受賞区分：国内学会・会議・シンポジウム等の賞  受賞国：日本国

受賞国：アメリカ合衆国

記述言語：日本語   出版者・発行元：一般社団法人 日本機械学会  

DOI： 10.1299/jsmemag.126.1257_41

CiNii Research

記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）   出版者・発行元：American Institute of Aeronautics and Astronautics  

DOI： 10.2514/6.2023-2407

記述言語：英語   掲載種別：研究論文（学術雑誌）   出版者・発行元：American Institute of Aeronautics and Astronautics (AIAA)  

<jats:p> In this paper, an efficient aeroelastic model for morphing structures with corrugated panels is proposed, combining different fidelities of aerodynamic models. A finite element method with an actuation model is used to analyze the structural deformation of morphing structures. A vortex lattice method and Cartesian-grid-based computational fluid dynamics are individually coupled with the structural model to build the medium- and high-fidelity aeroelastic models. Three different morphing cases are simulated with the two fidelities of aeroelastic models to understand the influence of the model fidelity on the simulation results. Based on the comparison study, a new efficient aeroelastic model is proposed where the medium-fidelity aeroelastic model speeds up the calculations in the aeroelastic loop and the high-fidelity aeroelastic model computes accurate aerodynamic characteristics and necessary actuation loads. Computational time of the proposed method is half of the high-fidelity model while maintaining the computational accuracy. </jats:p>

DOI： 10.2514/1.C036692

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記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）   出版者・発行元：Proceedings of ASME 2023 Aerospace Structures, Structural Dynamics, and Materials Conference, SSDM 2023  

Morphing technology has been intensively studied in the last decades. Camber morphing is one of the most popular and effective types of morphing, and its aerodynamic advantages have been demonstrated. Although its aeroelasticity has been studied in previous research, the coupling between its aeroelasticity and the flight dynamics of the overall aircraft has not been investigated well. This study aims to understand the influence of the aeroelasticity of morphing control surfaces on the flight dynamics of the aircraft. For this objective, an aeroelastic flight simulation framework that can consider camber morphing is developed. For the structural model, finite shell elements are used to capture the behavior of the camber morphing structures. For aerodynamics, an unsteady vortex lattice method is used to estimate the unsteady aerodynamic loads efficiently. A rigid-body flight dynamics is coupled with the structural and aerodynamic model to construct the aeroelastic flight simulation framework. The flight motions of the aircraft with morphing elevators are simulated under open-loop control. The results demonstrated that the aeroelastic response of morphing elevators differs depending on the stiffness of the morphing structure. It is also shown that this leads to the different gusts that the aircraft with morphing elevator experiences severe altitude changes.

DOI： 10.1115/ssdm2023-106523

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担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）   出版者・発行元：AIAA SciTech Forum and Exposition, 2023  

Mechanical metamaterials are artificially manufactured materials with properties, which cannot be obtained from natural materials, consisting of deliberately designed microscopic internal structures. Those conceptual artificial materials are ready to fabricate with the advent of additive manufacturing technology. Recently, a class of metamaterials has been actively studied due to its potential for performance improvements and extensions of structural capabilities. Mechanical metamaterials can exhibit exotic material characteristics and/or macroscopic behaviors attributed to their micro/mesoscale internal structural designs such as truss or porous in μm/mm order in addition to material properties constructing the structural components. Mechanical metamaterials with unique properties and capabilities of vibration suppression/isolation are hoped to realize high-performance structures. In this paper, the dispersion characteristics of wave propagation in lattice-based mechanical metamaterials for vibration suppression will be studied. The objectives of this paper are 1) to develop an analysis framework, which enables effective dispersion analysis to design mechanical metamaterials, 2) to study dispersion characteristics of wave propagation in lattice-based mechanical metamaterials, and 3) to explore the feasibility and potential of lattice-based mechanical metamaterials for vibration suppression with an experimental approach. To efficiently evaluate the dispersion characteristics of waves in lattice-based mechanical metamaterials, a finite element approach with Floquet-Bloch’s principles is implemented. A unit cell of the periodically distributed structure is modeled as representative finite elements, and the wave dispersion properties of the unit cell are calculated with the analysis framework. Furthermore, the calculated dispersion characteristics are verified by both numerical analysis and experimental approaches. The triangular lattice structures demonstrated the potential as vibration-restraining structures by numerical and experimental evaluations.

