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1. 发明专利

JP2014108781A Retractable equipment system including device optimized for driving protection flaps 有权
标题翻译：可回收设备系统，包括优化驱动保护措施的设备
公开(公告)号：JP2014108781A
公开(公告)日：2014-06-12
申请号：JP2013247669
申请日：2013-11-29
申请人： Airbus Operations Sas , エアバスオペラシオンソシエテパアクシオンスシンプリフィエ
发明人： MICHEL L HERITIER , ERIC DOUSTENS , PHILIPPE BOSC , PHILIPPE CASTAGNE
IPC分类号： B64D47/00 , B64D47/08
CPC分类号： B64C7/00 , B64D47/00 , B64D47/08 , G03B15/006
摘要： PROBLEM TO BE SOLVED: To optimize drive of protection flaps in a retractable equipment system for aircraft.SOLUTION: In a system 10 for retractable equipment that has movable protection flaps 38, a flap drive device 40 drives the flaps to optimally move while providing mechanical coupling between the flaps and the retractable equipment so that a common motor member 22, 24 can be used for driving both the equipment and the flaps. The drive device includes a cam 44 secured to a frame of the system and a cam follower 52 mechanically coupled to the retractable equipment 12 and to a flap drive member 72. The path followed by the retractable equipment is also optimized.
摘要翻译：要解决的问题：优化用于飞行器的可伸缩设备系统中的保护翼的驱动。解决方案：在具有可移动保护翼38的可伸缩设备的系统10中，翼片驱动装置40驱动翼片以最佳地移动，同时提供机械耦合在翼片和可伸缩设备之间，使得公共马达构件22,24可以用于驱动设备和翼片。驱动装置包括固定到系统的框架的凸轮44和机械地联接到可缩回的设备12和折翼驱动构件72的凸轮从动件52。还优化了可伸缩设备所遵循的路径。

2. 发明专利

JP2014050885A Frictional agitation welding improvement method and system for fixing reinforcing material to panel of airplane 有权
标题翻译：用于固定加固材料的机动焊接改进方法和系统
公开(公告)号：JP2014050885A
公开(公告)日：2014-03-20
申请号：JP2013183691
申请日：2013-09-05
申请人： Airbus Operations Sas , エアバスオペラシオンソシエテパアクシオンスシンプリフィエ
发明人： MIALHE CHRISTOPHE , PATRICK LIEVEN , ROMAIN DELAHAYE
IPC分类号： B23K20/12 , B64C1/12 , B64F5/00
CPC分类号： B23K20/122 , B23K20/1245 , B23K20/1255 , B23K20/126 , B23K20/1265
摘要： PROBLEM TO BE SOLVED: To improve a frictional agitation welding method and system for fixing a reinforcing material to a panel of an airplane.SOLUTION: The method is provided for executing linear permeation friction agitation welding FSW on a flange 26 of a reinforcing material 22 on at lease one panel 24 for the airplane. In the method, a welding bead 90 is formed along the flange 26 of the reinforcing material, in which the welding bead extends to a second side edge part 32b opposed from a first side edge part 32a of the reinforcing material flange 26 in its cross section. In the welding system for executing the welding method, the welding system comprises three welding heads 54a and 54b arranged in a triangular shape, in which its respective ones are provided with rotary pins 66a and 66b and shoulder parts 74a and 74b extending in base parts of the rotary pins.
摘要翻译：要解决的问题：提高用于将增强材料固定到飞机面板的摩擦搅拌焊接方法和系统。解决方案：该方法用于在加强材料22的凸缘26上执行线性渗透摩擦搅拌焊接FSW 至少有一架面板24用于飞机。在该方法中，沿着加强材料的凸缘26形成焊珠90，焊接珠沿着加强材料凸缘26的横截面与第一侧边缘部分32a相对的第二侧边缘部分32b延伸。在用于执行焊接方法的焊接系统中，焊接系统包括布置成三角形形状的三个焊接头54a和54b，其中各自的焊接头54a和54b设置有旋转销66a和66b以及在基座部分延伸的肩部部分74a和74b 旋转销。

