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2014/6/3 特別講義御案内
2014年6月3日，金崎都市教養「航空機力学とペーパープレーン」にて，元Boeing社で研究開発に携わり，ご退職後，東北大学を経て現在JAXAにて客員研究員を努められる楠瀬先生による御講義を頂きます．
finland_japan_joint_seminor
This document describes using efficient global optimization applied to wind tunnel experiments to optimize flow control by plasma actuators. The optimization method uses a Kriging surrogate model and genetic algorithm to select additional sampling locations for wind tunnel runs to improve the model. Over 20 runs, it identified design variables that minimized drag for different plasma actuator configurations. Design A achieved the lowest drag by reducing flow separation with high duty cycle and modulation frequency settings. Design B also reduced drag with lower electrical energy requirements. The automated optimization successfully integrated wind tunnel experiments to efficiently optimize plasma actuator control parameters.
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非構造高速ソルバFaSTARを利用するための環境構築，実施事例（航空機フライトシミュレーションと降下経路最適化，火星探査航空機カプセル離脱時の展開シミュレーション，超音速航空機エンジン統合設計）について．
第２１回新生流体科学セミナー@宇宙航空研究開発機構(JAXA)
第２１回新生流体科学セミナー講演資料．@宇宙航空研究開発機構(JAXA)
私が保有する最適設計の手法と実践例を紹介．自動車エンジンマニフォールド～火星探査航空機翼型～プラズマアクチュエータの実験的最適あ
CJ爆轟パラメータの計算 / computaion of detonation parameters.
爆発セミナーの資料です。（4中4）
CJ爆轟パラメータの計算 / computaion of detonation parameters. について。
ハイブリッドロケットエンジンを用いたクラスタ型多段ロケットの設計＠ICFD2014
This document summarizes research on the design optimization of a launch vehicle concept using a clustered hybrid rocket engine for future space transportation. The researchers developed a design methodology for a launch vehicle with clustered hybrid rocket engines and investigated combinations of unit engines. Their objectives were to maximize payload to gross weight ratio and minimize gross weight. They defined four design cases and used multi-objective genetic algorithms and data visualization techniques to optimize the design variables. The results showed that a design with optimized engines for each stage performed best by avoiding excess unburnt fuel from shared engines across stages. Future work could further reduce unburnt fuel and improve payload ratio.
Multi-objective Genetic Algorithm Applied to Conceptual Design of Single-stag...
"Multi-objective Genetic Algorithm Applied to Conceptual Design of Single-stage Rocket Using Hybrid Propulsion System" presented at The Eighth China-Japan-Korea Joint Symposium on Optimization of Structural and Mechanical Systems (CJK-OSM).
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2014/6/3 特別講義御案内
2014年6月3日，金崎都市教養「航空機力学とペーパープレーン」にて，元Boeing社で研究開発に携わり，ご退職後，東北大学を経て現在JAXAにて客員研究員を努められる楠瀬先生による御講義を頂きます．
finland_japan_joint_seminor
This document describes using efficient global optimization applied to wind tunnel experiments to optimize flow control by plasma actuators. The optimization method uses a Kriging surrogate model and genetic algorithm to select additional sampling locations for wind tunnel runs to improve the model. Over 20 runs, it identified design variables that minimized drag for different plasma actuator configurations. Design A achieved the lowest drag by reducing flow separation with high duty cycle and modulation frequency settings. Design B also reduced drag with lower electrical energy requirements. The automated optimization successfully integrated wind tunnel experiments to efficiently optimize plasma actuator control parameters.
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非構造高速ソルバFaSTARを利用するための環境構築，実施事例（航空機フライトシミュレーションと降下経路最適化，火星探査航空機カプセル離脱時の展開シミュレーション，超音速航空機エンジン統合設計）について．
第２１回新生流体科学セミナー@宇宙航空研究開発機構(JAXA)
第２１回新生流体科学セミナー講演資料．@宇宙航空研究開発機構(JAXA)
私が保有する最適設計の手法と実践例を紹介．自動車エンジンマニフォールド～火星探査航空機翼型～プラズマアクチュエータの実験的最適あ
CJ爆轟パラメータの計算 / computaion of detonation parameters.
爆発セミナーの資料です。（4中4）
CJ爆轟パラメータの計算 / computaion of detonation parameters. について。
ハイブリッドロケットエンジンを用いたクラスタ型多段ロケットの設計＠ICFD2014
This document summarizes research on the design optimization of a launch vehicle concept using a clustered hybrid rocket engine for future space transportation. The researchers developed a design methodology for a launch vehicle with clustered hybrid rocket engines and investigated combinations of unit engines. Their objectives were to maximize payload to gross weight ratio and minimize gross weight. They defined four design cases and used multi-objective genetic algorithms and data visualization techniques to optimize the design variables. The results showed that a design with optimized engines for each stage performed best by avoiding excess unburnt fuel from shared engines across stages. Future work could further reduce unburnt fuel and improve payload ratio.