DOI： 10.2514/6.2023-2575

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記述言語：日本語   出版者・発行元：一般社団法人 日本機械学会  

<p>Fatigue properties of an additively manufactured metal lattice structure were experimentally investigated. Fatigue specimens that have a lattice structure in their gauge section were manufactured using an aluminum alloy, AlSi10Mg, by selective laser melting powder bed fusion. The lattice structure consisted of simple cubic unit cells. Fatigue tests at room temperature in air were conducted under load control conditions with a frequency of 10 Hz and a load ratio of <i>R</i> = 0.1 (tension-tension) or <i>R</i> = 10 (compression-compression). The following achievements are reported in this manuscript: demonstrating the specimens and the testing methods; collecting basic fatigue data; understanding fundamental mechanisms of deformation and failure; evaluating an applicability of a conventional fatigue life prediction law.</p>

DOI： 10.1299/jsmemm.2023.mm1306

CiNii Research

担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（学術雑誌）   出版者・発行元：Materials Today Communications  

The authors regret errors in the published paper and has updated Tables 1–3 as below: 1. The Table 1 should be modified to: [Table presented] 2. The Table 2 should be modified to: [Table presented] 3. The Table 3 should be modified to: [Table presented] The authors would like to apologise for any inconvenience caused.

DOI： 10.1016/j.mtcomm.2022.104336

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記述言語：英語   掲載種別：研究論文（学術雑誌）   出版者・発行元：International Journal of Aeronautical and Space Sciences  

Aeroservoelastic characteristics of a morphing control surface with corrugated structures are investigated in this paper. The finite element structural model and the aerodynamic model with an unsteady vortex lattice method are used to analyze the aeroelastic response of a corrugated morphing control surface. The equation of motion for the corrugated morphing control surface is derived in the state-space form, and a classic LQR control technique is integrated to function the morphing structures as control surfaces. Considering the structural and control design parameters, the aeroservoelastic response of corrugated morphing control surfaces under continuous gusts is analyzed. Simulation results demonstrate that the flexible design of corrugations may lead to undesirable vibrations even with actuation control. It is also shown that the structural modes which play important roles in the lift control can change according to the structural design parameters. This work provides important insights into designing a morphing control surface with flexible structures such as corrugated structures.

DOI： 10.1007/s42405-022-00474-3

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出版者・発行元：Materials Today Communications  

There is an emerging class of artificial materials, so-called mechanical metamaterials. By deliberately designing microscopic internal mechanisms, these materials exhibit exotic properties, which distinguish the mechanical metamaterials from natural materials. As additive manufacturing technology has been rapidly developed and its manufacturing quality has been improved, those conceptual artificial materials are ready to fabricate. This paper presents a decoupled two-scale analysis framework to efficiently evaluate the stiffness and strength characteristics of lattice-based mechanical metamaterials. Structural characteristics of lattice-based mechanical metamaterials are effectively captured by accommodating a computational homogenization method to lattice-based structures. In the computational homogenization procedure, a unit cell of the periodically distributed structure is modeled as representative finite elements. Equivalent stiffness properties of the unit cell are calculated based on the computational homogenization procedure. The equivalent structural properties are then used to perform macroscopic structural analysis of lattice-based structures in an effective manner. Similarly, a local/microscopic stress distribution within the periodic lattice unit cell is recovered by transforming macroscopic sectional loads, which are obtained from the macroscopic structural analysis, through a stress amplification matrix. The microscopic stress distribution obtained with the two-scale analysis can be used for strength evaluation. Subsequently, numerical results are validated by comparing them with experimental results providing actual behaviors of lattice-based mechanical metamaterials. This work presents the novel use of the multi-scale analysis scheme combining the computational homogenization method and the stress field transformation method enabling structural evaluations to design mechanical metamaterials with structural integrity. This study also demonstrates the feasibility and capability of the presented approach to effectively predict stiffness and strength characteristics of lattice-based structures.

