coding technique using factorial design is proposed for Evolutionary Algorithm(EA) applied to an aerodynamic optimization. Coding structure for EA is determined by the epistasis analysis using the factorial design in advance. The present epistasis analysis is applied to aerodynamic design of a transonic wing. The resulting EA succeeded in finding a good compromised design.

[7] Akira Oyama, Shigeru Obayashi, Kazuhiro Nakahashi, and Naoki Hirose “Fractional Factorial Design of Genetic Coding for Aerodynamic Optimization,” AIAA Paper 99-3298, AIAA 14th Computational Fluid Dynamics Conference, Norfolk, Virginia, June 28 - July 1, 1999.
Evolutionary Algorithms (EAs) based on structured coding have been proposed for aerodynamic optimization of wing design. Fractional factorial design is used to investigate interactions of the design variables to determine the appropriate coding structure for EAs in advance. To improve efficiency and accuracy of this approach, parameterization techniques of airfoil shapes are first tested through reproduction of a NASA supercritical airfoil. Their performance is also examined by performing aerodynamic design optimization coupled with a two-dimensional Navier-Stokes code. Finally, three-dimensional wing design is optimized based on a potential flow code and the design result is presented.

[8] Akira Oyama, Shigeru Obayashi, and Kazuhiro Nakahashi, “Wing Design Using Real-Coded Adaptive Range Genetic Algorithm,” Proceedings of 1999 IEEE International Conference on Systems, Man, and Cybernetics, 1999 IEEE International Conference on Systems, Man, and Cybernetics, Tokyo, Japan, October 1999.(2)
Real-coded Adaptive Range Genetic Algorithms (ARGAs) have been developed. The real-coded ARGAs posses both advantages of the binary-coded ARGAs and the use of the floating point representation to overcome the problems of having a large search space that requires continuous sampling. First, the efficiency and the robustness of the proposed approach have been demonstrated by using a typical test function. Then the proposed approach has been applied to an aerodynamic airfoil shape optimization problem. The results confirm that the real-coded ARGAs consistently find better solutions than the conventional real-coded GAs do. The design result is considered to be the global optimal and thus ensures the feasibility of the real-coded ARGAs in aerodynamic designs.

[9] Akira Oyama, Shigeru Obayashi, Kazuhiro Nakahashi, and Takashi Nakamura, "Aerodynamic Optimization of Transonic Wing Design Based on Evolutionary Algorithm," Proceedings of Third International Conference on Nonlinear Problems in Aviation and Aerospace Methods and Software, Third International Conference on Nonlinear Problems in Aviation and Aerospace Methods and Software, DAYTONA BEACH, FLORIDA, May 2000
Evolutionary Algorithm (EA) is applied to a practical three-dimensional shape optimization for aerodynamic design of an aircraft wing. Aerodynamic performances of the design candidates are evaluated by using the three-dimensional compressive Navier-Stokes equations. A structural constraint is introduced to avoid an apparent solution of zero thickness wing for low drag in high speeds. To overcome enormous computational time necessary for the optimization, the computation is parallelized on Numerical Wind Tunnel at National Aerospace Laboratory in Japan, a parallel computer with 166 vector-processing elements. The results ensure the capability of the EA in handling large-scale design optimizations.

[10] Akira Oyama, "Multidisciplinary Optimization of Transonic Wing Design Based on Evolutionary Algorithms Coupled with CFD solver, "CD-Rom Proceedings of ECCOMAS 2000, European Congress on Computational Methods in Applied Sciences and Engineering, Barcelona, Spain, September 2000.
Evolutionary Algorithms (EAs) were applied to multidisciplinary transonic wing design optimizations. Aerodynamic performances of the design candidates were evaluated by using the three-dimensional compressive Navier-Stokes equations to guarantee an accurate model of the flow field. The wing structure is modeled on a box-beam to estimate the wing thickness and wing weight. To overcome enormous computational time necessary for the optimization, the computation was parallelized on Numerical Wind Tunnel at NAL in Japan and NEC SX-4 computers at Computer Center of Tohoku University in Japan. First, a single objective wing design optimization was demonstrated by maximizing L/D with a structural constraint using a real-coded Adaptive Range Genetic Algorithm (ARGA). Because the structural constraint imposed a tradeoff between minimizations of the induced drag and the wave drag, the present ARGA found a compromised but reasonable design. Then, a multiobjective wing design optimization is performed by minimizing both drag and weight with a constraint on CL using a Multiobjective Evolutionary Algorithm (MOEA). Due to the tradeoff between minimization of aerodynamic drag and minimization of weight of wing structure, the solution to this problem is not a single point but a set of compromised designs. The present MOEA successfully captured these solutions that revealed the tradeoff information. These results showed that EAs were promising approach to multidisciplinary optimization problems.

[11] Akira Oyama, Shigeru Obayashi, and Takashi Nakamura, "Real-Coded Adaptive Range Genetic Algorithm Applied to Transonic Wing Optimization," Lecture Notes in Computer Science 1917, Parallel Problem Solving from Nature - PPSN VI, Springer, pp. 712-721, Parallel Problem Solving from Nature VI, PPSN VI, Paris, France, 2000.
Real-coded Adaptive Range Genetic Algorithms (ARGAs) have been applied to a practical three-dimensional shape optimization for aerodynamic design of an aircraft wing. The real-coded ARGAs possess both advantages of the binary-coded ARGAs and the floating-point representation to overcome the problems of having a large search space that requires continuous sampling. The results confirm that the real-coded ARGAs consistently find better solutions than the conventional real-coded Genetic Algorithms do.

[12] Shigeru Obayashi, Akira Oyama, and Takashi Nakamura, "Transonic Wing Design Based on Evolutionary Algorithms Coupled with CFD Solver," Third International Symposium on High Performance Computing, Tokyo, Japan, October 2000.

[13] Akira Oyama, and Meng-Sing Liou, "Multiobjective Optimization of Rocket Engine Pumps Using Evolutionary Algorithm," CD-ROM Proceedings of AIAA CFD Conference, AIAA-2001-2581, 15th AIAA Computational Fluid Dynamics Conference, Anaheim, California, June 11-14, 2001.
Design optimization method for turbopumps of cryogenic rocket engines has been developed. Multiobjective Evolutionary Algorithm is used for multiobjective pump design optimizations. Performances of design candidates are evaluated by using the meanline pump flow modeling method based on the meanline pump flow modeling method based on the Euler turbine equation coupled with empirical correlations for rotor efficiency.
To demonstrate the feasibility of the present approach, single stage centrifugal pump design and multistage pump design optimizations are presented. In both cases, present method obtains very reasonable Pareto-optimal solutions that include some designs outperforming the original design in total head as well as input power by 1%. Detailed observation of the design results also reveals some important design policies in turbopump design of cryogenic rocket engines. These results ensure the feasibility of EA-based design optimization method in this field.

[14] Akira Oyama, and Meng-Sing Liou, "Multiobjective Optimization of a Multi-Stage Compressor Using Evolutionary Algorithm," AIAA-2002-3535, 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Indianapolis, Indiana, July 7-10, 2002.
A multiobjective design optimization tool for multistage compressors has been developed. Multiobjective Evolutionary Algorithm is used to handle multiobjective design optimization problems. Performances of compressors are evaluated by using the axisymmetric through-flow code UD0300M that employs the streamline curvature method. To demonstrate feasibility of the present method, a multiobjective optimization of a four-stage compressor design was performed for maximization of the overall isentropic efficiency and the total pressure ratio. Total pressure and solidities at the rotor trailing edges, and flow angles and solidities at the stator trailing edges are considered as design parameters. The present method obtained hundreds of reasonable and uniformly distributed Pareto-optimal solutions that outperformed the baseline design in both objectives. Detailed observation of the Pareto-optimal designs revealed some design criteria for multi-stage compressor designs.

[15]Akira Oyama, Meng-Sing Liou, and Shigeru Obayashi, "Transonic Axial-Flow Blade Shape Optimization Using Evolutionary Algorithm and Three-Dimensional Navier-Stoke Solver," AIAA-2002-5642, 9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, Atlanta, Georgia, September 4-6, 2002.
A reliable and efficient aerodynamic design optimization tool using evolutionary algorithm has been developed for transonic compressor blades. A real-coded adaptive-range genetic algorithm is used to improve efficiency and robustness in design optimization. To represent flow fields accurately and produce reliable designs, three-dimensional Navier-Stokes computation is used for aerodynamic analysis.
To ensure feasibility of the present method, aerodynamic redesign of NASA rotor67 is demonstrated. Entropy production is considered as the objective function to be minimized. The computation is parallelized on the SGI ORIGIN2000 cluster at Institute of Fluid Science, Tohoku University, by distributing flow analyses of design candidates to 64 processing elements. The present method successfully obtained a design that reduced entropy production by more than 19% compared with the rotor67 while satisfying constraints on the mass flow rate and the pressure ratio. The use of the present tool for turbomachinery blade design is demonstrated to allow designers to achieve higher aerodynamic efficiency, while shortening design cycle and reducing design costs significantly.

[16] Akira Oyama, Meng-Sing Liou, and Shigeru Obayashi, "High-Fidelity Swept and Leaned Rotor Blade Design Optimization Using Evolutionary Algorithm," AIAA-2003-4091, 16th AIAA Computational Fluid Dynamics Conference, Orlando, Florida, June 23-26, 2003.
In this paper, aerodynamic blade design optimization for a transonic axial compressor has demonstrated by using an evolutionary-algorithm-based high-fidelity design optimization tool. The present method uses a three-dimensional Navier-Stokes solver named TRAF3D for aerodynamic analysis to represent flow fields accurately and the real-coded ARGA for efficient and robust design optimization. The present method successfully obtained a design that reduced entropy production by more than 16% compared with the rotor67 while satisfying constraints on the mass flow rate and the pressure ratio. This study gave some insights into design optimization of a swept and leaned rotor blade for transonic axial compressors.

[17] Akira Oyama, and Meng-Sing Liou, "A Multi-Stage Compressor Design Optimization Using CFD," The 8th Japan-Russia Joint Symposium on Computational Fluid Dynamics, September 25, 2003.
A new constraint-handling method based on Pareto-optimality concept for multiobjective multi-constraint design optimization problems has been proposed. The proposed method does not need any constants to be tuned for constraint handling. In addition, the present method does not use weighted-sum of constraints and thus does not need tuning of weight coefficients and is efficient even when the amount of violation of each constraint is significantly different. The proposed approach is demonstrated to be remarkably robust than the dynamic penalty approach and other dominance-based approaches through the optimal design of a welded beam and conceptual design optimization of a two-stage-to-orbit space plane.

[18] Yong-Sheng Lian, Meng-Sing Liou, and Akira Oyama, "An Enhanced Evolutionary Algorithm with a Surrogate Model," The 2004 Genetic and Evolutionary Computation Conference, Bird-of-a-feather Workshop on Application of Hybrid Evolutionary Algorithms to Complex Optimization Problems, Seattle, Washington, June 26-30, 2004.
In this paper we present an enhanced evolutionary algorithm (EA) to solve computationally expensive design optimization problems. In this algorithm we integrate a genetic algorithm (GA) with a local search method to expedite convergence of the GA. We first use a GA to generate a population of data by evaluating real functions, then we construct computationally cheap surrogate models based on the available data. Thereafter, we perform gradient-based local searches on the surrogate models in lieu of the real functions. We apply the GA and gradient-based method alternatively until an optimum is reached. To guarantee convergence to the original problem, we use a trust region management to handle surrogate models. We investigate the number of points used to construct the surrogate model, number of surrogate model constructed, and number of local search performed. Our numerical results, based on two single-objective problems and one multi-objective optimization problem, demonstrate the advantages of the hybrid GA over pure GAs.

