著者

杉浦 正彦 田辺 安忠 菅原 瑛明 木村 桂大 竹川 国之 大山 聖 佐藤 允 金崎 雅博 岸 祐希 SUGIURA Masahiko TANABE Yasutada SUGAWARA Hideaki KIMURA Keita TAKEKAWA Kuniyuki OYAMA Akira SATO Makoto KANAZAKI Masahiro KISHI Yuki

出版者

宇宙航空研究開発機構(JAXA)

雑誌

宇宙航空研究開発機構特別資料: 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2020オンライン論文集 = JAXA Special Publication: Proceedings of Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online (ISSN:24332232)

巻号頁・発行日

vol.JAXA-SP-20-008, pp.157-164, 2021-02-08

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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2020オンライン (2020年9月28日-30日. 日本航空宇宙学会 : 宇宙航空研究開発機構(JAXA)オンライン会議)

著者

岸 祐希 金崎 雅博 牧野 好和 松島 紀佐

出版者

一般社団法人 日本機械学会

雑誌

日本機械学会論文集 (ISSN:21879761)

巻号頁・発行日

vol.83, no.849, pp.16-00454-16-00454, 2017 (Released:2017-05-25)

参考文献数

20

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When a wing of airplane is designed, it is necessary to have knowledge regarding planforms considered their optimum airfoils in order to design efficiently, because each wing planform has both of advantage and disadvantage. In this study, the wing design problem for supersonic transport is carried out for different planforms for two different planforms. Multi-objective problem, which is minimization drags for two supersonic cruise conditions (transonic and supersonic flight) is solved to obtain knowledge of the supersonic airfoil from the viewpoint of the multi-point design. Two types of planforms are considered—a cranked arrow wing with a high sweep-back angle and a single tapered wing with a low sweep-back angle. Optimization problems are carried out by efficient global optimization, which is evolutionary algorithm based on the Kriging surrogate model. To acquire design knowledge, a parallel coordinate plot and functional analysis of variance (functional ANOVA) are applied. The design results showed the difference airfoil between two planforms. The optimum airfoil for the single tapered wing has a small or negative camber at the leading edge to minimize the supersonic cruising. On the other hand, the optimum airfoil for the cranked arrow wing has an airfoil with a lower thickness and larger camber at the leading edge.

著者

大山 聖 永井 大樹 藤田 昂志 安養寺 正之 岡本 正人 江 光希 金崎 雅博 高野 敦 水上 諒 竹内 伸介 安部 明雄 佐々 修一 布田 翼 満武 勝嗣 得竹 浩 火星探査航空機リサーチグループ Oyama Akira Nagai Hiroki Fujita Koji Anyoji Masayuki Okamoto Masato Koh Mitsuki Kanazaki Masahiro Takano Atsushi Mizukami Ryo Takeuchi Shinsuke Abe Akio Sasa Shuichi Futa Tsubasa Mitsutake Katsushi Tokutake Hiroshi

出版者

宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)

雑誌

大気球シンポジウム: 平成30年度 = Balloon Symposium: 2018

巻号頁・発行日

2018-11

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大気球シンポジウム 平成30年度(2018年11月1-2日. 宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)), 相模原市, 神奈川県

著者

金崎 雅博 千葉 一永 北川 幸樹 嶋田 徹

出版者

進化計算学会

雑誌

進化計算学会論文誌 (ISSN:21857385)

巻号頁・発行日

vol.6, no.3, pp.137-145, 2015 (Released:2015-12-18)

参考文献数

19

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With the multi-combustion technology, the combustion in a hybrid rocket engine (HRE) can be temporarily stopped via oxidizer throttling. In this paper, two types of HREs, one with multi-combustion technology and the other without, are compared to investigate the effects of multi-combustion on the flight performance of launch vehicles (LVs). Non-dominated Sorting Genetic Algorithm-II (NSGA-II) which was a multi-objective evolutionary algorithm (MOEA) was applied to solve the design problems using real-number coding and the Pareto ranking method. To investigate the effects of the multi-combustion on flight performance of LV with HRE, three design problems were considered. The first case was the maximization of the flight altitude and the minimization of the gross weight. The second case was the minimization of the maximum acceleration and the minimization of the gross weight. The final case was the maximization of the flight downrange and the minimization of the gross weight. Many non-dominated solutions were obtained by NSGA-II, and a trade-off was observed between the two objective functions in each case. MOEA results were visualized using a parallel coordinate plot. According to the exploration result, it was found that the multi-combustion of HRE was effective to reduce the maximum acceleration. Such ability could be expected to reduce the shock load to payloads carried by the LV with HRE.