DOI： 10.1016/j.mtcomm.2022.103598

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担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（学術雑誌）   出版者・発行元：Journal of Sound and Vibration  

In this paper, an aeroelastic framework developed in the previous works has been extended for a geometrically nonlinear aeroelastic stability analysis. In the aeroelastic stability analysis, modal mass and stiffness matrices are constructed using shell finite elements with the corotational approach, which can take into account the geometric stiffening under large deformations. A generalized aerodynamic force matrix is derived by accommodating the unsteady vortex-lattice method based on a modal approach. The derived modal aeroelastic equations are solved using the p-k method. Individual modules to calculate generalized structural matrices with the corotational approach and aerodynamic forces based on the unsteady vortex-lattice method are verified. The present geometrically nonlinear aeroelastic framework for aeroelastic stability analysis is also validated in a comparison with an experimental result in the flutter wind tunnel test showing a reasonable accuracy for a prediction of flutter speed, while there still is room for further improvement in the estimation of flutter frequency. In addition, the present method allows studying the flutter characteristics of flexible wings with different incident angles, which cannot be evaluated by traditional linear flutter simulations. Finally, effects of geometric nonlinearity and large deformation on flutter characteristics of flexible and high-aspect-ratio wings were explored by using the present method. The present method can help to understand aeroelastic stability characteristics for such high-aspect-ratio wings.

DOI： 10.1016/j.jsv.2021.116621

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担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（大学，研究機関等紀要）   出版者・発行元：Japan Aerospace Exploration Agency  

DOI： 10.20637/00048265

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記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）   出版者・発行元：AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022  

In this study, transient aeroelastic behaviors of corrugated morphing wings in a prescribed flight path are investigated. A simulation framework for the wings with corrugated control surfaces is developed. A shell finite element is used to model the composite corrugated morphing wings, and the mechanical properties of corrugations are homogenized to implement in the structural model. An unsteady vortex lattice method (UVLM) is coupled with the structural model to simulate the aeroelastic behaviors of the morphing wings. The prescribed 1-cos plunge motion is forced with corrugated morphing wings with different configurations, and the transient aeroelastic responses are analyzed. The simulation results demonstrate that the morphing structures passively reduce the influences of the plunge motion.

DOI： 10.2514/6.2022-0242

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担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（学術雑誌）   出版者・発行元：Elsevier BV  

DOI： 10.1016/j.ast.2021.106923

担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（学術雑誌）   出版者・発行元：MDPI AG  

<jats:p>Additive manufacturing (AM) technology has a potential to improve manufacturing costs and may help to achieve high-performance aerospace structures. One of the application candidates would be a wind tunnel wing model. A wing tunnel model requires sophisticated designs and precise fabrications for accurate experiments, which frequently increase manufacturing costs. A flutter wind tunnel testing, especially, requires a significant cost due to strict requirements in terms of structural and aeroelastic characteristics avoiding structural failures and producing a flutter within the wind tunnel test environment. The additive manufacturing technique may help to reduce the expensive testing cost and allows investigation of aeroelastic characteristics of new designs in aerospace structures as needed. In this paper, a metal wing model made with the additive manufacturing technique for a transonic flutter test is studied. Structural/aeroelastic characteristics of an additively manufactured wing model are evaluated numerically and experimentally. The transonic wind tunnel experiment demonstrated the feasibility of the metal AM-based wings in a transonic flutter wind tunnel testing showing the capability to provide reliable experimental data, which was consistent with numerical solutions.</jats:p>