[19] Akira Oyama, and Kozo Fujii, "Airfoil Design Optimization for Airplane for Mars Exploration," J-55, The 3rd China-Japan-Korea Joint Symposium on Optimization of Structural and Mechanical Systems, CJK-OSM3, Kanazawa, Ishikawa, October 30- November 2, 2004.
Aerodynamic design optimization of an airfoil for the Mars exploration airplane has been demonstrated by using an evolutionary algorithm. The adaptive range genetic algorithm is used for efficient and robust design optimization. Two-dimensional Navier-Stokes solver is used for accurate aerodynamic performance evaluation. The present computation is parallelized on the SX-6 vector computers in Institute of Space and Aeronautical Science (ISAS) / Japan Aerospace Exploration Agency (JAXA). The optimized airfoil achieved very high aerodynamic performance. The optimum airfoil for Mars exploration airfoil has extremely thin airfoil thickness and strong camber while an optimum airfoil for typical airplane fly on Earth has substantial airfoil thickness in the front. However, a thin airfoil has disadvantages such as structural weight and fuel tank space (if an engine is used for propulsion). The present optimization indicates necessity of multiobjective design optimization for practical airfoil design for Mars exploration airplane.

[20] Nobuyoshi Fujimatsu, Yoshiaki Tamura, Akira Oyama and Kozo Fujii, "Software for Molecular-sensing Application-oriented Postprocessing," Proceedings of International Workshop on Molecular Imaging for Interdisciplinary Research, Sendai, Japan, November 8-9, 2004, pp.94-95.


[21] Hirofumi Ouchi, Masato Ito, Akira Oyama and Kozo Fujii, Application of Ru(U)-Complex- Based PSP Measurement To Engineering Problems, Proceedings of International Workshop on Molecular Imaging for Interdisciplinary Research, Sendai, Japan, November 8-9, 2004.


[22] Akira Oyama, Kozo Fujii, Koji Shimoyama, and Meng-Sing Liou, "Pareto-Optimality-Based Constraint-Handling Technique and Its Application to Compressor Design," AIAA2005-4983, the 17th AIAA Computational Fluid Dynamics Conference, Toronto, Ontario, June 6-9, 2005.
A new constraint-handling technique based on Pareto-optimality concept is proposed for evolutionary algorithms to efficiently deal with multiobjective multi-constraint design optimization problems. The essence of the proposed method is to apply non-dominance concept based on constraint function values to infeasible designs and to apply non-dominance concept based on objective function values to feasible designs. The proposed technique does not need any constants to be tuned as the proposed technique does not use weighted-sum of constraints. First, the proposed approach is demonstrated to be remarkably more robust than traditional constraint-handling techniques through the optimal design of a welded beam and conceptual design optimization of a two-stage-to-orbit space plane. Next, high-fidelity aerodynamic design optimization of an axial compressor blade design is demonstrated.

[23] Kozo Fujii, Akira Oyama, Nobuyuki Tsuboi, Motoo, Tsukada, Humihiro Ouchi, Masato Ito, and Koichi Hayashi, "Flow Field Analysis of Under-Expanded Supersonic Jets Impinging on an Inclined Flat Plate - Analysis with PSP/Schlieren Images and CFD Simulations", Proceedings of 2005 ASME Fluids Engineering Division Summer Meeting and Exhibition, pp. 683-691, 2005 ASME Fluids Engineering Division Summer Meeting and Exhibition, FEDSM2005, Houston, Texas, June 19-23, 2005. (3)
Flow 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.

[24] Koji Shimoyama, Akira Oyama, and Kozo Fujii, "A New Efficient and Useful Robust Optimization Approach -Design for Multi-Objective Six Sigma," 2005 IEEE Congress on Evolutionary Computation Proceedings, 1, pp. 950-957, 2005 IEEE Congress on Evolutionary Computation, 2005 IEEE CEC, Edinburgh, United Kingdom, September 2-5, 2005. (5)
An 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.

[25] Akira Oyama, Koji Shimoyama, and Kozo Fujii, "New Constraint-Handling Method for Multi-Objective Multi-Constraint Evolutionary Optimization and Its Application to Space Plane Design," CD-ROM Proceedings of EUROGEN 2005, Evolutionary and Deterministic Methods for Design, Optimization and Control with Applications to Industrial and Societal Problems, EUROGEN 2005, Munich, Germany, 12-14 September 2005.
A new constraint-handling method based on Pareto-optimality concept for multiobjective multi-constraint design optimization problems has been proposed. The proposed method does not need any constants to be tuned for constraint handling. In addition, the present method does not use weighted-sum of constraints and thus does not need tuning of weight coefficients and is efficient even when the amount of violation of each constraint is significantly different. The proposed approach is demonstrated to be remarkably robust than the dynamic penalty approach and other dominance-based approaches through the optimal design of a welded beam and conceptual design optimization of a two-stage-to-orbit space plane.

[26] Akira Oyama, and Kozo Fujii, "A Study on Airfoil Design for Future Mars Airplane," AIAA-2006-1484, 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, January 9-12, 2006.
An optimum airfoil design for future Mars airplane for Mars exploration is obtained by evolutionary computation coupled with a two-dimensional Reynolds-averaged Navier-Stokes solver. The optimized airfoil design is also compared with other airfoil designs optimized at different Reynolds number or at different Mach number to discuss Reynolds number and Mach number effects on airfoil design. These results indicate same important design policies in airfoil design optimization in regard to Reynolds number and Mach number effects.

[27] Masato Ito, Akira Oyama, Kozo Fujii, and Koichi Hayashi, "Flow Field Analysis of Jet Impinging on an Inclined Flat Plate at High Plate Angles", AIAA-2006-1047, 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, January 9-12, 2006.
Flow 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/Ls’ 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.

[28] Genta Imai, Kozo Fujii, and Akira Oyama, "Computational Analyses of Supersonic Flows Over a Delta Wing at High Angles of Attack," 2.5S, the 25th International Congress of the Aeronautical Sciences, ICAS 2006, Hamburg, Germany, September 3-8, 2006.
Supersonic flows over a 65-degrees sweep delta wing with a sharp leading edge at high angles of attack are computationally studied.  Computational simulations with various free-stream Mach numbers show that there is a sudden change in flow fields between the free-stream Mach number of 0.8 and 1.2. Visualized images of the simulation results at different flow conditions show that this nonlinear behavior occurs as expansion waves from the leading edge accelerate the flow and shift the share layer closer to the surface when the Mach number at the leading edge becomes supersonic. The results also show that aerodynamic characteristics have a different trend below and above the free-stream Mach number of 1.0. The sudden change occurs not at the boundary of the classification proposed by the former studies. When the free-stream Mach number becomes supersonic, components of the three-dimensional flow structure such as primary vortex, vortex breakdown and windward flow have different nature, which lead to the nonlinear behavior of aerodynamic characteristics.

[29] Koji Shimoyama, Akira Oyama, and Kozo Fujii, "Robust Aerodynamic Airfoil Design Optimization against Wind Variations for Mars Exploratory Airplane," IAC-06-A3.P.3.07, the 57th International Astronautical Congress, IAC 2006, Valencia, Spain, October 2-6, 2006.
Robust aerodynamic airfoil design optimizations of Mars exploratory airplane against wind variations have been carried out by using DFMOSS coupled with the CFD simulation. The present robust optimization successfully found the airfoil designs with robust aerodynamic performances against wind variations. Obtained airfoil design information about the optimality and the robustness of aerodynamic performances indicated that an airfoil with smaller camber can improve the robustness in lift to drag ratio against the variation of flight Mach number, and an airfoil with larger curvature near the shock wave location can improve the robustness in pitching moment against the variation of flight Mach number.

[30] Koji Shimoyama, Akira Oyama, and Kozo Fujii, "Multi-Objective Optimization for Robust Airfoil Design Considering Design Errors and Uncertainties," Proceedings of the 3rd International Conference on Flow Dynamics, pp. 237-238, The 3rd International Conference on Flow Dynamics, ICFD 2006, Matsushima, Japan, November 7-9, 2006.

[31] Koji Shimoyama, Akira Oyama, and Kozo Fujii, "Multi-Objective Six Sigma Approach Applied to Robust Airfoil Design for Mars Airplane," 9th AIAA Non-Deterministic Approaches Conference, Honolulu, Hawaii, AIAA-2007-1966, 23-26 April, 2007.
A new optimization approach for robust design, design for multi-objective six sigma (DFMOSS) has been developed and applied to robust aerodynamic airfoil design for Mars exploratory airplane. The present robust aerodynamic airfoil design optimization using DFMOSS successfully showed the trade-off information between maximization and robustness improvement in aerodynamic performance by a single optimization run without careful input parameter tuning. The obtained trade-off information indicated that an airfoil with a smaller maximum camber improves robustness of lift to drag ratio, and that with a larger curvature near the shock wave location improves robustness of pitching moment against the variation of flight Mach number.

[32] Akira Oyama, Yoshiyuki Okabe, Kozo Fujii, and Koji Shimoyama, "A Study on Flapping Motion for MAV Design Using Design Exploration," AIAA Infotech@Aerospace 2007 Conference and Exhibit, Rohnert Park, California,  AIAA-2007-2878,  May 7-10, 2007
Aerodynamic knowledge for practical flapping-wing micro air vehicle (MAV) design is obtained by application of the design exploration framework coupled with CFD to a multiobjective aerodynamic design optimization problem of two-dimensional flapping motion of an airfoil. Lift and thrust are maximized while required power is minimized in the design problem.  Pareto-optimal solutions are obtained by a multiobjective evolutionary optimization and analyzed with the self-organizing map.  Aerodynamic performance of each flapping motion is evaluated by a two-dimensional Navier-Stokes solver.  The result reveals tradeoff information between each objective and effect of each design parameters on them.  Analysis of the time histories of lift, thrust, and required power coefficients and corresponding pressure coefficient distribution of the extreme Pareto-optimal solutions leads to useful guidelines for the lift maximization, thrust maximization, and required power minimization.

[33] Akira Oyama, Masato Ito, Genta Imai, Seiji Tsutsumi, Nobuo Amitani, and Kojo Fujii, "Mach Number Effect on Flowfield over a Delta Wing in Supersonic Region," 46th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, AIAA-2008-0354, January 7-10, 2008.
To understand Mach number effect on flow field over a delta wing with blunt leading edge in supersonic and high angle of attack region, wind tunnel experiments of a 65° delta wing are performed in supersonic and high angle of attack flow conditions at the JAXA’s transonic / supersonic wind tunnel.  Oil flow for surface flow visualization, pressure sensitive paint for surface pressure distribution measurement, and Schlieren images for shock wave visualization are used.  The present results indicate that a delta wing with blunt leading edge can be mixed flow of two different types of flow structure in supersonic and high angle of attack flow region and the location of the boundary of the two types of flow moves toward the apex of the wing as the free-stream Mach number increases.

[34] Akira Oyama, Genta Imai, Akira Ogawa, and Kozo Fujii, "Aerodynamic Characteristics of a Delta Wing at High Angles of Attack," 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Dayton, Ohio, AIAA-2008-2563, April 28 - May 1, 2008.