3. 发明专利

JP2013056665A Method for fabrication of structure comprising skin and stiffener 有权
标题翻译：用于制造包含皮肤和刺激物的结构的方法
公开(公告)号：JP2013056665A
公开(公告)日：2013-03-28
申请号：JP2012197171
申请日：2012-09-07
申请人： Airbus Operations Sas , エアバスオペラシオンソシエテパアクシオンスシンプリフィエ
发明人： BLOT PHILIPPE
IPC分类号： B64C1/12 , B64C1/00 , B64F5/00
CPC分类号： B64C1/12 , B29C33/14 , B29C33/76 , B29C70/205 , B29C70/342 , B29D99/0014 , B29K2707/04 , B29L2031/3082 , B64C2001/0072 , B64F5/10 , Y02T50/433 , Y10T428/24744
摘要： PROBLEM TO BE SOLVED: To provide a method for fabrication of a structure including a skin (2) and a molded component (4) having a V-section called a stiffener fixed to the skin (2), in particular an aircraft fuselage made of a composite material.SOLUTION: The method includes a step of positioning a die on a mandrel to form grooves between the dies. The grooves are arranged in at least two network structures (6a, 6b, 6c), each groove of the same network structure (6a, 6b, 6c) intersects at least one groove to another network structure at a node. The method also includes a step of positioning a preform of stiffeners in the grooves so that two stiffeners (4) at least intersect at the node (8) and a step of injecting resin so as to assemble the stiffeners (4). This provides a structure made of a monoblock.
摘要翻译：要解决的问题：提供一种制造包括皮肤（2）和模制部件（4）的结构的方法，所述模制部件具有称为固定到皮肤（2）的加强件的V形部分，特别是飞机机身由复合材料制成。解决方案：该方法包括将模具定位在心轴上以在模具之间形成凹槽的步骤。凹槽布置在至少两个网络结构（6a，6b，6c）中，相同网络结构（6a，6b，6c）的每个凹槽在至少一个凹槽与一个节点处的另一个网络结构相交。该方法还包括将加强件的预制件定位在凹槽中的步骤，使得至少在节点（8）处相交的两个加强件（4）和注入树脂以便组装加强件（4）的步骤。这提供了由整数构成的结构。版权所有（C）2013，JPO＆INPIT

4. 发明专利

JP2014050884A Improved system for friction stir welding equipped with movable opposing support 有权
标题翻译：用于具有可移动对接支持的摩擦式STIR焊接改进系统
公开(公告)号：JP2014050884A
公开(公告)日：2014-03-20
申请号：JP2013183675
申请日：2013-09-05
申请人： Airbus Operations Sas , エアバスオペラシオンソシエテパアクシオンスシンプリフィエ
发明人： MIALHE CHRISTOPHE , PATRICK LIEVEN , ROMAIN DELAHAYE
IPC分类号： B23K20/12 , B64C1/12 , B64F5/00
CPC分类号： B23K20/126 , B23K20/122 , B23K20/1255 , B23K20/1265 , B23K20/26 , B23K2201/006
摘要： PROBLEM TO BE SOLVED: To improve a friction stir welding system.SOLUTION: A friction stir welding system 46 for welding at least two parts 22 and 24 to be assembled includes a welding unit including a welding device having at least one welding head 54 provided with a rotary pin 66 and an opposing support unit 50 providing a supporting surface designed in such a manner as to support the parts to be assembled against pressures applied by individual welding heads. Each welding head can move in the direction parallel to the rotation axis 68 of the rotary pin of the welding head with respect to the supporting surface of the opposing support unit and also in the second direction crossing the rotation axis of the rotary pin of the welding head at right angle.
摘要翻译：要解决的问题：改善摩擦搅拌焊接系统。解决方案：用于焊接待组装的至少两个部件22和24的摩擦搅拌焊接系统46包括焊接单元，其包括焊接装置，该焊接装置具有至少一个焊接头54，旋转销66和相对的支撑单元50，其提供支撑表面，该支撑表面设计成能够抵抗由各个焊接头施加的压力来支撑待组装的部件。每个焊接头可以相对于相对的支撑单元的支撑表面在平行于焊接头的旋转销的旋转轴线的方向上移动，并且在与焊接的旋转销的旋转销的旋转轴线交叉的第二方向上移动头直角