DOI： 10.3390/aerospace8080200

CiNii Research

出版者・発行元：American Institute of Aeronautics and Astronautics  

DOI： 10.2514/6.2021-0953

CiNii Research

記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

担当区分：筆頭著者,　最終著者,　責任著者   記述言語：日本語   掲載種別：研究論文（学術雑誌）   出版者・発行元：一般社団法人 日本航空宇宙学会  

<p>In this paper, a new multi-fidelity aeroelastic framework for highly flexible wings is proposed. A corotational approach with a shell finite element is used to consider the geometrical nonlinearity produced by flexible wings. An unsteady vortex-lattice aerodynamic method and a fast unstructured CFD code are coupled with the structural model subject to the large deformations, providing different fidelity solutions. The developed geometrically nonlinear aeroelastic solutions with different fidelities are compared to evaluate accuracies and computational efficiencies. </p>

DOI： 10.2322/jjsass.68.142

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担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

出版者・発行元：American Institute of Aeronautics and Astronautics  

DOI： 10.2514/6.2020-2189

CiNii Research

担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

DOI： 10.2514/6.2020-0450

担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

担当区分：筆頭著者,　最終著者,　責任著者   記述言語：日本語   掲載種別：研究論文（学術雑誌）   出版者・発行元：一般社団法人 日本機械学会  

<p>Various high-performance structures are ready to fabricate with the advent of the technology for the additive manufacturing. This additive manufacturing technology has a potential to improve manufacturing costs and may help to achieve high-performance aerospace structures. One of application candidates would be a wind tunnel wing model. A wing tunnel model requires sophisticated designs and precise fabrications for accurate experiments, which frequently increase manufacturing cost. At the same time, there are design trends of high aspect ratio wings to enhance flight performance of aircraft. Those wings may undergo large deformation during flights. Therefore, a geometrically nonlinear aeroelastic analysis of such flexible wings plays important role in design. In this paper, manufacturing accuracy and aeroelastic characteristics of an additively manufactured wing model are evaluated numerically and experimentally. The feasibility of such wings to use in wind tunnel tests is also demonstrated. In addition, a geometrically nonlinear aeroelastic analysis model, which have been developed in the previous study, is validated by comparing with results of the wind tunnel test for the additively manufactured highly flexible wing model. The effect of geometrical nonlinearity in aeroelastic characteristics of a highly flexible wing has been observed in the comparison between linear and nonlinear aeroelastic solutions and the wind tunnel result.</p>

DOI： 10.1299/transjsme.19-00452

CiNii Research

記述言語：日本語   出版者・発行元：一般社団法人 日本機械学会  

<p>The additive manufacturing technology has a potential to improve manufacturing costs and may help to achieve high-performance aerospace structures. One of application candidates would be a wind tunnel wing model. A wind tunnel model requires sophisticated designs and precise fabrications for accurate experiments, which frequently increase manufacturing cost. The additive manufacturing technique may help to reduce the expensive testing cost and allow us to investigate aeroelastic characteristics of new designs of aerospace structures as many as we need. In this paper, metal wing models with the additive manufacturing technique for a flutter test has been studied. Structural/aeroelastic characteristics of additively manufactured wing models are evaluated numerically and experimentally.</p>

DOI： 10.1299/jsmetld.2020.29.2002

CiNii Research

担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（学術雑誌）   出版者・発行元：ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER  

DOI： 10.1016/j.ast.2019.03.025

担当区分：筆頭著者,　最終著者,　責任著者   記述言語：日本語   掲載種別：研究論文（学術雑誌）   出版者・発行元：一般社団法人 日本機械学会  

<p>In this paper, a flexible morphing wing with piezoelectric materials for morphing actuation is studied. The objectives of this paper are 1) to develop an integrated geometrically nonlinear electro-aeroelastic framework, which allows evaluating performances of flexible morphing wings with piezoelectric actuators, 2) to validate the developed analysis framework, and 3) to demonstrate the capability of the framework and explore the performance. This paper provides a description of the electro-aeroelastic equations of morphing wings taking into account piezoelectric effects, which can be used to actuate morphing wings. The electro-mechanical model is validated by comparing with experimental results. The validation with a single macro fiber composite showed a very good agreement between the experimental result and the simulation. The result of an actuation test with an integrated corrugated structure and macro fiber composite also reasonably agreed with the solution from the present code. Aeroelastic behaviors of a corrugated wing with the piezoelectric actuator are then explored. The camber morphing wing with the corrugated structure actuated by the piezoelectric actuator could provide a larger lift in the vicinity of the trailing edge. Such a camber morphing has a good potential to control aeroelastic response by wing morphing with piezoelectric actuation.</p>