[35]Naoki Tani, Akira Oyama, and Nobuhiro Yamanishi, "Multi Objective Design Optimization of Rocket Engine Turbopump Turbine," 5th International Spacecraft Propulsion Conference / 2nd International Symposium on Propulsion for Space Transportation, Crete, Greece, May 5-8, 2008.
JAXA is now planning to develop a next generation booster engine named LE-X, which is a successor of LE-7A. From an engine cycle study, the LE-X requires a high efficiency turbine. To achieve this requirement, a feasibility study of multi-objective design optimization with generic algorithm was applied to the turbine blade shape. The optimized results show strong tradeoff between axial-horsepower and entropy-rise within the stage. By use of Self-Organizing MAP (SOM) and correlation function, it is revealed that this tradeoff is primarily derived from outlet blade design, and inlet blade shape also has an influence to axial-horsepower improvement.

[36]Tomoaki Tatsukawa, Akira Oyama, and Kozo Fujii, "Comparative Study of Data Mining Methods for Aerodynamic Multiobjective Optimizations," 8th World Congress on Computational Mechanics (WCCM8) / 5th European Congress on Computational Methods in Applied Sciences and Engineering (ECCOMAS2008), Venice, Italy, June 30 - July 5, 2008.

[37] Roel Muller, Akira Oyama, Kozo Fujii, and Harry Hoeijmakers, "Propulsion by an Oscillating Thin Airfoil at Low Reynolds Number," The Fifth International Conference on Computational Fluid Dynamics, Seoul, Korea, July 7-11, 2008.
This paper describes an investigation of the mechanisms producing thrust for an airfoil performing a pitching or heaving motion in a low Reynolds-number flow (Re=1000, based on chord length) by analysis of numerically obtained flow fields and forces on the airfoil.

[38] Naoki Tani, Akira Oyama, Koichi Okita, and Nobuhiro Yamanishi, "Feasibility Study of Multi Objective Shape Optimization for Rocket Engine Turbopump Blade Design," AIAA-2008-4659, 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Hartford, CT, July 14-16, 2008.
JAXA is now planning to develop a next generation booster engine named LE-X, which is a successor of LE-7A. From an engine cycle study, the LE-X requires a relatively high efficiency turbopump. To achieve this requirement, a feasibility study of design optimization with generic algorithm was applied to the impeller and turbine blade shape. As the first step, single objective optimization was carried out on the impeller blade design, and the second one was a multi objective optimization on the turbine blade shape. It was concerned that optimization may not be effective in such a highly loaded component, however, each of the optimized result have shown improvement on performance. Especially, multi objective optimization can show tradeoff information for several important parameters, therefore, it can be said that such method is quite useful for the improvement or the developing of high efficiency turbopumps.

[39] Keiichiro Fujimoto, Akira Oyama, Kozo Fujii, Nobuyuki Iizuka, and Koichi Okita, "Visualization and Verification Method for Failure Network Analysis of Space Launch Vehicles," DETC2008-49656, Proceedings of IDETC/CIE 2008, New York, New York, August 3-6, 2008.
Comprehensive 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.


[40] Kengo Asada, Yoshihiko Ninomiya, Akira Oyama, and Kozo Fujii, "Airfoil Flow Experiment on the Duty Cycle of DBD Plasma Actuator," AIAA-2009-0531, 47th AIAA Aerospace Sciences Meeting, Orlando, Florida, January 5-8, 2009.

[41] Akira Oyama, Taku Nonomura, and Kozo Fujii, "Data Mining of Pareto-Optimal Transonic Airfoil Shapes Using Proper Orthogonal Decomposition," AIAA-2009-4000, 19th AIAA Computational Fluid Dynamics, San Antonio, Texas, June 22-25, 2009.
A new approach to extract useful design information from Pareto-optimal solutions of optimization problems is proposed and applied to an aerodynamic transonic airfoil shape optimization. The proposed approach enables an analysis of line, face, or volume data of all Pareto-optimal solutions such as shape and flow field by decomposing the data into principal modes and corresponding base vectors using proper orthogonal decomposition (POD). Analysis of the shape and surface pressure data of the Pareto-optimal solutions of an aerodynamic transonic airfoil shape optimization problem showed that the optimized airfoils can be categorized into two families (low drag designs and high lift designs), where the lift is increased by changing the camber near the trailing edge among the low drag designs while the lift is increased by moving the lower surface upward among the high lift designs.

[42] Akira Oyama, Taku Nonomura, and Kozo Fujii, "Data Mining of Non-Dominated Solutions Using Proper Orthogonal Decomposition," Proceedings of the 11th Annual Conference on Genetic and Evolutionary Computation, pp. 1935-1936, Association for Computing Machinery, New York, NY, USA, 2009.
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.

[43]Takashi Kubota, Naoko Ogawa, Tatsuaki Okada, Hideaki Miyamoto, Mutsuko Yano Morimoto, Kazuhisa Fujita, Tetsuya Yamada, Takahide Mizuno, Yasuhiro Kawakatsu, Akira Oyama, Takehiko Satoh, Jun'ichiro Kawaguchi, "Preliminary Study on Lander System and Scientific Investigation for Next Mars Exploration," ISTS2009-K-21, 27th International Symposium on Space Technology and Science (ISTS 2009), Tsukuba, Japan, July 5-12, 2009.
This paper presents Japanese Mars exploration plan. Firstly the outline of Mars exploration plan, scientific objectives and technological challenges.This paper presents Mars robotics exploration by landers in detail. This paper describes the system design of landers and science investigation. This paper also presents the technical challenges, especially accurate navigation and guidance, reliable landing scheme with obstacle avoidance, surface exploration technology.

[44] Akira Oyama, Paul C. Verburg, Taku Nonomura, Harry W. M. Hoeijmakers, and Kozo Fujii, "Flow Field Data Mining of Pareto-Optimal Airfoils Using Proper Orthogonal Decomposition," AIAA-2010-1140, 48th AIAA Aerospace Sciences Meeting, Orlando, Florida, January 4-7, 2010.
Capability of proper-orthogonal-decomposition-based data mining approach for analysis of flow field data of the Pareto-optimal solutions is demonstrated. This method enables a designer to extract design knowledge by examining baseline data and a limited number of eigenvectors and orthogonal base vectors. The flow data analyzed here are pressure field data of the Pareto-optimal solutions of an aerodynamic transonic airfoil shape optimization problem. The present result shows that the proper-orthogonal-decomposition-based data mining approach is a useful approach for extracting design knowledge from flow field data of the Pareto-optimal solutions.

[45] Weipeng Li, Taku Nonomura, Akira Oyama, and Kozo Fujii, "LES Study of Feedback-loop Mechanism of Supersonic Open Cavity Flows," AIAA-2010-5112, 40th Fluid Dynamics Conference and Exhibit, Chicago, Illinois, June 28-1, 2010.
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.

[46] Yoshinori Namera, Ryoji Takaki, Akira Oyama, Kozo Fujii, and Makoto Yamamoto, "Aerodynamic Shape Design of the Vertical Landing Rocket Vehicle," AIAA-2010-4367, 28th AIAA Applied Aerodynamics Conference, Chicago, Illinois, June 28-1, 2010
Aerodynamic characteristics of a vertical landing rocket vehicle are computationally investigated under subsonic and supersonic flight conditions as a preliminary study for the concept design using a light optimization method and a light CFD tool. The results show that the simulations with a coarse grid can accurately estimate the aerodynamic characteristics like axial force coefficient and the lift-to-drag ratio. The results of the light aerodynamic shape optimization indicate tradeoff information among objective functions, and the correlation between design variables and objective functions. The preliminary knowledge for the aerodynamic shape design is obtained.

[47] Yuki Yamazaki, Akira Oyama, Taku Nonomura, Kozo Fujii, and Makoto Yamamoto, "Aerodynamic multiobjective design exploration of flapping wing using a Navier-Stokes solver," International Conference on Computational Fluid Dynamics, St. Petersburg, Russia, July 12-16, 2010.
An aerodynamic design optimization problem of a three-dimensional flapping wing is explored with the multiobjective design exploration framework coupled with a Navier-Stokes solver. The results show that there is a tradeoff among lift maximization, thrust maximization, and required power minimization. The results also show that strong vortex is generated in both down stroke and up stroke motions for thrust maximization while strong vortex is generated only in down stroke motion for lift maximization. This study also reveals effects of the design parameters on the design objectives, for example, pitch offset has positive linear relationship to the lift.

[48] Ryoji Kojima, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Large Eddy Simulation of the Flow over a Thin Airfoil at Low Reynolds Number," International Conference on Computational Fluid Dynamics, St. Petersburg, Russia, July 12-16, 2010.
The performance of airfoil NAXA0002 at Reynolds number of 2.3x104 is investigated with large-eddy simulation. The angle of attack is 3, 6, or 9 degrees. The behavior of a laminar separation bubble which appears over a thin airfoil and its effects on aerodynamic characteristics are mainly discussed.

[49] Koichi Okada, Kozo Fujii, Koji Miyaji, Akira Oyama, Kengo Asada, and Taku Nonomura, "Computational Study of the Synthetic Jet on Separated Flow over a Backward-Facing Step," IMECE2010-38767, ASME International Mechanical Engineering Congress & Exposition, Vancouver, British Columbia, Canada, November 12-18, 2010.

[50] Yukihiro Kosugi, Akira Oyama, Kozo Fujii, Masahiro Kanazaki, "Multidisciplinary and Multi-objective Design Exploration Methodology for Conceptual Design of a Hybrid Rocket", ,Infotech@Aerospace 2011, St. Louis, Missouri, March 2011.


[51] Seiya Ugajin, Akira Oyama, Taku Nonomura, Masaya Suzuki, Makoto Yamamoto, and Kozo Fujii, "Aerodymamic Design Exploration of flapping motion for development of Mars Aircraft," CFD & Optimization, Antalya, Turkey, May 23-25, 2011.

[52] Tomoaki Tatsukawa, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Aerodynamic Design Exploration for Reusable Launch Vehicle Using Genetic Algorithm with Navier-Stokes Solver," The 28th International Symposium on Space Technology and Science, Ginowan, Japan, June 5-12, 2011.

[53] Taro Shimizu, Dan Hori, Keiichi Kitamura, Yu Daimon, and Akira Oyama, "Slit Resonator Design and Damping Estimation in Linear and Non-linear Ranges," AIAA-2001-3261, 41st AIAA Fluid Dynamics Conference and Exhibit, Honolulu, Hawaii, June 27-30, 2011.

[54] Satoshi Sekimoto, Kengo Asada, Tatsuya Usami, Shinichiro Ito, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Experimental Study of Effects of Frequency for Burst Wave on DBD Plasma Actuator for Separation Control," AIAA-2011-3989, 41st AIAA Fluid Dynamics Conference and Exhibit, Honolulu, Hawaii, June 27-30, 2011.

[55] Akira Oyama, "Airplanes for Mars Exploration," 21st Workshop on Astrodynamics and Flight Mechanics, Sagamihara, Kanagawa, July 25-26, 2011.

[56] Akira Oyama, "Multiobjective Design Exploration of Airplane for Mars Exploration," 21st Workshop on Astrodynamics and Flight Mechanics, Sagamihara, Kanagawa, July 25-26, 2011.

[57] Taku Nonomura, Satoshi Sekimoto, Kengo Asada, Akira Oyama, and Kozo Fujii, "Experimental Study of Blowing Direction Effects of DBD Plasma Actuator on Separation Control of Flow Around an Airfoil," ASME-JSME-KSME Joint Fluids Engineering Conference 2011, AJK2011-15010, Hamamatsu, Japan, July 24-29, 2011.

[58] Ryoji Kojima, Donghi Lee, Tomoaki Tatsukawa, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Three-Dimensional Wing Design Towards the Future Mars Airplane," ASME-JSME-KSME Joint Fluids Engineering Conference 2011, AJK2011-15013, Hamamatsu, Japan, July 24-29, 2011.