5. 发明专利

JP2013056662A Framing element of an aircraft fuselage 有权
标题翻译：飞机配件的框架元件
公开(公告)号：JP2013056662A
公开(公告)日：2013-03-28
申请号：JP2012193366
申请日：2012-09-03
申请人： Airbus Operations (Sas) , エアバスオペラシオン(エス.ア.エス)
发明人： DELAHAYA ROMAIN , LIEVEN PATRICK , MIALHE CHRISTOPHE
IPC分类号： B64C1/06
CPC分类号： B64C1/061 , B64C1/068 , B64C1/10 , B64C1/18
摘要： PROBLEM TO BE SOLVED: To provide a framing element of an aircraft fuselage where a part of crossing member and a section of a frame are integrally assembled into a unit component to simplify the design of parts which constitute a triangular region, a fuselage tab frame region, and a frame upper part of an aircraft fuselage.SOLUTION: There are included: frame elements 101, 102 and 103 of the fuselage of an aircraft provided with parts 1a, 101a, 102a and sections 1b, 101b of a crossing member that are integrally assembled into a unit component and 102b of a frame, an upper frame 5, a floor crossing member 3, and a lower frame 4 are connected to one another; and a frame of the fuselage of an aircraft having a segment 1c replaced with a floor strut where an assembly of the crossing members and a crossing member for use to fix either a freight crossing member or a luggage storing part of the aircraft are formed at the crossing member at the crossing member of the frame elements 101, 102.
摘要翻译：要解决的问题：为了提供飞机机身的框架元件，其中交叉构件的一部分和框架的一部分整体地组装成单元部件以简化构成三角形区域的部件的设计，机身翼片框架区域和飞机机身的框架上部。解决方案：包括：机身机身的框架元件101,102和103，其具有一体地组装成单元部件的部件1a，101a，102a和部分1b，101b和102b，框架，上框架5，地板交叉构件3和下框架4彼此连接; 以及具有更换为地面支柱的段1c的飞行器的机身的框架，在该支架上形成有用于固定飞机的货运交叉构件或行李存放部分的交叉构件和交叉构件的组件在框架元件101,102的交叉构件上的交叉构件。版权所有（C）2013，JPO＆INPIT

6. 发明专利

JP2011256389A Novel stable aqueous dispersion liquid of nanoparticle of high-performance thermoplastic polymer, and use of the same as film-forming agent 审中-公开
标题翻译：高性能热塑性聚合物纳米颗粒的新型稳定的水性分散液，以及其作为成膜剂的用途
公开(公告)号：JP2011256389A
公开(公告)日：2011-12-22
申请号：JP2011127738
申请日：2011-06-07
申请人： Airbus Operations Sas , Centre National De La Recherche Scientifique (Cnrs) , エアバスオペラシオンソシエテパアクシオンスシンプリフィエ , サントルナシオナルドゥラルシェルシェサイアンティフィク(セエヌエールエス)
发明人： BERGERAT JEAN-MICHEL , GIRAUD ISABELLE , DANTRAS ERIC , PEREZ EMILE , LACABANNE COLETTE
IPC分类号： C08J3/07 , D06M15/647 , D06M101/40
CPC分类号： D06M15/59 , B82Y30/00 , C08G2650/40 , C08J5/005 , C08J2371/10 , C08J2379/08 , C08L71/00 , C08L79/08 , C09D171/00 , D06M15/53 , D06M23/08 , D06M2101/36 , D06M2101/40 , D06M2200/40 , Y10T428/2938
摘要： PROBLEM TO BE SOLVED: To provide a novel stable aqueous dispersion liquid of a nanoparticle of a high-performance thermoplastic polymer, and to provide a use method of the same as a film-forming agent.SOLUTION: The present invention relates to a novel aqueous dispersion liquid of a thermoplastic polymer, which is suitable as a film-forming agent, particularly, for sizing of fibers to facilitate handling of the fibers, and fabricating a composite material.
摘要翻译：要解决的问题：提供一种新型稳定的高性能热塑性聚合物纳米颗粒的水性分散液，并提供其作为成膜剂的用途。解决方案：本发明涉及一种热塑性聚合物的新型水分散液，其适合作为成膜剂，特别是用于纤维尺寸调节以便于处理纤维，以及制备复合材料。版权所有（C）2012，JPO＆INPIT