DOI： 10.1299/transjsme.18-00506

CiNii Research

担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（学術雑誌）   出版者・発行元：一般社団法人 日本機械学会  

<p>Morphing aircraft technology has recently gained attention of many research groups by its potential for aircraft performance improvement and economic flight. Although the performance of conventional control surfaces is usually compromised in off-design flight conditions, the morphing technique may achieve optimal flight performance in various operations by to adaptively altering the wing shape during flight. This paper aims to provide a comprehensive review on morphing aircraft/wing technology, including morphing mechanisms or structures, skins, and actuation techniques as element technologies. Moreover, experimental and numerical studies on morphing technologies applying those elemental technologies are also introduced. Recent research on these technologies are particularly focused on in this paper with comparisons between developments in Japan and other countries. Although a number of experimental and numerical studies have been conducted by various research groups, there are still various challenges to overcome in individual elemental technologies for a whole morphing aircraft or wing systems. This review helps for researchers working in the field related to morphing aircraft technology to sort out current developments for morphing aircraft.</p>

DOI： 10.1299/mer.19-00197

CiNii Research

担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）   出版者・発行元：American Institute of Aeronautics and Astronautics  

DOI： 10.2514/6.2019-0219

CiNii Research

記述言語：日本語   出版者・発行元：一般社団法人 日本機械学会  

<p>Various high-performance structures are ready to fabricate with the advent of the technology for the additive manufacturing. This additive manufacturing technology has a potential to improve manufacturing costs and may help to achieve high-performance aerospace structures. One of application candidates would be a wind tunnel wing model. A wing tunnel model requires sophisticated designs and precise fabrications for accurate experiments, which frequently increase manufacturing cost. In this paper, manufacturing accuracy and aeroelastic characteristics of an additively manufactured wing model are presented. The feasibility of such wings to use in wind tunnel tests is also demonstrated.</p>

DOI： 10.1299/jsmetld.2019.28.1007

CiNii Research

記述言語：日本語   出版者・発行元：一般社団法人 日本機械学会  

<p>Morphing technologies are attracting much attention as breakthrough technologies to improve the performance of aircrafts. Structural designing of morphing wings is one of the important challenges and corrugated panels are regarded as promising candidate materials for morphing wings. In this paper, designs of corrugated morphing wings for drag reduction are studied considering necessary actuation forces. Static aeroelastic models are constructed to assess the aerodynamic performances or deformations of morphing wings, and aeroelastic analyses are performed with multiple parameter settings. An objective function considering the drag coefficient and the necessary actuation force is prepared and the performance of each case is analyzed. Numerical results show that there is a desirable design parameter or actuation when the two evaluation components are considered at the same time.</p>

DOI： 10.1299/jsmetld.2019.28.1008

CiNii Research

記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.1016/j.polymer.2018.07.005

担当区分：筆頭著者,　最終著者,　責任著者   記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

担当区分：筆頭著者,　責任著者   記述言語：英語   掲載種別：研究論文（学術雑誌）   出版者・発行元：Elsevier {BV}  

DOI： 10.1016/j.ast.2018.05.056

記述言語：日本語   出版者・発行元：一般社団法人 日本機械学会  

In this paper, a flexible morphing wing with piezoelectric materials for morphing actuation is studied. It provides a description of the electro-aeroelastic equations of morphing wings taking into account piezoelectric effects, which can be used to actuate morphing wings. The electro-mechanical model is validated by comparing with experimental results. The actuation of rectangular corrugated wing for camber morphing is also verified. Aeroelastic behaviors of a corrugated wing with the piezoelectric actuator are also explored.