Multi-objective Genetic Algorithm Applied to Conceptual Design of Single-stag...
"Multi-objective Genetic Algorithm Applied to Conceptual Design of Single-stage Rocket Using Hybrid Propulsion System" presented at The Eighth China-Japan-Korea Joint Symposium on Optimization of Structural and Mechanical Systems (CJK-OSM).
火星探査ミッション検討・課題抽出プログラムへのお誘い【2018年度首都大】
平成３０年度に学部生を中心に，「学生主体の課題抽出を求める惑星探査を題材としたシステム統合技術者育成プログラム」（担当者：金崎，佐原）を実施することになりました．題材は惑星探査ですが，航空宇宙分野に限らず，システムインテグレーターとしてのエンジニアとなることを目指します．単位などにはなりませんが，少し進んだことを学んだり，ディスカッションを行ったり，皆さんのアイデアで研究開発を行ってみませんか？
Aerodynamic design of Aircraft”
Lecture on “Aerodynamic design of Aircraft” in University of Tokyo 21st December, 2015. Optimization techniques, data-visualization and their applications are inclusive.
Design of Novel Wing Body Considering Intake/Exhaust Effect
"Design of Novel Wing Body Considering Intake/Exhaust Effect" presented in APISAT-2013 at Takamatsu, Japan.
14/01/20 "Engineering Optimization in Aircraft Design" Aerodynamic Design at ...
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Lecture about design optimization, data mining, and real-world problems in aerospace engineering.
トリムを考慮した小型翼胴融合型旅客機の翼型空力設計
埴田 亮（首都大・院），村山光宏， 野村聡幸， 山本一臣，金崎雅博（首都大），「トリムを考慮した小型翼胴融合型旅客機の翼型空力設計」，日本航空宇宙学会北部支部2013年講演会，仙台2013年3月．
進化計算法を用いたハイブリッドロケットエンジン最適設計の試み
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1) The study aimed to perform multi-point aerodynamic design of a supersonic wing using an efficient global optimization methodology.
2) The methodology used a modified PARSEC airfoil representation and kriging model-based genetic algorithm for efficient global optimization.
3) The design explored maximizing lift-to-drag ratio at high and low Mach cruise speeds, finding many potential designs and discovering that camber of the kink and root airfoils most affected performance at high Mach while thickness curvature at kink and root did so at low Mach.
Multidisciplinary Design Optimization of Supersonic Transport Wing Using Surr...
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Multi-Disciplinary Conceptual Design of Multi-Stage Hybrid Rocket using Genet...
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Numerical Simulation: Flight Dynamic Stability Analysis Using Unstructured Ba...
The document summarizes a numerical simulation of flight dynamic stability analysis using an unstructured Navier-Stokes solver. It investigates the ability of computational fluid dynamics (CFD) to analyze dynamic stability at supersonic flight conditions. The study uses the Standard Dynamics Model configuration and estimates aerodynamic derivatives from computational results to analyze stiffness, damping, and unsteady oscillation characteristics. Grid dependency is also examined using coarse, medium, and fine meshes.
Vortex Dissipation Due to Airfoil-Vortex Interaction
1) A numerical simulation was conducted of airfoil-vortex interaction (AVI) for two airfoils to improve a hybrid method for predicting blade-vortex interaction (BVI) noise.
2) The simulation estimated the change in vortex center location and circulation due to sequential AVI. It found that the original vortex was decelerated and moved upward due to induced counter-rotating vortices from the first airfoil.
3) Sound pressure fluctuations were also estimated, finding that the pressure level after the second AVI was lower than after the first due to the increased miss-distance between the vortex and airfoil. This simulation provided data to modify the prescribed wake model used in the hybrid
Multidisciplinary and Multi-objective Design Exploration Methodology for Conc...
The document describes a study that developed an evaluation tool and used multi-objective genetic algorithms to explore the conceptual design of a hybrid rocket launch vehicle. The study aimed to evaluate launch vehicles with hybrid rocket engines and demonstrate multi-disciplinary design optimization. The design method involved using a genetic algorithm with Pareto ranking to optimize objectives of minimizing gross weight and maximizing flight altitude for a single-stage rocket carrying a 40kg payload. The results showed a tradeoff between weight and altitude, with a maximum altitude of around 180km found. One optimal design was compared to an existing solid-fuel rocket, showing the hybrid rocket design had a higher aspect ratio due to longitudinal component placement.
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火星探査ミッション検討・課題抽出プログラムへのお誘い【2018年度首都大】
平成３０年度に学部生を中心に，「学生主体の課題抽出を求める惑星探査を題材としたシステム統合技術者育成プログラム」（担当者：金崎，佐原）を実施することになりました．題材は惑星探査ですが，航空宇宙分野に限らず，システムインテグレーターとしてのエンジニアとなることを目指します．単位などにはなりませんが，少し進んだことを学んだり，ディスカッションを行ったり，皆さんのアイデアで研究開発を行ってみませんか？
Aerodynamic design of Aircraft”
Lecture on “Aerodynamic design of Aircraft” in University of Tokyo 21st December, 2015. Optimization techniques, data-visualization and their applications are inclusive.