7. 发明专利

JP2014114012A Aircraft which includes center wing and fuselage, and in which the fuselage comprises connection device that is connected to the center wing and configured so as to transmit stress received by the fuselage to the center wing 审中-公开
标题翻译：飞机包括中心线和接头，并且其中的连接包括连接到中心的连接设备，并且被配置为将发送的接口发送到中心的接口
公开(公告)号：JP2014114012A
公开(公告)日：2014-06-26
申请号：JP2013255257
申请日：2013-12-10
申请人： Airbus Operations Sas , エアバスオペラシオンソシエテパアクシオンスシンプリフィエ
发明人： FRANCOIS LOYANT , ALEXANDRE LEGARDEZ
IPC分类号： B64C1/26
CPC分类号： B64C1/26
摘要： PROBLEM TO BE SOLVED: To provide an aircraft comprising a fuselage which optimizes dispersion of stress and has a simple, convenient and economical connection device.SOLUTION: A fuselage comprises a connection device which is connected to a center wing and configured so as to transmit stress received by the fuselage when an aircraft is operated to the center wing. The connection device is formed by a keel beam (20) and a beam plate (24) which is connected to the keel beam via a connecting portion (22) of the keel beam, and the keel beam further includes: a major portion (21) which extends in a first direction of an approximately longitudinal direction; and guiding portions (23) which extend in a second direction different from the first direction and are configured to be connected to the center wing. The major portion, the guiding portions and the connecting portion are configured to guide a major portion of stress received by the keel beam to the second direction and transmit the major portion of the stress to the center wing as compressive stress.
摘要翻译：要解决的问题：提供一种包括优化应力分散的机身的飞行器，并且具有简单，方便和经济的连接装置。解决方案：机身包括连接到中心翼的连接装置，并被构造成传递应力当飞机运行到中心翼时，机身接收到的。连接装置由龙骨梁（20）和梁板（24）形成，梁板（24）经由龙骨梁的连接部分（22）连接到龙骨梁，龙骨梁还包括：主要部分（21 ），其沿大致纵向方向的第一方向延伸; 以及沿与第一方向不同的第二方向延伸并且构造成连接到中心翼的引导部分（23）。主要部分，引导部分和连接部分构造成将由龙骨梁接收的应力的主要部分引导到第二方向，并将应力的主要部分作为压应力传递到中心翼。

8. 发明专利

JP2013049408A Method and system for determining flight parameter of aircraft 有权
标题翻译：用于确定飞机飞行参数的方法和系统
公开(公告)号：JP2013049408A
公开(公告)日：2013-03-14
申请号：JP2012169183
申请日：2012-07-31
申请人： Airbus Operations Sas , エアバスオペラシオンソシエテパアクシオンスシンプリフィエ , Onera (Office National D'etudes Et De Recherches Aerospatiales) , オネラ (オフイスナシオナルデチュードエドゥルシェルシュアエロスパシヤル)ONERA (Office National d’Etudes et de Recherches Aerospatiales)
发明人： EZERZERE PIERRE , SEREN CEDRIC , HARDIER GEORGES
IPC分类号： B64D45/00
CPC分类号： G05D1/0055 , B64D45/00 , G05B13/04
摘要： PROBLEM TO BE SOLVED: To provide a method and system for determining flight parameters of an aircraft.SOLUTION: The system for determining, in real time, flight parameters of an aircraft, in the course of a flight of the latter, includes an extended Kalman filter 10 which is configured on the basis of flight mechanics equations establishing a dependency relationship between at least two preselected flight parameters of the aircraft to be estimated and which is formed so as to deliver, during a flight of the aircraft, the joint estimation of the selected flight parameters.
摘要翻译：要解决的问题：提供一种用于确定飞行器的飞行参数的方法和系统。解决方案：实时确定飞行器飞行参数的系统在后者的飞行过程中包括扩展卡尔曼滤波器10，其基于建立依赖关系的飞行力学方程式在待估计的飞行器的至少两个预选飞行参数之间，并且形成为在飞行器飞行期间传递所选飞行参数的联合估计。版权所有（C）2013，JPO＆INPIT