DOI： 10.1299/jsmetld.2018.27.1005

CiNii Research

記述言語：日本語   出版者・発行元：一般社団法人 日本機械学会  

To improve the fuel efficiency, commercial aircraft has recently had high aspect ratio wing. However, it increases the wing root bending moment and reduces the performance of wing strength. As a solution to this issue, adaptive wing structures are proposed. The adaptive wing means a wing which can change its shape in flight. The previous research shows that wing root bending moment can be decreased by using adaptive wing structures, but many analysis cases are needed for optimization of the wing root bending moment. This study focuses on the reduction of the high computational cost. A new method for Load Control using Superposition (LCS method) is suggested. By comparing the analysis result of LCS method with that of MSC/NASTRAN, the LCS method are verified. In addition, the LCS method is compared with geometrically nonlinear aeroelastic analysis to evaluate its accuracy for large deflection cases. The large flap angle causes the geometrically nonlinear effect, so it is suggested that the LCS method works only in range of about 10 degrees of flap angles.

DOI： 10.1299/jsmetld.2018.27.1007

CiNii Research

担当区分：筆頭著者   記述言語：英語   掲載種別：研究論文（学術雑誌）   出版者・発行元：ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER  

DOI： 10.1016/j.ast.2017.09.026

担当区分：筆頭著者   記述言語：英語   掲載種別：学位論文（博士）  

担当区分：筆頭著者   記述言語：英語   掲載種別：研究論文（学術雑誌）   出版者・発行元：ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER  

DOI： 10.1016/j.ast.2017.02.013

担当区分：筆頭著者   記述言語：英語   掲載種別：研究論文（学術雑誌）   出版者・発行元：AMER INST AERONAUTICS ASTRONAUTICS  

DOI： 10.2514/1.C033846

担当区分：筆頭著者   記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

DOI： 10.2514/6.2017-1126

担当区分：筆頭著者   記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

DOI： 10.2514/6.2017-0624

担当区分：筆頭著者   記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

担当区分：筆頭著者   記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）  

担当区分：筆頭著者   記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）   出版者・発行元：AMER INST AERONAUTICS ASTRONAUTICS  

DOI： 10.2514/6.2015-0444

開催年月日： 2023年

記述言語：英語   会議種別：口頭発表（招待・特別）  

開催地：東京   国名：日本国  

開催年月日： 2022年

記述言語：英語   会議種別：口頭発表（招待・特別）  

開催地：Singapore   国名：シンガポール共和国  

開催年月日： 2021年5月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2021年3月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2021年1月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2021年1月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2020年11月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2020年11月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2020年11月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2020年9月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2020年8月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2020年8月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2020年8月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2020年5月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2020年5月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2020年5月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2020年3月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2020年1月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2020年1月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2020年1月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2020年1月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2019年11月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2019年11月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2019年11月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2019年11月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2019年11月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2019年10月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2019年9月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2019年8月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2019年8月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2019年7月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2019年6月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2019年5月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2019年3月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2019年1月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2019年

記述言語：日本語   会議種別：口頭発表（招待・特別）  

開催地：愛知県   国名：日本国  

開催年月日： 2018年12月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2018年12月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2018年11月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2018年9月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2018年8月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2018年8月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2018年7月

記述言語：日本語   会議種別：口頭発表（一般）  

開催年月日： 2018年

記述言語：日本語   会議種別：口頭発表（招待・特別）  

開催地：愛知県   国名：日本国  

開催年月日： 2018年

記述言語：英語   会議種別：口頭発表（招待・特別）  

開催地：India   国名：インド  

開催年月日： 2017年1月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2017年1月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2017年

記述言語：日本語   会議種別：口頭発表（招待・特別）  

開催地：大阪府   国名：日本国  

開催年月日： 2017年

記述言語：日本語   会議種別：口頭発表（招待・特別）  

開催地：大阪府   国名：日本国  

開催年月日： 2016年5月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2016年1月

記述言語：英語   会議種別：口頭発表（一般）  

開催年月日： 2015年1月

記述言語：英語   会議種別：口頭発表（一般）  

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