[59] Ryoji Kojima, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Computational Study of Flow Characteristics of Thick and Thin Airfoil with Implicit Large-eddy Simulation at Low Reynolds Number," ASME-JSME-KSME Joint Fluids Engineering Conference 2011, AJK2011-15026, Hamamatsu, Japan, July 24-29, 2011.

[60] Akira Oyama, Yasuhiro Kawakatsu, and Kazuko Hagiwara, "Application of Multiobjective DEsign Exploration to Solar-C orbit Design," AAS 11-616, the 2011 AAS/AIAA Astrodynamics Specialist Conference, Girdwood, Alaska, July 31- August 4, 2011.

[61] Tomoaki Tatsukawa, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Aerodynamic Design Exploration for Reusable Launch Vehicle Using Multi-Objective Genetic Programming," ASME 2011 International Design Engineering Technical Conferences & Computers and Information in Engineering Conference, Washington, DC, August 28-31, 2011.

[62] Masayuki Anyoji, Taku Nonomura, Akira Oyama, Kozo Fujii, Kei Nose, Daiju Numata, Hiroki Nagai, and Keisuke Asai, "Aerodynamic Characteristics of Ishii Airfoil at Low Reynolds Numbers," Eighth International Conference on Flow Dynamics, Sendai, Japan, November 9-11, 2011.

[63] Naoya Kowatari, Akira Oyama, Hernan Aguirre, and Kiyoshi Tanaka, "A study on Large Population MOEA Using Adaptive Epsilon-Box Dominance and Neighborhood Recombination for Many-Objecitve Optimization, Learning and Intelligent Optimization Conference (LION) 6, Paris France, January 16-20, 2012.

[64] Akira Oyama, "Problem Understanding with Data Mining of Pareto-Optimal Designs in Space Engineering," Dagstuhl Seminar 12041 Learning in Multiobjective Optimization, January 23-27, 2012.

[65] Dan Hori, Taro Shimizu, Keiichi Kitamura, Kazuto Kuzuu, and Akira Oyama, “Slit Resonator Damping Estimation and Proposal of a New Geometry,” 18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference), AIAA-2012-2095, 2012.

[66] Tomoaki Tatsukawa, Akira Oyama, and Kozo Fujii, “Extraction of Design Information from Pareto-Optimal Solutions Using Genetic Programming: A First Report,” International Workshop on Future of CFD and Aerospace Sciences, Kobe, Japan, May 23-25, 2012.

[67] Akira Oyama, Yasuhiro Kawakatsu, and Kazuko Hagiwara, “Data Mining of Pareto-Optimal Solutions of a Solar- Observatory Trajectory Design Problem,” Infotech@Aerospace 2012, AIAA-2012-2442 , Orange County, California, June 19-21, 2012.

[68] Naoya Kowatari, Akira Oyama, Hernan Aguirre, and Kiyoshi Tanaka, “Analysis on Population Size and Neighberhood Recombination on Many-Objective Optimization,” 12th International Conference on Parallel Problem Solving from Nature, S7.8, Taormina, Italy, Sep. 1-5, 2012.

[69] Masaki Nakamiya, Satoru Kitani, Akira Oyama, and Yasuhiro Kawakatsu, “Preliminary Study of the Trajectory from the Earth to the Moon with Low Thrust for the Small Scientific Spacecraft, DESTINY,” 63rd International Astronautical Congress, IAC-12.C1.4.4, Naples, Italy, Oct. 1-5, 2012.

[70] Gaku Sasaki, Tomoaki Tatsukawa, Taku Nonomura, Koichi Yonemoto, Akira Oyama, Takaaki Matsumono, and Tomohiro Narumi, “Multi-Objective Numerical Exploration of Airfoil Design for Mars Aircraft,” 5th Symposium on Integrating CFD and Experiments in Aerodynamics, Tokyo, Japan, Oct. 3-5, 2012.

[71] Masaki Nakamiya, Akira Oyama, Mai Bando, Chikako Hirose, Stefano Campangnola, Yasuhiro Kawakatsu, “Trajectory Design from the Earth to the Moon Using the Multi-Objective Optimization for DESTINY Mission,” 23rd International Symposium on Space Flight Dynamics, Pasadena, California, Oct. 29-Nov. 2, 2012.

[72] Gaku Sasaki, Tomoaki Tatsukawa, Taku Nonomura, Koichi Yonemoto, Akira Oyama, and Takaaki Matsumono, “Multi-Objective Optimization of Airfoil in Low Reynolds Number Using Genetic Algorithm,” 2012 Asia-Pacific International Symposium on Aerospace Technology, Jeju, Korea, Nov. 13-15, 2012.

[73] Antonio L ópez, Carlos A. Coello Coello, Akira Oyama, and Kozo Fujii, “An Alternative Preference Relation to Deal with Many-Objective Optimization Problems,” 7th International Conference on Evolutionary Multi-Criterion Optimization, Sheffield, UK, Mar. 19-22, 2013.

[74] Hern án Aguirre, Akira Oyama, and Kiyoshi Tanaka, “Adaptive ε-Sampling and ε-Hood for Evolutionary Many-Objective Optimization,” 7th International Conference on Evolutionary Multi-Criterion Optimization, Sheffield, UK, Mar. 19-22, 2013.

[75] Tomoaki Tatsukawa, Taku Nonomura, Akira Oyama, and Kozo Fujii, “A New Multiobjective Genetic Programming for Extraction of Design Information from Non-Dominated Solutions ,” 7th International Conference on Evolutionary Multi-Criterion Optimization, Sheffield, UK, Mar. 19-22, 2013.

[76] Kazuhisa Fujita, Genya Ishigami, Naoko Ogawa, Akira Oyama, Kazuhiko Yamada, Takashi Kubota, Hirdy Miyamoto, and Takehiko Satoh, "Preliminary Design Study of EDL System for Japan's Mars Rover Mission," 4th INTERNATIONAL ARA DAYS, Arcachon, France, May 27-29, 2013.

[77] Naoya Fujioka, Taku Nonomura, Akira Oyama, Makoto Yamamoto, and Kozo Fujii, "Computational Analysis of Aerodynamic Performance of Mars Airplane," 29th International Symposium on Space Technology and Science, Nagoya, Japan, June 2-9, 2013.

[78] Katsutoshi Kondo, Hikaru Aono, Taku Nonomura, Masayuki Anyoji, Akira Oyama, Tianshu Liu, Kozo Fujii, and Makoto Yamamoto, "Analysis of Owl-like Airfoil Aerodynamics at Low Reynods Number Flow," 29th International Symposium on Space Technology and Science, Nagoya, Japan, June 2-9, 2013.

[79] Gaku Sasaki, Kyoshiro Itakura, Tomoaki Tatsukawa, Taku Nonomura, Koichi Yonemoto, Akira Oyama, and Takaaki Matsumoto, "Multi-Objective Optimization of Airfoil for Mars Exploration Aircraft Using Genetic Algorithm," 29th Innternational Symposium on Space Technology and Science, Nagoya, Japan, June 2-9, 2013.

[80] Bikash Ranjan Das, Junya Aono, Taku Nonomura, Kazuto Kuzuu, Akira Oyama, and Kozo Fujii, "Aerodynamic Effects of Fin Layout on Reusable Vehicle Testing during Gliding Phase," 29th Innternational Symposium on Space Technology and Science, Nagoya, Japan, June 2-9, 2013.

[81] Kazuhisa Fujita, Genya Ishigami, Naoko Ogawa, Akira Oyama, Kazuhiko Yamada, Takashi Kubota, Hirdy Miyamoto, Takehiko Satoh, "Design Study of Mars EDL Demonstrator for MELOS Mission," 29th International Symposium on Space Technology and Science, Nagoya, Japan, June 2-9, 2013.

[82] Naoko Ogawa, Kazunori Ogohara, Kazuhisa Fujita, Takashi Kubota, Genya Ishigami, Akira Oyama, Kazuhiko Yamada, Takehiko Satoh, "Case Study of Trajectory Design for Synergetic Mars Exploration by Orbiter and Lander," 29th International Symposium on Space Technology and Science, Nagoya, Japan, June 2-9, 2013.

[83] Katsutoshi Kondo, Hikaru Aono, Taku Nonomura, Akira Oyama, Kozo Fujii, Makoto Yamamoto, "Large-eddy simulation of Owl-like wing under low Reynolds number conditions," FEDSM2013-16377, ASME Fluid Engineering Division Summer Meeting 2013, Incline Village, Nevada, July, 2013.

[84] Taufik Sulaiman, Satoshi Sekimoto, Tomoaki Tatsukawa, Taku Nonomura, Akira Oyama and Kozo Fujii, "DBD Plasma Actuator Multi-Objective Design Otimization at Reynolds Number 63000: Baseline case," FEDSM2013-16325, ASME Fluid Engineering Division Summer Meeting 2013, Incline Village, Nevada, July, 2013.

[85] Naoko Ogawa, et. al., "Preliminary Trajectory Design of MELOS1 Considering Landing Site Candidates," Astrodynamics Conference, 2013.

[86] Hiroki Nagai, Akira Oyama, and Mars Airplane WG, "Mission Scenario of Mars Exploration by Airplane," The 2013 Adsia-Pacific International Symposium on Aerospace Technology, Nov. 20-22, 2013.
[87] Katsutoshi Kondo, Hikaru. Aono, Taku Nonomura , Akira. Oyama, Kozo. Fujii and Makoto Yamamoto, "Computational Study of Reynolds Number Effect on Owl-like Wing Aerodynamics at Low ," 1502, 5th Asia Pacific Congress on Compuattional Mechanics and 4th International Symposium on Computational Mechanics, Singapole, December, 2013.

[88] T. Tatsukawa,Y. Nagata, T. Nonomura, A. Oyama, K. Fujii, and M. Yamamoto, "Multiobjective Design Exploration of an Aero-Acoustic Rocket Launch Site Design Problem with Evolutionary Computation and Large Eddy Simulations," SCITECH 2014, National Harbor, Maryland, 13-17 January, 2014.


[89] Yutaka Nishio, Akira Oyama, Youhei Akimoto, Hernan Aguirre and Kiyoshi Tanaka, "Many-objective Optimization of Trajectory Design for DESTINY Mission," Learning and Intelligent Optimization conference, Gainesville, Florida, USA, Feb 16-21, 2014.

[90] Takeshi Watanabe, Tomoaki Tatsukawa, Antonio Lopez Jaimes, Hikaru Aono, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Many-Objective Evolutionary Computation for Optimization of Separated-Flow Control Using a DBD Plasma Actuator," 2014 IEEE World Congress on Computational Intelligence, July 6-11, Beijing International Convention Center, Beijing, China.

[91] Hernan Aguirre, Yuki Yazawa, Akira Oyama and Kiyoshi Tanaka, "Extending AeSeH from Many-objective to Multi-objective Optimization," Proceedings of Tenth International Conference on Simulated Evolution and Learning, Dunedin, New Zealand, 15-18 December, 2014.

[92] Tomoaki Tatsukawa, Takeshi Watanabe, Akira Oyama, and Kozo Fujii, "Multiobjective Design Exploration of a Many-objective Space Trajectory Problem for Low-Thrust Spacecraft Using MOEA with Large Populations," AIAA SCITECH 2015, Kissimmee, Florida, Jan 5-9, 2015.