著者

小堺 孝和 加藤 裕之 中北 和之 金崎 雅博

出版者

一般社団法人 日本機械学会

雑誌

日本機械学会論文集 (ISSN:21879761)

巻号頁・発行日

pp.15-00188, (Released:2015-08-20)

参考文献数

13

被引用文献数

1 1

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The “buffet” which is the shock wave vibration on the wing at transonic speed has influence to the aerodynamic performance of the civil transport. It is significant because the wing cannot maintain its aerodynamic performance and it is also led to the stall. Therefore, several researches on the suppression of the buffet are carried out. A Vortex Generator (VG) is one of the way which can improve to the transonic buffet. It is simple device and widely applied to the commercial airplane. Conventionally, VGs are installed along the wing span. However, they increase the friction and the instruction drag. Thus, the number of VGs should not be beyond the minimum necessary. Another problem is that it is still expensive for the computational fluid dynamics to simulate the small size vortex accurately. Therefore, the optimization procedure of the VGs installation is developed with directly combining the wind tunnel evaluation result. To reduce the number of experimentations, the surrogate model based GA exploration is employed. The design objective is to maintain the linearity of the variation lift with changing angle of attack (lift curve), because the stall is appeared if the curvature of the lift curves become smaller. Eight initial designs are evaluated and five design samples are acquired. As this result, optimum samples can be explored with reducing the number of the experiment. Several samples successfully prevent the stall without increasing the drag. In addition, the design knowledge can be obtained regarding the optimum VG’s layout by visualization.

著者

千葉 一永 金崎 雅博

出版者

進化計算学会

雑誌

進化計算学会論文誌 (ISSN:21857385)

巻号頁・発行日

vol.4, no.1, pp.28-37, 2013 (Released:2013-05-17)

参考文献数

22

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Design informatics, which is the efficient design methodology, has three points of view. The first is the efficient exploration in design space using evolutionary-based optimization methods. The second is the structurization and visualization of design space using data mining techniques. The third is the application to practical problems. In the present study, the influence of the difference among the seven pure and hybrid optimization methods for design information has been investigated in order to explain the selection manner of optimization methods for data mining. The practical problem of a single-stage hybrid rocket is picked up as the present design object. A functional analysis of variance and a self-organizing map are employed as data mining techniques in order to acquire the global design information in dasign space. As a result, mining result depends on not the number of generation (i.e. convergence) but the optimization methods (i.e. exploration space). Consequently, the optimization method with diversity performance is the beneficial selection in order to obtain the global design information in design space.

著者

岸 祐希 アリヤリ アタフォン 金崎 雅博

出版者

進化計算学会

雑誌

進化計算学会論文誌 (ISSN:21857385)

巻号頁・発行日

vol.12, no.3, pp.137-147, 2021 (Released:2022-01-18)

参考文献数

32

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In this study, a multi-fidelity approach was developed based on the efficient global optimization (EGO) and integrated with multi-additional sampling. The developed approach was more efficient than the conventional multi-fidelity approach when applied to design problems. The effectiveness of the proposed approach was demonstrated by solving two test problems (a test problem in Van Valedhuizen’s test suite and a test problem with a convex Pareto front) before applying the approach to real-world problems. As a demonstration of solving real-world problem, we solved two objective airfoil design problems for a small unmanned airplane. The objective functions were the drag coefficient (for flight efficiency) and the thickness at the 75% chord position (for structural strength and manufacturability). The results of the test problems revealed that the proposed approach obtained more non-dominant solutions near the theoretical Pareto front than those obtained by the Original optimization approach at the same iteration number of EGO loop; this is because the proposed approach obtained more additional samples than the Original optimization approach (multi-objective multi-fidelity EGO without multi-additional sampling) per additional sampling loop. A comparison of the accuracies of surrogate models based on the proposed approach and the Original optimization approach using leave-one-out cross validation suggested that, depending on the optimization problem, one of the two approaches can yield greater accuracy. The airfoil design results, as well as the test problems, revealed that the proposed approach can obtain several better solutions than those obtained by the Original optimization approach when the number of iterations of additional sampling was the same between both approaches. The hypervolume in the proposed approach also increases more rapidly than that in the Original optimization approach.

著者

後藤 駿 金崎 雅博 村山 光宏 伊藤 靖 山本 一臣 Goto Shun Kanazaki Masahiro Murayama Mitsuhiro Ito Yasushi Yamamoto Kazuomi

出版者

宇宙航空研究開発機構(JAXA)

雑誌

宇宙航空研究開発機構特別資料: 第48回流体力学講演会/第34回航空宇宙数値シミュレーション技術シンポジウム論文集 = JAXA Special Publication: Proceedings of the 48th Fluid Dynamics Conference / the 34th Aerospace Numerical Simulation Symposium (ISSN:1349113X)

巻号頁・発行日

vol.JAXA-SP-16-007, pp.189-194, 2016-12-27

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第48回流体力学講演会/第34回航空宇宙数値シミュレーション技術シンポジウム (2016年7月6日-8日. 金沢歌劇座), 金沢市, 石川

