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1. 发明公开

EP3333738A1 STREAKLINE VISUALIZATION APPARATUS, METHOD, AND PROGRAM 审中-公开
公开(公告)号：EP3333738A1
公开(公告)日：2018-06-13
申请号：EP17203528.9
申请日：2017-11-24
申请人： FUJITSU LIMITED , The University Of Tokyo
发明人： Kushibe, Daisuke , Watanabe, Masahiro , Hisada, Toshiaki , Sugiura, Seiryo , Washio, Takumi , Okada, Jun-ichi
IPC分类号： G06F17/50
CPC分类号： A61B6/032 , A61B6/504 , A61B6/507 , A61B6/5217 , G06F17/5009 , G06F17/5095 , G06F2217/16 , G06F2217/46 , G06T7/0016 , G06T2207/30104 , Y02T90/50
摘要： In a streakline visualization apparatus, a processing unit calculates, by using an expression including a correction value for correcting an error attributable to accelerated motion of a plurality of grid points represented by position information, time differential values of velocities of fluid on the plurality of grid points at each of the plurality of first time points. The processing unit calculates, based on the velocities and the time differential values of the velocities of the fluid on the plurality of grid points at each of the plurality of first time points, positions of a series of a plurality of particles sequentially outputted from a particle generation source as analysis time progresses at each of a plurality of second time points having a second time interval shorter than the first time interval. The processing unit generates display information about a streakline indicating the series of the plurality of particles.

2. 发明公开

EP3276514A1 PROCEDE D OPTIMISATION DES SECTIONS D'UNE POUTRE DE QUEUE DESTINEE A UN AERONEF A VOILURE TOURNANTE 有权
标题翻译：一种用于旋转转向飞机的尾梁优化方法
公开(公告)号：EP3276514A1
公开(公告)日：2018-01-31
申请号：EP17183214.0
申请日：2017-07-26
申请人： Airbus Helicopters
发明人： ALFANO, David , LEGRAS, Guillaume , LEUSINK, Debbie
IPC分类号： G06F17/50 , B64C1/00 , B64C27/82
CPC分类号： B64C27/82 , B64C1/0009 , B64C27/06 , B64F5/00 , G06F17/5009 , G06F2217/46 , Y02T90/50
摘要： La présente invention concerne un procédé d'optimisation des sections d'une poutre de queue (10) destinée à un aéronef à voilure tournante ainsi qu'une poutre de queue (10) comportant de telles sections. Ledit procédé comporte une étape de création d'une base de données caractérisant des sections standards d'une poutre de queue (10) privilégiant la diminution d'une déportance F D et/ou l'augmentation d'une force latérale F L générées par le flux d'air d'un rotor principal dudit aéronef circulant sur ladite poutre de queue (10), une étape d'établissement de caractéristiques aérodynamiques et structurelles recherchées de ladite poutre de queue (10) et une étape de définition desdites sections de ladite poutre de queue (10) en fonction desdites sections standards et desdites caractéristiques aérodynamiques et structurelles recherchées. La poutre de queue (10) ainsi définie optimise la diminution de la déportance F D et/ou l'augmentation de la force latérale F L générées par ledit flux d'air dudit rotor principal.
摘要翻译：本发明涉及一种用于优化用于旋翼飞机的尾梁（10）和具有这些部分的尾梁（10）的区段的方法。所述方法包括创建有利于减小由流动所产生的横向力FL的下压力FD和/或扩展的数据库表征标准尾梁部（10）的步骤的主转子的空气所述飞机上行进，所述尾架（10），建立所要求的空气动力和结构特征的所述步骤尾梁（10）和所述光束的所述部分的定义步骤根据所述标准部分和所述期望的空气动力学和结构特征来确定尾部（10）。尾梁（10）和限定优化所述空气流FD的下压力和/或增加所产生的横向力FL从所述主转子下降。

3. 发明公开

EP3336729A1 COMPUTER-AIDED METHOD AND SYSTEM FOR A QUICK PREDICTION OF VORTEX TRAJECTORIES ON AIRCRAFT COMPONENTS CHECKING HIGH PRESSURE GRADIENTS AND HIGH DRAG FRICTION COEFFICIENTS 审中-公开
公开(公告)号：EP3336729A1
公开(公告)日：2018-06-20
申请号：EP16382604.3
申请日：2016-12-15
申请人： Airbus Operations, S.L.
发明人： VINHA, Nuno , VALLESPIN FONTCUBERTA, David , DE PABLO FOUCE, Valentín , VALERO, Eusebio
IPC分类号： G06F17/50
CPC分类号： G06F17/5095 , G06F17/5009 , G06F17/5018 , G06F17/5086 , G06F2217/16 , Y02T90/50
摘要： The invention provides a computer-aided method suitable for assisting in the design of an object zone such as a CROR engine of an aircraft subjected to high vorticity and/or low static pressure fields when moving inside a flow field by providing suitable seed points for constructing vortex core lines in a fluid data model of the environment of said object zone and a system based in said method. The method steps are: a) Obtaining a dataset of candidate seeds containing all the cells or points satisfying a condition of the pressure gradient in the direction of the flow or a condition of the drag friction coefficient at the solid boundaries; b) Updating the previous dataset of candidate seeds with all the cells or points satisfying the equation not used for obtaining the dataset in step a).