[93] Takeshi Watanabe, Hikaru Aono, Tomoaki Tatsukawa, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Design Exploration of a DBD Plasma Actuator for Massive Separation Control," AIAA SCITECH 2015, Kissimmee, Florida, Jan 5-9, 2015.

[94] Mari Nishiyama,, Hisashi Otake, Takeshi Hoshino, Tatsuaki Hashimoto, Takeshi Watanabe, Tomoaki Tatsukawa, Akira Oyama, "Selection of Landing Sites for Future lunar Missions with Multi-Objective Optimization," 46th Lunar and Planetary Science Conference, The Woodlands, Texas, March 16-20, 2015.



国内会議

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[11] 大山聖,Meng-Sing Liou,大林茂,「航空機エンジン圧縮機動翼の空力設計最適化」第17回数値流体力学シンポジウム論文集,2003年12月17-19.
[12] 大山聖,藤井孝藏,「低レイノルズ数翼型の設計最適化」日 本流体力学会 年会,名古屋,日本流体力学会年会論文集,pp. 660-661,F337,2004年8月9-11
[13] 伊 藤匡人, 大内弘文, 藤井孝藏, 大山聖, 佐藤清, 入門朋子, 林光一,ルテニウム錯体系感圧塗料を用いた宇宙往還機模型の力計測,平成16年度宇宙航行の力学シンポジウム,相模原,平成16年度宇宙航行の力学シンポ ジウム講演論文集,pp. 124-127,2004.
[14] 大山聖, 下山幸治,藤井孝藏,「パレー ト概念に基づいた新しい制約条件取り扱い法の開発とTSTO概念設計への適用」,平成16年度「サイレント超音速飛行実現のための実験・計算融合研究」 「レーザー駆動管内加速装置:基礎物理の解明と実用展開」合同シンポジウム, 2005年1月21〜22日.
[15] 大 山 聖,藤松信義,伊藤匡人,藤井孝藏,「感圧・感温塗料圧力計測系のための取得画像後処理ソフトウェアの開発」,第33回可視化情報シンポジウム講演論文 集,pp. 313-316,可視化情報シンポジウム2005年7月.
[16] 伊 藤匡 人,大山聖,藤井孝藏,林光一「感圧・感温塗料を用いた斜め平板衝突噴流の解析」,第33回可視化情報シンポジウム,可視化情報シンポジウム講演論文集, pp. 317-320,2005年7月.
[17] 下山幸治, 大山 聖, 藤井孝藏,高効率かつ利便性に優れたロバスト最適化手法の開発 - 多目的シックスシグマ手法,第15回設計工学・システム部門講演会, 札幌市,北海道大学,1515, 第15回設計工学・システム部門講演会論文集, pp237-240,2005.
[18] 大山聖,藤井孝藏,「火星探 査飛行機翼型の空力設計最適 化」,第83期日本機械学会流体工学部門講演会,第83期日本機械学会流体工学部門講演会論文集,G405,金沢市,2005年10月.
[19] 伊藤匡人, 大山聖, 藤井孝藏,有機ELを用いた感圧塗料圧力計測系による平板衝突噴流の解析,第83期日本機械学会流体工学部門講演会, 日本機械学会流体工学部門講演会講演集, pp. 153-154, GS-C9024, 10月,2005.
[20] 下山幸治, 大山聖,藤井孝藏,飛行Mach数変動に対する性能のロバスト性に着目した火星航空機2次元翼の空力最適化,平成17年度宇宙航行の力学シンポジウム,相 模原市,平成17年度宇宙航行の力学シンポジウム論文集,pp. 53-56,2005.
[21] 網谷修男, 伊藤匡人, 山下加奈, 藤井孝藏, 大山聖, 佐藤清, 入門朋子, 飯田明由,低速流におけるデルタ翼周りの流れ場解析,平成17年度宇宙航行の力学シンポジウム,12月,2005.
[22] 下山幸治, 大山聖, 藤井孝藏,飛行Mach数変動に対する性能のロバスト性に着目した火星航空機2次元翼の空力最適化,平成17年度宇宙航行の力学シンポジウム,12月, 2005.
[23] 藤井孝藏, 大山聖, 高木亮治, 田中義輝,火星飛行機探査実現に向けた空力課題と解決への提案ーその1,平成17年度科研費空力班シンポジウム「デトネーション利用推進機関システムの構 築」,pp. 35-39, 1月,2006.
[24] 下山幸 治, 大山聖, 藤井孝藏,気流変動を考慮した火星探査航空機翼型のロバスト空力設計,第38回流体力学講演会, 第38回流体力学講演会講演集,1A17,pp. 63-66,室蘭市,室蘭工業大学,9月28日-29日,2006.
[25] 伊 藤匡人, マキロイ寛済, 大山聖, 藤井孝藏, 林光一,感圧・感温塗料を用いた斜め平板衝突噴流の解析,第84期日本機械学会流体工学部門講演会,流体工学部門講演会講演概要集,910,川越市,東洋 大学川越キャンパス,10月28日-29日,2006.
[26] 下山 幸治,大山 聖,藤井孝藏,多目的シックスシグマ手法の開発と火星航空機翼型ロバスト空力設計への適用,第19回計算力学講演会,第19回計算力学講演会講演論文集, pp. 189-190,名古屋市,11月3日-5日, 2006.
[27] 網谷修 男, 伊藤匡人, 今井源太, 藤井孝藏, 大山聖, 飯田明由,デルタ翼流れにおける一様流マッハ数効果に関する実験的研究,平成18年度宇宙航行の力学シンポジウム,相模原市,12月14-15, 2006.
[28] 桐迫啓誠, 藤井孝藏,大山聖,野中聡,山本誠,補助翼が付いた再使用観測ロケットのCN,CMp特性 に関する研究,平成18年度宇宙航行の力学シンポジウム,相模原市,12月14-15, 2006.
[29] 大 山聖,谷直樹,山西伸宏,藤井孝藏,宇宙工学分野における多目的最適化,第45回飛行機シンポジウム,北九州,北九州国際会議場,10月10日-10月 12日,2007.
[30] 大 山聖,飯塚宣行,藤本圭一郎,角有司,藤井孝藏,南里秀明,沖田耕一,JAXA基幹ロケットバルブの信頼性向上へ向けた開発の情報化,第17回設計工学・ システム部門講演会,仙台市,10月31日-11月2日,2007.
[31] 藤 本圭一郎,飯塚宣行,大山聖,角有司,藤井孝藏,南里秀明,沖田耕一,詳細FMEAデータをもとにしたインターフェース情報の可視化,第17回設計工学・ システム部門講演会,仙台市,10月31日-11月2日,2007.
[32] 田 中元史,林和夫,松田寿,大友文雄,野田悦夫,新関良樹,安井祐之,志村尚彦,藤井孝蔵,大山聖 ,二宮由光,非平衡プラズマによる気流制御(第1報)−プラズマ誘起噴流による翼面剥離抑制効果−,第85期日本機械学会流体工学部門講演会,広島大学, 11月17日-18日,2007.
[33] 大 山聖,網谷修男,堤誠司,飯田明吉,藤井孝藏,デルタ翼流れにおけるー様流マッハ数効果に関する実験的研究・第ニ報,平成19年度宇宙航行の力学シンポジ ウム,相模原市12月17日-18日,2007.
[34] 小川烈,藤井孝藏,大山聖,高速、高迎角におけるデルタ翼のマッハ数効果,第21回数値流体力学シン ポジウム,秋葉原,秋葉原コンベンションホール,12月19日-21日,2007.
[35] 谷 直樹,大山聖,山西伸宏,遺伝的アルゴリズムと格子モーフィングを使用したロケットエンジン用タービン翼形状最適化,第21回数値流体力学シンポジウム, 秋葉原,秋葉原コンベンションホール,12月19日-21日,2007.
[36] 大山聖,藤井孝藏,高迎角デルタ翼流れにおける一様流マッハ数効果,平成19年度科研費空力班シンポ ジューム,伊豆の国市,伊豆長岡KKR千歳荘,1月25日-26日,2008.
[37] 立 川智章,大山聖,藤井孝藏,多目的空力最適化におけるデータマイニング手法の研究,第13回計算工 学講演会,仙台市,仙台市民会館,計算工学講演会論文集,5月19日-21日,2008.
[38] 石 川義泰,大山聖,藤井孝藏,パレート最適翼型からの重要パラメータの抽出法,日本流体力学会年会2008,神戸市,9月4日-7日,2008.
[39]  Paul C. Verburg, Yoshiyuki Ishikawa, Akira Oyama, Kozo Fujii, "A Proposal of Airfoil Parameters Providing Good Correlation with Aerodynamic Performance," 第22回数値流体力学シンポジウム,東京都渋谷区,12月17日−19日,2008.
[40]  大 山聖,野々村拓,藤井孝藏,多目的空力形状最適化問題のパレート最適解の固有直交分解を用いた分析法の提案,進化計算シンポジウム2008,北海道登別 市,12月20日-21日,2008.
[41] 藤井 孝藏,大山聖,Paul C. Verburg,石川義泰,設計探査・データ探査利用の試み - 2次元遷音速翼型を例として,平成 20年度航空宇宙空力班シンポジウム,佐賀県嬉野市,1月22-23日,2009.
[42] 大山聖,野々村拓,藤井孝藏,固有直交分解を用いたパレート最適遷音速翼型のデータマイニング,日本航空宇宙学会北部支部2009年講演会/第10回再使 用型宇宙推進系シンポジウム,宮城県仙台市,3月11-12日,2009.
[43]大山聖,Paul C. Verburg,野々村拓,藤井孝藏,固有直交分解を用いたパレート最適翼型の流れ場マイニング,第14回計算工学講演会,東京都目黒区,5月12-14 日,2009.
[44] 谷直樹,吉田義樹,大山聖,内海政春,山西伸宏,遺伝的アルゴリズムを用いたインペラチップクリアランスの影響評価,ターボ機械協会第61回総会講演会, pp.63-68, 5月15日,2009.
[45] 大山聖,藤井孝藏,火星飛行機主翼の空力設計,1G07,第 53回宇 宙科学 技術連合講演会講演集[CD-ROM], 9月9-11,京都府京都市,2009.
[46]滑慶則,高木亮治,大山聖,山本誠,藤井孝藏,再使用観測ロケットの空力形状最適化に関する研究,第19回設計工学・システム部門講 演会,10月 28-30日,沖縄県読谷村,2009.
[47]大山聖,藤井孝藏,小型火星飛行機主翼の空力設計初期検討,宇宙航行の力学シンポジウム,12月10,11日,神奈川県相模原市, 2009.
[48] 小嶋亮次,野々村拓,大山聖,藤井孝藏,低レイノルズ数における3次元矩形薄翼の空力特性に関する研究,平成21年度宇宙航行の力学シンポジウム, 2009.
[49] 山崎佑希,野々村拓,大山聖,藤井孝藏,山本誠,翼周り渦挙動が羽ばたき翼性能に与える効果,第23回数値流体力学シンポジウム,2009.
[50] 滑慶則,高木亮治,大山聖,藤井孝藏,山本誠,再使用観測ロケット打ち上げおよび帰還時の空力特性評価,第23回数値流体力学シンポジウム,2009.
[51] 大山聖,他6名,飛行機を用いた火星探査,第10回宇宙科学シンポジウム,2010.
[52] 久保田孝,尾川順子,藤田和央,山田哲哉,大山聖,他,火星着陸探査の工学的技術チャレンジ,第10回宇宙科学シンポジウム,神奈川県相模原市,1月 7〜8日,2010.
[53] 野々村拓,小嶋亮次,福本浩章,大山聖,藤井孝蔵,低レイノルズ数における矩形翼とデルタ翼の空力特性比較,第42回流体力学講演会/航空宇宙数値シミュ レーション技術シンポジウム2010,1E11,鳥取県米子市,6月24〜25日,2010.
[54] Akira Oyama, Yasuhiro Kawakatsu, Kazuko Hagiwara, "Application of Multiobjective Design Exploration to Solar-C Orbit Design," The 20th JAXA Workshop on Astrodynamics and Flightmechanics, Kanagawa, Sagamihara, July 26-27, 2010.
[55] 宇佐美達也,伊藤慎一郎,大山 聖,藤井孝藏,DBD プラズマアクチュエータにおける駆動周波数が翼剥離制御に与える影響,S0502-3-6 ,日本機械学会2010年度年次大会,愛知県名古屋市,9月5〜8日,2010.
[56] Weipeng Li Taku Nonomura, Akira Oyama, and Kozo Fujii, "LES Study of Feedback-loop Mechanism in Supersonic Open Cavity Flows," 日本流体力学会年会2010,北海道札幌市,9月,2010.
[57] 大元雅英,吉川大弘,古橋武,大山聖,堤誠司,通信量を考慮したマルチプロセッサスケジューリング問題へのGAの適用方法に関する検討〜単一目的問題にお ける多様解の獲得に関する検討〜,第26回ファジィシステムシンポジウム,広島県広島市,9月,2010.
[58] 永井大樹,藤田昂志,浅井圭介,大山聖,竹内伸介,豊田裕之,小川博之,戸田和朗,岡田達明,藤井孝藏,米本浩一,砂田茂,得竹浩,小池勝,元田敏和,藤 田和央,火星探査航空機ワーキンググループ,火星探査航空機による高々度実証試験,平成22年度大気球シンポジウム,神奈川県相模原市,9月30日〜10 月1日,2010.
[59] 大山聖,MELOS1にむけた火星飛行機の概念検討,3F01,第54回宇宙 科学技術連合講演会,静岡県静岡市,11月17〜19日,2010.
[60] 小嶋亮次, 野々村拓, 大山聖, 藤井孝藏,低レイノルズ数における三次元矩形翼のアスペクト比とレイノルズ数の影響,3F07,第54回宇宙科学技術連合講演会,静岡県静岡市,11月 17〜19日,2010.
[61] 小嶋亮次, 李東輝, 野々村拓, 大山聖, 藤井孝藏,低レイノルズ数における空力性能評価手法に関する研究,3F08,第54回宇宙科学技術連合講演会,静岡県静岡市,11月17〜19日, 2010.
[62] 大山聖,MELOS1ミッションに向けた小型火星飛行機の空力設計初期検討,平成22年度宇宙航行の力学シンポジウム,神奈川県相模原市,12月16- 17日,2010.
[63] 小嶋亮次, 野々村拓, 大山聖, 藤井孝藏,低レイノルズ数における3次元矩形薄翼の空力特性に関する研究,平成22年度宇宙航行の力学シンポジウム,神奈川県相模原市, 12月16-17日,2010.
[64] 李東輝,小嶋亮次,野々村拓,大山聖,藤井孝藏,低レイノルズ数における薄翼の空力性能評価手法に関する研究,平成 22年度宇宙 航行の力学シンポジウム,神奈川県相模原市,12月16-17日,2010.
[65] 大山聖,川勝康弘,萩原和子,次期太陽観測衛星軌道 の多目的設計 探査の試み,進化計算シンポジウム2010,福岡県福岡市,12月,2010.
[66] 小杉幸寛,北川洋介,大山聖,藤井孝藏,金崎雅博,進化計算を用いた航空宇宙分野における多分野融合設計探査,進化計算シンポジウム2010,福岡県福岡 市,12月,2010.
[67] 小嶋亮次,野々村拓,大山聖,藤井孝藏,低レイノルズ数における厚翼と薄翼周り流れのiLES解析による特性比較,第24回数値流体力学シンポジウム, B7-3,神奈川県横浜市,12月,2010.
[68] 大山聖,永井大樹,竹内伸介,豊田裕之,砂田茂,得竹浩,小川博之,戸田和朗,小池勝,元田敏和,藤田和央,安部隆士,藤井孝藏,浅井圭介,火星探査航空 機WG,火星探査航空機の検討,第11回宇宙科学シンポジウム,神奈川県相模原市,1月,2011.