Design of Novel Wing Body Considering Intake/Exhaust Effect
"Design of Novel Wing Body Considering Intake/Exhaust Effect" presented in APISAT-2013 at Takamatsu, Japan.
14/01/20 "Engineering Optimization in Aircraft Design" Aerodynamic Design at ...
Special lecture fot "Aerodynamic Design of Aircraft" at Univ. Tokyo, "Engineering Optimization in Aircraft Design."
Efficient Design Exploration for Civil Aircraft Using a Kriging-Based Genetic...
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Lecture about design optimization, data mining, and real-world problems in aerospace engineering.
トリムを考慮した小型翼胴融合型旅客機の翼型空力設計
埴田 亮（首都大・院），村山光宏， 野村聡幸， 山本一臣，金崎雅博（首都大），「トリムを考慮した小型翼胴融合型旅客機の翼型空力設計」，日本航空宇宙学会北部支部2013年講演会，仙台2013年3月．
進化計算法を用いたハイブリッドロケットエンジン最適設計の試み
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MULTI-POINT DESIGN OF A SUPERSONIC WING USING MODIFIED PARSEC AIRFOIL REPRESE...
1) The study aimed to perform multi-point aerodynamic design of a supersonic wing using an efficient global optimization methodology.
2) The methodology used a modified PARSEC airfoil representation and kriging model-based genetic algorithm for efficient global optimization.
3) The design explored maximizing lift-to-drag ratio at high and low Mach cruise speeds, finding many potential designs and discovering that camber of the kink and root airfoils most affected performance at high Mach while thickness curvature at kink and root did so at low Mach.
Multidisciplinary Design Optimization of Supersonic Transport Wing Using Surr...
The document summarizes research on the multidisciplinary design optimization of supersonic transport wing concepts. The objectives were to develop an efficient MDO tool for conceptual design of SST wings using low-cost computational fluid dynamics and surrogate modeling. 107 design samples were evaluated for aerodynamic performance, sonic boom levels, and wing weight. 24 non-dominated solutions were identified, with the best designs having thinner root airfoils, larger inboard sweep angles, or modified tail angles compared to a baseline compromised design. Analysis of variance identified key design variables with the most influence on objectives.
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Vortex Dissipation Due to Airfoil-Vortex Interaction
1) A numerical simulation was conducted of airfoil-vortex interaction (AVI) for two airfoils to improve a hybrid method for predicting blade-vortex interaction (BVI) noise.
2) The simulation estimated the change in vortex center location and circulation due to sequential AVI. It found that the original vortex was decelerated and moved upward due to induced counter-rotating vortices from the first airfoil.
3) Sound pressure fluctuations were also estimated, finding that the pressure level after the second AVI was lower than after the first due to the increased miss-distance between the vortex and airfoil. This simulation provided data to modify the prescribed wake model used in the hybrid
Multidisciplinary and Multi-objective Design Exploration Methodology for Conc...
The document describes a study that developed an evaluation tool and used multi-objective genetic algorithms to explore the conceptual design of a hybrid rocket launch vehicle. The study aimed to evaluate launch vehicles with hybrid rocket engines and demonstrate multi-disciplinary design optimization. The design method involved using a genetic algorithm with Pareto ranking to optimize objectives of minimizing gross weight and maximizing flight altitude for a single-stage rocket carrying a 40kg payload. The results showed a tradeoff between weight and altitude, with a maximum altitude of around 180km found. One optimal design was compared to an existing solid-fuel rocket, showing the hybrid rocket design had a higher aspect ratio due to longitudinal component placement.
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13 1015科学技術週間募集掲示
- 1. 2014年度科学技術週間 学生スタッフ募集！ 「科学技術週間」中に行われます，「Tokyoふしぎ祭エンス 2014」(2014/4/19-20の土日)で航空宇宙系企画を行いま す．事前～当日に手伝ってくれる学生スタッフを募集． イベントは子供向け，「紙飛行機の製作」，「簡易実験」，「RCに よる空撮大会」，などを検討中．他のアイデア募集． 12月~翌2月ごろから動き出しますが，既にクラウドを介してアイ デア出しから行っています．事前実験なども可能な限り御参加下 さい． 「Tokyoふしぎ祭エンス2012」 → http://www.fushigi2012.metro.tokyo.jp/ （少なくとも当日は）アルバイト代あり．待遇等は調整中． 「何か作りたい」「子どもたちと遊んで自分も勉強したい」と言った皆様，専門・学年 問わず募集します！(給料目的の人にはお勧めしません…)興味ある方，メール等 で金崎までご連絡ください． 金崎 雅博 航空宇宙システム工学コース e-mail: kana@sd.tmu.ac.jp website: www.sd.tmu.ac.jp/aerodesign twitter: twitter.com/Kanazaki_M 掲示期限：2014/1/31