4. 发明公开

EP2832465A1 PRESS-FORMING ANALYSIS METHOD 失效
标题翻译： PRESSFORMUNGSANALYSEVERFAHREN
公开(公告)号：EP2832465A1
公开(公告)日：2015-02-04
申请号：EP13768492.4
申请日：2013-03-04
申请人： JFE Steel Corporation
发明人： MINOTE, Toru , TOKITA, Yuichi , TAMAI, Yoshikiyo , URABE, Masaki , FUJITA, Takeshi
IPC分类号： B21D22/00 , B21D22/20 , B21D53/88
CPC分类号： G01B5/20 , B21D22/208 , B21D53/88 , G01N19/08 , G01N25/72 , G06F17/5018 , G06F17/5095 , G06F2217/41 , G06F2217/42 , G06F2217/44 , G06F2217/46 , Y02T90/50
摘要： A press-forming analysis method according to the present invention includes a step of analyzing press forming (S1) including setting an initial temperature distribution to a heated press-forming metallic sheet, and acquiring shape information, a temperature distribution, a stress distribution, and a strain distribution before mold release, in which a temperature analysis and a structural analysis are coupled; a step of analyzing springback (S3) including conducting a springback analysis based on the shape information, the temperature distribution, the stress distribution, and the strain distribution acquired at the step of analyzing press forming, and acquiring shape information, a temperature distribution, a stress distribution, and a strain distribution after springback; and a step of analyzing cooling stress (S5) including restraining particular nodes based on the shape information, the temperature distribution, the stress distribution, and the strain distribution acquired at the step of analyzing springback, and analyzing stress distributions during cooling and after the cooling by coupling a temperature analysis and a structural analysis.
摘要翻译：根据本发明的压制成形分析方法包括分析压制成形（S1）的步骤，包括将初始温度分布设定到加热的压制成形金属板，获取形状信息，温度分布，应力分布和脱模之前的应变分布，其中温度分析和结构分析耦合; 分析回弹（S3）的步骤，包括基于在分析压制成型步骤中获取的形状信息，温度分布，应力分布和应变分布进行回弹分析，并获取形状信息，温度分布，应力分布和回弹后的应变分布; 以及基于在分析回弹的步骤中获取的形状信息，温度分布，应力分布和应变分布来分析冷却应力（S5）的步骤，包括约束特定节点，以及分析冷却期间和冷却后的应力分布通过耦合温度分析和结构分析。

5. 发明授权

EP2983099B1 METHOD FOR DETERMINING REDUCTION FACTOR OF AXIAL LOAD BEARING CAPACITY OF A CYLINDRICAL SHELL STRUCTURE IN A ROCKET 有权
公开(公告)号：EP2983099B1
公开(公告)日：2018-11-28
申请号：EP14779155.2
申请日：2014-02-12
申请人： Dalian University of Technology
发明人： WANG, Bo , HAO, Peng , LI, Gang , TIAN, Kuo , MENG, Zeng , DU, Kaifan , ZHOU, Yan , ZHANG, Xi , TANG, Xiaohan , WANG, Bin , LUO, Hongzhi
IPC分类号： G06F17/50 , B64C1/06 , G01M99/00
CPC分类号： G01M99/007 , B64C1/068 , G06F17/5018 , G06F2217/16 , G06F2217/46 , Y02T90/50
摘要： A method for determining a reduction factor of a bearing capacity of an axial load cylindrical shell structure relates to stability checking of main bearing strength thin-walled members of aerospace and architectural structures. Different from experiment experience-based conventional defect sensitivity evaluating method represented by NASA SP-8007, a depression defect is introduced in a manner of applying a radial disturbance load. First, an influence rule of a depression defect amplitude of a single point to an axial load bearing capacity is analyzed by using numerical values, so as to determine a load amplitude range; then, defect sensitivity analysis is performed on depression defects of multiple points; then, experiment design sampling is performed by using load amplitude values and load position distribution as design variables; and finally, based on optimizing technologies such as an enumeration method, a genetic algorithm and a surrogate model, the most disadvantageous disturbance load of the multiple points that limits the defect amplitude is searched for, and a reduction factor of the bearing capacity of the axial load cylindrical shell structure is determined, so as to establish a more physical method for evaluating the defect sensitivity and the bearing performance of the axial load cylindrical shell structure.

6. 发明授权

EP2339486B1 Methods and systems for optimising the design of aerodynamic surfaces 有权
公开(公告)号：EP2339486B1
公开(公告)日：2018-08-01
申请号：EP10192955.2
申请日：2010-11-29
申请人： Airbus Operations S.L.
发明人： Redondo García, Daniel , De Bona Piedrabuena, Javier
IPC分类号： G06F17/50
CPC分类号： G06F17/5018 , G06F17/5095 , G06F2217/16 , Y02T90/50
摘要： Methods and systems for optimising the design of aerodynamic surfaces. They include in the design process of the aerodynamic surface of a body (41) which moves through a flow field, the following steps: a) preparation of a CFD simulation of said body (41); b) resolution of the CFD calculation for specific conditions of the flow field and for obtaining the flow lines (51) of the flow on said surface; c) calculation of at least one geometrical variable of the surface such as the normal curvature, according to the direction of said flow lines (51) and additionally at least one relevant variable of the aerodynamic flow, such as the pressure gradient; d) simultaneous visualisation of the surface of said body (41) and of at least one geometric variable and, additionally, said at least one variable of the aerodynamic flow.

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