[69] 大山聖,藤井孝藏,立川智章,遺伝的プログラミングと空気力学と空力設計,平 成22年度航空宇宙空力班シンポジウム,L1,栃木県宇都宮市,1月, 2011.
[70] 藤井孝藏,小嶋亮次,野々村拓,大山聖,低レイノルズ数における翼型の空力特性に関して,平成22年度航空宇宙空力班シンポジウム,L3,栃木県宇都宮 市,1月,2011.
[71] 大山聖,川勝康弘,萩原和子,電気推進を用いたSOLAR-C軌道計画問題の多目 的設計探査,平成22年度宇宙輸送シンポジウム,STEP-2010- 22,神奈川県相模原市,1月,2011.
[72] 古渡直哉,大山聖,エルナン・アギレ,田中清,大規模個体集団を用いた進化計算の試み,2011年電子情報通信学会総合大会,ISS-P-340,東京都 世田谷区,3月,2011.
[73] 古渡直哉,大山聖,エルナンアギレ,田中清,
適応ε- Box支配と近傍交叉を用いた大集団MOEAの基礎検討,第1回進化計算学会研究会/第7回進化計算フロンティア研究会合同研究会,東京都,文京区,9 月,2011.
[74] 伊藤慎一郎,宇佐美達也,大山聖,藤井孝蔵,DBD プラズマアクチュエータにおいてバースト周波数がもたらす剥離制御の実験的解析,
日 本機械学会2011年度年次大会「先端技術フォーラム」,目黒区,東京都,9月,2011.
[75] 大山聖,他,火星探査飛行機の高高度飛行試 験計画,大気球シンポジウム,相模原市,神奈川県,10月,2011.
[76] 大山聖,他,火星探査航空機のミッション・設計検討,第49回飛行機シンポジウム,3F1,石川県,金沢市,10月,2011.
[77]
古渡直哉,大山聖,エルナンアギレ,田中清,適応ε-Box支配を用いた大集団MOEAにおける近傍交叉の効果,平成23年度電子情報通信 学会信越支部大会,新潟県,柏崎市,10月,2011.
[78]
古渡直哉,大山聖,エルナンアギレ,田中清,MOEAにおける 集団サイズ増加の効果,平成23年度電子情報通信学会信越支部大会,新潟 県,柏崎市,10月,2011.
[79] 古渡直哉,大山聖,エルナンアギレ,田中清,大集団MOEAにおける適応ε-Box支配の効果,平成23年度電子情報通信学会信越支部大 会,新潟県,柏崎市,10月,2011.
[80] 大山聖,米本浩一,竹内伸介,得竹浩,永井大樹,砂田茂,大槻真嗣,火星探査飛行機の多目的設計探査,第55回宇宙科学技術連合講演会,愛媛県,松山市, 11月,2011.
[81] 安養寺正之,野々村拓,大山聖,藤井孝藏,野瀬慶,沼田 大樹,永井大樹,浅井圭介,低レイノルズ数領域における石井翼の空力特性評価,第55回宇宙科学技術連合講演会,愛媛県,松山市,11月,2011.
[82] 立川智章,野々村拓,大山聖,藤井孝藏,再使用観測ロケットの多目的空力設計探査,第55回宇宙科学技術連合講演 会,愛媛県,松山市,11月,2011.
[83] 大山聖,川勝康弘,萩原和子,太陽極域観測衛星軌道設計の多目的設計探査,進化計算シンポジウム2011,宮城県,岩沼市,12月,2011.
[84] 古渡直哉,大山聖,エルナンアギレ,田中清,多数目的最適化における集団サイズと交叉の降下に関する検討,進化計 算シンポジウム2011,宮城県,岩沼市,12月,2011.
[85] 立川智章,野々村拓,大山聖,藤井孝藏,パレート最適解からの設計知見抽出のための多目的遺伝的プログラミングの提案と再使用観測ロケット空力設計問題で の実証,進化計算シンポジウム2011,宮城県,岩沼市,12月,2011.
[86]宇賀神,青野光,野々村拓,大山聖,藤井孝藏,山本誠,平均揚力最大時の羽 ばたき翼の三次元効 果の解析,第25回数値流体力学シンポジウム,大阪府,吹田市,12月,2011.
[87] 青野光,野々村拓,安養寺正之,大山聖,藤井孝藏,低レイノルズ数流れにおける固
定翼翼断面形状の空力性能への影響,第25回数値流体力学シンポジウム,大阪府,吹 田市,12月,2011.
[88] 大山聖,米本浩一,竹内伸介,得竹浩,永井大樹,砂田茂,大槻真嗣,MELOS1に 向けた火星探査飛行機の多目的設計探査,平成23年度宇宙航行の力学シンポジウム,12月,2011.
[89] 安養寺正之,野々村拓,大山聖,藤井孝藏,野中聡,火星探査飛行機の空力性能評価に向けた惑星環境風洞の動作特性,平 成23年度宇宙航行の力学シンポジウム,12月,2011.
[90] 立川智章,野々村拓,大山聖,藤井孝藏,再使用観測ロケット計上の多目的空力設計探査,平成23年度宇 宙航行の力学シンポジウム,12月,2011.
[91] 掘暖,清水太郎,北村圭一,大山聖,進化計算によるレゾネータ設計の最適化と大振幅時の減衰特性の検討,第49回燃焼シンポジウム,神奈川県,横浜市, 12月,2011.
[92] 大山聖,他,火星表面探査用航空機の研究開発,第12回宇宙科学シンポジウム,神奈川県,相模原市,1月, 2012.
[93] 藤田和央,宮本英昭,岡田達明,石上玄也,尾川順子,大山聖,佐藤毅彦,久保田孝,MELOS1 EDLシステ ム概要,第12回宇宙科学シンポジウム,神奈川県,相模原市,1月,2012.
[94] 尾川順子,石井信明,津田雄一,川勝康弘,川口淳一郎,松本道弘,藤田和央,大山聖,石上玄也,久保田孝,佐 藤毅彦,MELOS1軌道とミッション・オペレーション,第12回宇宙科学シンポジウム,神奈川県,相模原市,1月,2012.
[95] 森澤征一郎, 野々村拓, 大山聖, 藤井孝藏, 大林茂,データマイニングによる斜め平板に衝突する超音速ジェットから発生する音響波の理解,第44回流体力学講演会/航空宇宙数値シミュレーション技術 シンポジウム,富山県富山市,7月5日6日,2012,
[96] 西尾豊,大山聖, エルナンアギレ,田中清,適応ε-Box支配を用いたMOEAにおける近傍交叉の一検討,平成24年度電子情報通信学会信越支部大会,新潟県新潟市, 10月13日,2012.
[97] 大山聖,永井大樹,得竹浩,竹内伸介,豊田裕之,藤田昂志,安養寺正之,元田敏和,米本浩一,浅井圭介,藤井孝藏,火星探査航空機ワーキンググループ,火 星探査飛行機の高高度飛行試験計画(その2),平成24年度大気球シンポジウム,神奈川県相模原市,10月16日17日,2012.
[98] 大山聖,永井大樹,得竹浩,竹内伸介,豊田裕之,藤田昂志,安養寺正之,元田敏和,米本浩一,MELOS1にむけた火星飛行機の高高度飛行試験計画,第 56回宇宙科学技術連合講演会,大分県別府市,11月20日〜22日,2012.
[99] 近藤勝俊,青野光,野々村拓, 安養寺正之, 大山聖, Liu Tianshu,藤井孝藏, 山本誠,火星航空機に向けた低Re数における数値シミュレーションによるOwl翼の空力特性,第56回宇宙科学技術連合講演会,大分県別府市,11月20 日〜22日,2012.
[100] 佐々木岳, 立川智章, 野々村拓, 大山聖, 米本浩一,松本剛明,遺伝的アルゴリズムによる低レイノルズ数高揚抗比翼型の設計探査,第56回宇宙科学技術連合講演会,大分県別府市,11月20日 〜22日,2012.
[101] 安養寺正之,永井大樹,大山聖,藤井孝藏,火星飛行機の全機特性,第56回宇宙科学技術連合講演会,大分県別府市,11月20日〜22日,2012.
[102] 元田敏和,大山聖,永井大樹,得竹浩,火星探査航空機にむけた高高度飛行試験の飛行経路検討,第56回宇宙科学技術連合講演会,大分県別府市,11月20 日〜22日,2012.
[103] 廣瀬史子,中宮賢樹,大山聖,Antonio L Jaimes,竹内央,川勝康弘,DESTINY ミッションプロファイル,第56回宇宙科学技術連合講演会,大分県別府市,11月20日〜22日,2012.
[104] 山本高行, 川勝康弘, 大山聖, 萩原和子,イプシロンロケットによる高エネルギ軌道投入,第56回宇宙科学技術連合講演会,大分県別府市,11月20日〜22日,2012.
[105] 大山聖,川口淳一郎,産学官連係-航空宇宙学会が果たすべき役割とその将来像,第56回宇宙科学技術連合講演会,大分県別府市,11月20日〜22日, 2012.
[106] 安養寺正之,永井大樹,大山聖,藤井孝藏,火星飛行機の全機空力特性に関する惑星環境風洞試験,平成24年度宇宙航行の力学シンポジウム,神奈川県相模原 市,12年13日14日,2012.
[107] 近藤勝俊,青野光,野々村拓,安養寺正之,大山聖,Tianshu Liu,藤井孝藏,山本誠,火星探査航空機に向けた低レイノルズ数におけるフクロウ翼の空力特性,平成24年度宇宙航行の力学シンポジウム,神奈川県相模 原市,12年13日14日,2012.
[108] 大山聖,世界初の火星飛行機の実現を目指して,平成24年度宇宙航行の力学シンポジウム,神奈川県相模原市,12年13日14日,2012.
[109] Antonio López, Akira Oyama, Kozo Fujii, “Evaluating Two Evolutionary Approaches to Solve a Many-objective Space Trajectory Design Problem,” 進化計算シンポジウム2012,長野県軽井沢町,12月15日16日,2012.
[110] Hernán Aguirre, Akira Oyama, and Kiyoshi Tanaka, “A Study on Mappings for Evolutionary Many-objective Distribution Search,” 進化計算シンポジウム2012,長野県軽井沢町,12月15日16日,2012.
[111] Hernán Aguirre, Akira Oyama, and Kiyoshi Tanaka, “A Study on Neighborhoods for Survival and Mating Selection for Many-objective Optimization,” 進化計算シンポジウム2012,長野県軽井沢町,12月15日16日,2012.
[112] Taufik Sulaiman, Satoshi Sekimoto, Tomoaki Tatsukawa, Taku Nonomura, Akira Oyama, Kozo Fujii, “Multi-Objective Design Exploration (MODE) for DBD Plasma Actuator based on Wind Tunnel Testing,” 進化計算シンポジウム2012,長野県軽井沢町,12月15日16日,2012.
[113] 飯田大貴,佐々木岳,大山聖,藤井孝藏,米本浩一,翼型形状のクラスタリングによる非劣解の分析方法の提案,進化計算シンポジウム2012,長野県軽井沢 町,12月15日16日,2012.
[114] 近藤勝俊,青野光,野々村拓,安養寺正之,大山聖,Tianshu Liu,藤井孝藏,山本誠,LESによるフクロウ翼(Re=23000)の空力特性評価,第26回数値流体力学シンポジウム,D07-4,東京都渋谷区, 12月18日-20日, 2012.
[115] 大山聖,藤井孝藏,Taufik Slaiman,風洞実験に基づく多目的設計探査,平成24年度航空宇宙空力班シンポジウム,京都府亀岡市,1月25日26日,2013.
[116] 安養寺正之, 岡本正人, 日高秀徳, 大山聖, 藤井孝藏,火星探査航空機のスケール機による空力性能評価,日本航空宇宙学会北部支部2013年講演会,宮城県仙台市,3月14日15日,2013.
[117] Hernán Aguirre, Akira Oyama, and Kiyoshi Tanaka, “A Study on ε-Mappings and Recombination Rate for Distribution Search in Evolutionary Many-objective Optimization,”,第4回進化計算学会研究会,神奈川県 横須賀市,3月18日19日,2013.
[118] Naoya Kowatari, Akira Oyama, Hernán Aguirre, and Kiyoshi Tanaka, “A Study on Population Size and Neighborhood Recombination in Evolutionary Many-Objective Continuous Optimization,”,第4回進化計算学会研究会,神奈川県 横須賀市,3月18日19日,2013.
[119] 藤田和央,石上玄也,尾川順子,大山聖,山田和彦,久保田孝,宮本英昭,佐藤毅彦,火星着陸技術実証機と地上探査,日本航空宇宙学会第44期年会講演会, 東京都文京区,4月18日19日,2013.
[120] 日高秀徳,安養寺正之,大山聖,岡本正人,火星飛行機の全機模型低速風洞実験,日本航空宇宙学会第44期年会講演会,東京都文京区,4月18日19日, 2013.
[121] 立川智章,長田裕樹,山本誠,野々村拓,大山聖,藤井孝藏,ロケットの射点設計に向けた空力音響最適化問題の多目的設計探査,W121002,日本機械学 会2013年度年次大会,2013.
[122] 藤田和央,他,火星着陸探査機の概念設計ベースライン,第57回宇宙科学技術連合講演会,JSASS-2013-4303,米子,2013年10月10 日.
[123] 安養寺正之,野々村拓,大山聖,藤井孝藏,永井大樹,低Re数領域の平面形空力特性に対するRe数効果,第57回宇宙科学技術連合講演会,JSASS- 2013-4547米子,2013年10月11日.
[124] 安養寺正之, 野々村拓,大山聖, 藤井孝藏,永井大樹,低レイノルズ数領域の平面形空力特性に対するレイノルズ数効果, 第57回宇宙科学技術連合講演会,米子,2013年10月11日.
[125] 藤岡直也,野々村拓,大山聖,藤井孝藏,山本誠,火星探査航空機の空力性能に対する各部位の寄与,第57回宇宙科学技術連合講演会,米子,2013年10 月11日.
[126] 山本高行,中宮賢樹,坂東麻衣,萩原和子,大山聖,廣瀬史子,Campangnola Stefano,Jaimes Antonio,Zuianni Federico,川勝 康弘,DESTINY軌道計画,第57回宇宙科学技術連合講演会,米子,2013年10月11日.
[127] 佐藤毅彦,他,火星探査計画MELOS1 の概要,2C05,第57回宇宙科学技術連合講演会,米子,2013年10月.
[128] 宮本英昭,他,MELOS1のめざすサイエンスと着陸候補地点,2C06,第57回宇宙科学技術連合講演会,米子,2013年10月.
[129] 尾川順子,他,MELOS1の軌道設計と着陸候補地点評価,2C08,第57回宇宙科学技術連合講演会,米子,2013年10月.
[130] 立川智章,長田裕樹,山本誠,野々村拓,大山聖,藤井孝藏,ロケット射点形状に関する空力音響多目的設計問題の非劣解データベースの分析,1909,日本 機械学会第26回計算力学講演会,2013.
[131] 立川智章,長田裕樹,山本誠,野々村拓,大山聖,藤井孝藏,進化計算とLESを用いたロケット射点形状の空力音響多目的設計探査,0634,日本機械学会 流体工学部門講演会講演論文集,2013.
[132] 大山聖,永井大樹,得竹浩,竹内伸介,豊田裕之,高橋優,大槻真嗣,元田敏和,岡本正人,安養寺正之,野々村拓,鎌田幸男,藤田昂志,平栗弘貴,佐々木 岳,米本浩一,浅井圭介,藤井孝藏,火星探査航空機ワーキンググループ,"火星探査飛行機の高々度飛行試験計画(その3)," 平成25年度大気球シンポジウム,神奈川,2013年11月.
[133] 近藤勝俊,安養寺正之,岡本正人,野々村拓,大山聖,藤井孝藏,山本誠, “低レイノルズ数における尾翼の舵効き性能評価”, 宇宙航行の力学シンポジウム2013, 宇宙科学研究所,2013年12月
[134] 立川智章,飯田大貴 ,野々村拓,大山聖,藤井孝藏,PODを用いたロケット射点形状多目的設計問題の非劣解の分析,進化計算シンポジウム2013,12月5-6日, 2013.