9. 发明专利

JP2013018286A Process for production of double-curved panel 有权
标题翻译：生产双曲面板的方法
公开(公告)号：JP2013018286A
公开(公告)日：2013-01-31
申请号：JP2012153811
申请日：2012-07-09
申请人： Airbus Operations Sas , エアバスオペレイションズエスエーエス
发明人： BERNADET PHILIPPE , GIUSEPPIN LAURENT
IPC分类号： B29C39/10 , B29C39/24 , B29K105/08 , B29L31/30 , B64C1/12
CPC分类号： B29C70/207 , B29B11/16 , B29C70/222 , B29C70/342 , B29C70/345 , B29L2031/3082 , Y02T50/433
摘要： PROBLEM TO BE SOLVED: To provide a process for production of an aircraft panel made of double-curved composite material to remedy the drawbacks of the prior art.SOLUTION: This process, in which a panel is obtained from a three-dimensional preform that includes fibers that are distributed in a defined arrangement, includes manufacturing a flat fiber preform 22, and deforming the flat preform 22 in such a way as to produce the three-dimensional preform, with the fibers following trajectories suitable for the flat preform in such a way as to obtain the defined arrangement of the fibers after deformation.

10. 发明专利

JP2011240925A Composite structural member with progressive rigidity 审中-公开
标题翻译：具有渐进刚度的复合结构构件
公开(公告)号：JP2011240925A
公开(公告)日：2011-12-01
申请号：JP2011110718
申请日：2011-05-17
申请人： Airbus Operations (Sas) , エアバスオペラシオン(エス.ア.エス)
发明人： SOULA DENIS , GUILLEMAUT JULIEN
IPC分类号： B64C1/00 , B29C70/06 , B29C70/10 , B29K105/08 , B29L31/30 , B64C3/18
CPC分类号： B29C70/207 , B29C70/30 , B29L2031/3085 , B64C1/26 , Y02T50/433 , Y10T428/24124
摘要： PROBLEM TO BE SOLVED: To provide a composite structural member with fiber reinforcement.SOLUTION: The invention relates to the composite structural member with fiber reinforcement and its application in the production of a wing box for aircraft. More specifically, it relates to a composite structural member (230) with fiber reinforcement comprising a plurality of layers oriented relative to a longitudinal direction (2) of the member in directions including 0°, 90° and +/-θ; the relative proportion of layers in one of these orientations being variable along a transverse direction (3) of the member so as to spatially adjust the rigidity of the member according to a defined distribution of mechanical stresses along this transverse axis (3). Thus the rigidity of the member is adapted locally to a stress system so as to dissipate the force flux over the entire volume of the member.
摘要翻译：要解决的问题：提供具有纤维增强的复合结构构件。解决方案：本发明涉及具有纤维增强件的复合结构件及其在生产用于飞机的翼箱中的应用。更具体地说，本发明涉及一种具有纤维增强材料的复合结构件（230），其包括在包括0°，90°和+/-θ的方向上相对于构件的纵向方向（2）定向的多个层; 这些取向之一中的层之间的相对比例沿着该构件的横向方向（3）是可变的，以便根据沿该横向轴线（3）的规定的机械应力分布来空间调整构件的刚性。因此，构件的刚性局部地适应于应力系统，以便在构件的整个体积上消散力通量。版权所有（C）2012，JPO＆INPIT

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