著者

金崎 雅博 四谷 智義 奈良 拓矢 松島 紀佐

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.59, no.684, pp.24-26, 2011 (Released:2011-03-03)

参考文献数

4

被引用文献数

1

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The original PARSEC (PARametric SECtion) method can satisfactorily solve the optimization problems involving transonic airfoils by using a few design variables. However, it is difficult to apply this method to the design of airfoils under other conditions such as supersonic flow and low Reynolds number flow. To solve various airfoil design problems by using a few design variables and the PARSEC representation, a modified PARSEC representation is proposed. The capability of the proposed modified representation to solve unknown real-world design problems is investigated; the proposed representation is used along with multi-objective genetic algorithms to solve two types of problems. One is the design of a conventional transonic airfoil that is to be used in the Earth's atmosphere; the other is the design of an airfoil that is to be used in the Martian atmosphere. To evaluate the aerodynamic performance of the airfoils, the structured Navier-Stokes solver is used. The results indicate that better solutions can be obtained by using the proposed PARSEC modification than by using the original PARSEC representation, especially in the Martian atmosphere.

著者

金崎 雅博 奈良 拓矢 四谷 智義

出版者

日本計算工学会

雑誌

計算工学講演会論文集 (ISSN:1342145X)

巻号頁・発行日

no.15, 2010-05

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In this paper, airfoil geometry representation is proposed for the efficient design optimization and the knowledge discovery. Here, PARSEC airfoil representation is improved with several modifications. To investigate the possibility to solve the unknown real-world design problem, two type airfoil geometries is considered using genetic algorithms. One is a conventional transonic airfoil in the Earth atmosphere, the other is a airfoil which can be used in Martian atmosphere To evaluate the aerodynamic performance, the structured Navier-Stokes solver with Baldwin-Lomax turbulent model is used. According to this result, the proposed airfoil representation method can generate the airfoil geometry which achieves high aerodynamic performance as same as NURBS representation. These results suggest that the proposed method can useful for the design exploration methods which include data mining, because the airfoil geometry can be defined with the design variables which show aerodynamic performance directly.

著者

四谷 智義 金崎 雅博

出版者

一般社団法人 日本機械学会

雑誌

設計工学・システム部門講演会講演論文集 2010.20 (ISSN:24243078)

巻号頁・発行日

pp._1405-1_-_1405-6_, 2010-10-27 (Released:2017-06-19)

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In this research, modified PARSEC airfoil representations are developed and they are investigated by the design exploration of airfoils for the Mars airplane. The existent PARSEC airfoil representation method is useful for the aerodynamic optimization and the knowledge discovery, because the original PARSEC airfoil is parameterized based on the aerodynamic theory. In this method, designer can directly define airfoil's parameters, the leading edge radius, the maximum thickness, the maximum camber, and so on, However, the original PARSEC representation cannot use for not subsonic flow (supersonic flow, low Reynolds number flow), because it was parameterized in consideration of a subsonic wing. To solve the several airfoil design problem, modified representation method is constructed and its design performance is investigated by solving multi-objective design problem. This study employs Genetic Algorithm (GA) for exploration of the multi-objective problem. Flowfield is solved by the structured Navier-Stokes solver with Baldwin-Lomax turbulent model. According to these results, the modified airfoil representation method can solve the design problem under the Martian atmosphere better than the original method.

著者

竹内 和也 松島 紀佐 金崎 雅博 楠瀬 一洋

出版者

一般社団法人 日本機械学会

雑誌

日本機械学会論文集 (ISSN:21879761)

巻号頁・発行日

vol.81, no.827, pp.15-00037, 2015 (Released:2015-07-25)

参考文献数

9

被引用文献数

3 3

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To systematically investigate the aerodynamic characteristics of wings with 30, 45 and 60 degree swept-back angles, and different taper ratios, Navier-Stokes (N-S) simulations for flows over a wing have been conducted. The Mach numbers of the flows range from 0.8 to 2.8. The planforms of wings are in various shapes whose half span aspect ratios are identically fixed in 2.0. The simulation and investigation has revealed new knowledge on the relation between swept-back angles and aerodynamic characteristics of a wing in a supersonic flow. As the aerodynamic characteristics, drag coefficient CD variation is primarily observed along flow Mach number increase. Results of N-S simulations show a realistic profile of the variation which is substantially different from that by the thin-wing theory commonly printed in a textbook. Moreover, the simulation results indicate not only the swept-back angle of a leading edge but also that of a trailing edge take important role on aerodynamics of a wing. Finely, the effect of drag coefficients induced by lift is analyzed using simulation results. It is found that the induced drag in realistic supersonic flows can be treated by the thin-wing theory if three-dimensionality is properly evaluated.