[135] 立川智章, Antonio Lopez Jaimes, 大山聖, 藤井孝藏,実問題を用いた多数目的最適化における進化的アルゴリズムの性能比較 - 衛星軌道設計問題を題材に-,進化計算シンポジウム2013,12月5-6日,2013.
[136] Antonio Lopez, Akira Oyama, and Kozo Fujii, "A Ranking Method Based on Two Preference Criteria: Chebyshev Function and e-indicator," 進化計算シンポジウム2013,12月5-6日,2013.
[137] 西尾豊,大山聖,秋本洋平,アギレエルナン,田中清,衛星軌道設計問題にAeSeHを用いて得られたPOSに関する一考察,進化計算シンポジウム 2013,12月5-6日,2013.
[138] 飯田大貴,大山聖,藤井孝藏,固有直交分解を用いたクラスタリングによる翼型形状最適化結果の詳細分析,進化計算シンポジウム2013,12月5-6日, 2013.
[139] 大山聖,他,火星探査飛行機の高高度飛行試験,P2-136,宇宙科学シンポジウム,2014.
[140] 藤田和央,他,火星着陸探査技術実証機検討の現状報告,P2-133,宇宙科学シンポジウム,2014.
[141] 佐藤峻介,山本高行,川勝康弘,大山聖,萩原和子,イプシロンロケットによるDESTINYの高エネルギ軌道投入,P2-175,宇宙科学シンポジウム,2014.

[142] 大山聖,立川智章,野々村拓,藤井孝藏,ロケット射点火炎偏向板の空力音響多目的設計探査,2L12,平成25年度航空宇宙空力シンポジウム,2014年1月24-25日,北海道登別市,2014.
[143] 福本浩章,浅野兼人,青野光,渡辺毅,田中元史,松田寿,大迫俊樹,野々村拓,大山聖,藤井孝藏,ピッチング翼周りの動的失速流れ制御におけるDBDプラズマアクチュエータ設置位置の影響,第28回数値流体力学シンポジウム,B12-3,東京都江戸川区,2014年12月.

[144 A Parallelized ACO Framework for Many-Objective Optimization, martin Schlueter, Takeshi Watanabe, and Akira Oyama, 進化計算シンポジウム2014, P3-16,広島県廿日市市,2014年12月20-21日.

[145] 解の探索方向を考慮した多数目的進化型アルゴリズムAεSεHの一検討,矢澤佑記, 大山聖, 秋本洋平, アギレエルナン, 田中清,進化計算シンポジウム2014, P4-01,広島県廿日市市,2014年12月20-21日.

[146] ハイパーヴォリュームの並列高速計算,渡辺毅,立川智章,大山聖,進化計算シンポジウム2014, P1-05,広島県廿日市市,2014年12月20-21日.

[147] 多数目的進化計算における集団サイズの超大規模化に関する一検討,立川智章,渡辺毅,大山聖,進化計算シンポジウム2014,P2-10,広島県廿日市市,2014年12月20-21日.

[148] Schlueter Martin, Watanabe Takeshi, Oyama Akira,超並列蟻コロニー最適化法による多数目的最適化日本機械学会第11回最適化シンポジウム(OPTIS2014) ,1112,石川県金沢市,2014年12月12-13日.

[149] 渡辺毅,萩原和子,立川智章,Chit Hong Yam, Federico Zuiani,大山聖,川勝康弘,DESTINY軌道設計の多目的設計探査,日本機械学会第11回最適化シンポジウム(OPTIS2014), 1219,石川県金沢市,2014年12月12-13日.

[150] 佐藤峻介,山本高行,川勝康弘,大山聖,萩原和子,多目的遺伝的アルゴリズムを用いたイプシロンロケットの軌道最適化,日本機械学会第11回最適化シンポジウム(OPTIS2014), 2109,石川県金沢市,2014年12月12-13日.

[151] 大山聖,立川智章,渡辺毅,スーパーコンピュータ「京」を用いた大規模多目的設計探査,日本機械学会第11回最適化シンポジウム(OPTIS2014) ,1218,石川県金沢市,2014年12月12-13日.

[152] 立川智章,渡辺毅,大山聖,超大規模集団サイズを用いた多数目的最適化に向けた進化計算手法の開発,日本機械学会第11回最適化シンポジウム(OPTIS2014) ,1113,石川県金沢市,2014年12月12-13日.

[153] 永井大樹, 安養寺正之 , 野々村拓,近藤勝俊,大山聖,岡本正人,佐々木岳 , 松本剛明 , 米本浩一,金崎雅博,砂田茂,米澤宏一,小池勝,藤田昂志, 浅井圭介,藤井孝藏,火星探査航空機 WG における空力研究のこれまでの 成果と現状,第 58 回 宇宙科学技術連合講演会,長崎県長崎市,1B01,2014年11月.

[154] 豊田 裕之 , 高橋 優 , 嶋田 貴信,鷲尾 英俊,小出 和也 , 大登 裕樹,大山 聖,火星探査を実現する軽量な太陽電池およびバッテリ の開発,第 58 回 宇宙科学技術連合講演会,長崎県長崎市,1B06,2014年11月.

[155] 藤田 昂志 , 永井 大樹,大山 聖,火星着陸探査技術実証機への搭載を目指した火星飛 行機の概念設計,第 58 回 宇宙科学技術連合講演会,長崎県長崎市,1B07,2014年11月.

[156] 佐藤 峻介 , 山本 高行 , 川勝 康弘 , 大山 聖,萩原 和子,イプシロンロケットによる高エネルギ軌道への投入,第 58 回 宇宙科学技術連合講演会,長崎県長崎市,1B20,2014年11月.

[157] 山 本 高 行 , 川 勝 康 弘 , Yam Chit Hong, Campagnola Stefano, 杉本 理英 , 大山 聖 , 立川 智章 , 渡辺 毅 , 廣瀬 史子 , 池永 敏憲,萩原 智子,小倉 聡司,中宮 賢樹,スパイラル軌道上昇と軌道計画,第 58 回 宇宙科学技術連合講演会,長崎県長崎市,1B21,2014年11月.

[158] 小郷原 一智,大山 聖,永井 大樹,得竹 浩,DESTINY 応用:火星気象衛星と火星航空機によるダ スト輸送メカニズムの解明ミッション,第 58 回 宇宙科学技術連合講演会,長崎県長崎市,2B08,2014年11月.

[159] 李 東輝,野々村 拓 , 大山 聖 , 藤井 孝藏,低レイノルズ数領域の翼型空力性能評価のための数 値計算法の比較,第 58 回 宇宙科学技術連合講演会,長崎県長崎市,2H14,2014年11月.

[160] 大山聖,永井大樹,得竹浩,竹内伸介, 豊田裕之, 宮澤優, 大槻真嗣,元田敏和,岡本正人,安養寺正之, 野々村拓, 鎌田幸男,藤田昂志,平栗弘貴,佐々木岳, 米本浩一,浅井圭介,藤井孝藏,火星探査飛行機の高高度飛行試験の進捗報告,平成26年度大気球シンポジウム,神奈川県相模原市,2014年11月6-7日.

[161] 森澤征一郎,野々村拓,大山聖,藤井孝藏,大林茂,低Re数域における翼型の空力特性に及ぼすマッハ数効果,第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム,1D10,青森県弘前市,2014年7月3日-4日.

[162] 安養寺正之、 岡本正人、藤岡直也、野々村拓、永井大樹、大山聖、藤井孝藏、山本誠、火星探査航空機の全機空力特性に関する風洞実験および数値解析,第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム、1D11、青森県弘前市、2014年7月3日-4日.

[163] 安藤善紀、野々村拓、大山聖、藤井孝藏、大林茂、低レイノルズ数における垂直突風に対する翼型の応答解析,第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム、2D02、青森県弘前市、2014年7月3日-4日.

[164] 安藤善紀,野々村拓,大山聖,藤井孝藏,大林茂,突風に強固な火星飛行機の翼の空力設計に向けた垂直突風に対する翼型の応答解析,平成26年度宇宙航行の力学シンポジウム,神奈川県相模原市,2014年12月18-19日.

[165] 藤田和央,石上玄也,畠中龍太,高井元,豊田裕之,尾川順子,春木美鈴,竹内央,野々村拓,山田和彦,高柳大樹,小澤宇志,松山新吾,大山聖,火星着陸技術実証機のシステム構成と技術開発,第15回宇宙科学シンポジウム,P-192(ポスター),神奈川県相模原市,2015年1月6-7日.

[166] 小郷原一智,大山聖,永井大樹,得竹浩,火星気象衛星と火星飛行機による ダスト輸送メカニズム解明ミッション,第15回宇宙科学シンポジウム,P-203(ポスター),神奈川県相模原市,2015年1月6-7日.

[167] 大山聖,川勝康弘,船木一幸,豊田裕之,對木淳夫,児子健一郎,新宇宙探査技術実験ミッションDESTINYのミッション要求とシステム要求,第15回宇宙科学シンポジウム,P-265(ポスター),神奈川県相模原市,2015年1月6-7日.

[168] 岩田隆浩,川勝康弘,村上豪,池永敏憲,江副祐一郎,亀田真吾,桂華邦裕,荒井朋子,松浦周二,佐伯孝尚,今村剛,小郷原一智,大山聖,DESTINYを用いた太陽系探査,第15回宇宙科学シンポジウム,P-266(ポスター),神奈川県相模原市,2015年1月6-7日.

[169] 山本高行,Yam Chit Hong, Campagnola Stefano,杉本理英,大山聖,立川智章,渡辺毅,廣瀬史子,池永敏憲,川勝康弘,萩原和子,小倉聡司, Srali Bruno,中宮賢樹,佐藤峻介,DESTINY機動計画,第15回宇宙科学シンポジウム,P-268(ポスター),神奈川県相模原市,2015年1月6-7日.

[170] 大山聖,火星飛行探査の検討の現状と将来計画,第2回火星科学研究会,兵庫県神戸市,2015年1月16-17日.

[171] 西山万里,大嶽久志,星野健,橋本樹明,渡辺毅,立川智,大山聖,月周回衛星「かぐや」のデータを用いた多目的最適化による月着陸最適候補地の選定,2014年度宇宙科学情報解析シンポジウム,神奈川県相模原市,2015年2月13日.




翻訳

[1] (原著)Lohner, R., Baum, J. D., Charman, C., and Pelessone, D. (翻訳)大山聖,「第一原理に基づくCFDCSD連成コードによる構造物への爆風効果の予測」, 計算工学,Vol.9, No.3,pp.30-37, 2004.




博士論文

Wing Design Using Evolutionary Algorithm
Akira Oyama, March 2000

Abstract
Although Evolutionary Algorithms (EAs) have become increasingly popular in aerodynamic design problems, the previous applications of EAs are restricted to more or less simplified problems involving not more than 10-30 design parameters. In contrast to that, in real-world design problems, a large number of design parameters must be handled ? for example, a wing shape for a generic transonic aircraft usually parameterized by more than a hundred of design parameters. Since such problem has a highly multidimensional search space and extremely complicated objective function distribution, standard EAs would fail to find a globally optimum. This research develops a new, robust, and efficient numerical design method applicable to such real-world aerodynamic design problems.
One of the most important difficulties in real-world aerodynamic shape design problems is their highly multidimensional design space. To develop a robust and efficient EA applicable to such design problems, the real-coded ARGAs have been developed by incorporating the idea of the binary-coded ARGAs with the use of the floating-point representation. The performance of the proposed EAs was demonstrated by applying to a typical test function minimization problem and an aerodynamic airfoil shape optimization problem. The real-coded ARGAs consistently found better solutions than the conventional real-coded GAs do.
Because the flow field is governed by a system of nonlinear partial differential equations, objective function landscape of an aerodynamic optimization is often multimodal and nonlinear. To improve EAs’ capability of finding a global optimum in such a problem, a crossover operator based on the structured coding has been proposed. The coding structure of the design variables is constructed according to the interaction information among design parameters analyzed by the experimental design. Aerodynamic optimizations of a transonic wing demonstrated that the crossover based on the structured coding was more efficient than the traditional one.
To ensure the capability of the present EA in handling large-scale aerodynamic design optimizations, the real-coded ARGA coupled with the crossover based on the structured coding is applied to an aerodynamic design optimization of a transonic wing shape for generic transport aircraft. Aerodynamic performances of the design candidates are evaluated by using the three-dimensional compressive Navier-Stokes equations to guarantee an accurate model of the flow field. Structural constraint is introduced to avoid an apparent solution of zero thickness wing for low drag in high speeds. To overcome enormous computational time necessary for the optimization, the computation is parallelized on NWT. The designed wing had a good L/D value satisfying the given structural constraint on wing thickness.
Finally, an EA is applied to an aerodynamic wing shape design for a supersonic transport to examine the feasibility of the EA-based optimization in supersonic wing design optimizations. The optimum design obtained from the present approach yielded both the minimum induced drag and the minimum volume wave drag in the given design space. The design also indicated the most important features of supersonic wing design as compared with conventional transonic wing design as follows:
1) Warp geometry based on camber line and twist angle distributions plays a more important role than spanwise thickness distribution because the thickness becomes simply as thin as possible. 2) Because the wing thickness constraint comes from the wing structure, a practical structural constraint will be required.

Contents

Table of Contents
contents.ps.gz
Chapter 1: Introduction
Chapter1.ps.gz Chapter1.pdf
Chapter 2: Real-Coded Adaptive Range Genetic Algorithm
Chapter2.ps.gz Chapter2.pdf
Chapter 3: Evolutionary Algorithms Based on Structured Coding for Aerodynamic Wing Optimizations
Chapter3.ps.gz Chapter3.pdf
Chapter 4: Transonic Wing Design Optimization Based on Evolutionary Algorithm
Chapter4.ps.gz Chapter4.pdf
Chapter 5: Supersonic Wing Design Optimization Based on Evolutionary Algorithm
Chapter5.ps.gz Chapter5.pdf
Chapter 6: Summary and Further Work
Chapter6.ps.gz Chapter6.pdf