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1. 发明申请

WO2012098331A3 FISH JOINT DEVICE HAVING AN IMPROVED MECHANICAL HOLD 审中-公开
标题翻译：鱼联合装置具有改进的机械控制
公开(公告)号：WO2012098331A3
公开(公告)日：2012-09-13
申请号：PCT/FR2012050102
申请日：2012-01-17
申请人： AIRBUS OPERATIONS SAS , GUILLEMAUT JULIEN , GALLANT GUILLAUME
发明人： GUILLEMAUT JULIEN , GALLANT GUILLAUME
IPC分类号： B64C1/26
CPC分类号： B64C1/26 , F16B5/02 , Y10T403/74
摘要： The invention relates to a fish joint device for securing first and second structural elements (1, 2) of an aircraft to each other, said device comprising two fish plates (20, 30) arranged either side of the structural elements (1, 2) and fixed thereto by means of a set of cross-members (11) for fixing fish plates. According to the invention, the fish joint device comprises at least one intermediate fish joint plate (40, 50) that is arranged between one of said fish plates (20, 30) and said structural elements (1, 2) partially covered by said intermediate plate, and is fixed thereto by a set of cross-members (11) for fixing intermediate plates, including the set of cross-members (11) for fixing fish plates.
摘要翻译：本发明涉及一种用于将航空器的第一和第二结构元件（1,2）相互固定的鱼尾接头装置，所述装置包括布置在结构元件（1,2）两侧的两个鱼尾板（20,30）并通过用于固定鱼尾板的一组横向构件（11）固定于其上。根据本发明，鱼尾接头装置包括至少一个布置在一个所述鱼尾板（20,30）和所述结构元件（1,2）之间的至少一个中间鱼尾板（40,50），所述结构元件（1,2）部分地被所述中间体并通过一组用于固定中间板的横向构件（11）固定于其上，该中间板包括用于固定鱼尾板的一组横向构件（11）。

2. 发明申请

WO2010136717A2 EQUIPMENT FOR PRODUCING A SEGMENT OF AN AIRCRAFT FUSELAGE 审中-公开
标题翻译：用于生产航空器熔接部分的设备
公开(公告)号：WO2010136717A2
公开(公告)日：2010-12-02
申请号：PCT/FR2010051005
申请日：2010-05-25
申请人： AIRBUS OPERATIONS SAS , GALLANT GUILLAUME , DELAHAYE ROMAIN
发明人： GALLANT GUILLAUME , DELAHAYE ROMAIN
IPC分类号： B64F5/00
CPC分类号： B29C70/86 , B29C33/301 , B29L2031/3082 , B64C1/061 , B64C1/12 , B64C2001/0072 , B64F5/10 , B64F5/50 , Y02T50/433 , Y10T29/49622 , Y10T29/53478
摘要： The invention relates to a method for producing an aircraft, comprising: passing a mandrel (6, 30) through frames (52) supported by a magazine (46) and, during the passing operation, transferring the frames onto the mandrel.
摘要翻译：本发明涉及一种用于生产飞行器的方法，包括：使心轴（6,30）穿过由弹匣（46）支撑的框架（52），并且在通过操作期间将框架转移到心轴上。

3. 发明申请

WO2011001081A3 FRAME FOR AN OPENING PROVIDED IN AN AIRCRAFT FUSELAGE 审中-公开
标题翻译：在飞机熔断器中提供的开口框架
公开(公告)号：WO2011001081A3
公开(公告)日：2011-06-30
申请号：PCT/FR2010051317
申请日：2010-06-25
申请人： AIRBUS OPERATIONS SAS , DUGERIE MARC , GALLANT GUILLAUME , DELAHAYE ROMAIN
发明人： DUGERIE MARC , GALLANT GUILLAUME , DELAHAYE ROMAIN
IPC分类号： B64C1/14
CPC分类号： B64C1/1461
摘要： The invention relates to a frame for a door provided at an opening provided in an aircraft fuselage defined by a skin, said frame including an upper longitudinal stiffener and a lower longitudinal stiffener connecting two vertical substructures (62) together, which are arranged on either side of the opening at which at least one abutment (56) is provided for transferring the radial forces exerted by the door, characterized in that each vertical substructure (62) includes at least three walls made of a composite material and connected together so as to form a closed and hollow profile in order to obtain a shell structure.
摘要翻译：本发明涉及一种用于门的框架，其设置在由蒙皮限定的飞机机身中设置的开口处，所述框架包括上部纵向加强件和将两个竖直子结构（62）连接在一起的下部纵向加强件，所述下部纵向加强件布置在任一侧其中至少一个支座（56）被设置用于传递由门施加的径向力，其特征在于，每个垂直底座（62）包括至少三个由复合材料制成并连接在一起以形成一个封闭和空心的外形，以获得壳结构。

4. 发明申请

WO2008043940A3 AIRCRAFT FUSELAGE MADE FROM LONGITUDINAL PANELS AND METHOD OF PRODUCING SUCH A FUSELAGE 审中-公开
标题翻译：远程面板制造的飞机熔接及其制造方法
公开(公告)号：WO2008043940A3
公开(公告)日：2008-06-12
申请号：PCT/FR2007052081
申请日：2007-10-04
申请人： AIRBUS FRANCE , GALLANT GUILLAUME , BERNADET PHILIPPE
发明人： GALLANT GUILLAUME , BERNADET PHILIPPE
IPC分类号： B64C1/00
CPC分类号： B64C1/068 , B64C2211/00
摘要： The invention relates to an aircraft fuselage comprising a nose cone (2), a tail section (2) and a central section (3), the central section comprising longitudinal panels (31 - 39) assembled directly with one another, at least one of these longitudinal panels having a length corresponding to the distance between the nose cone and the tail section in order to connect said nose cone with said tail section.
摘要翻译：本发明涉及一种包括鼻锥体（2），尾部部分（2）和中心部分（3）的飞行器机身，所述中心部分包括彼此直接组装的纵向面板（31-39），至少一个这些纵向面板的长度对应于鼻锥和尾部之间的距离，以将鼻锥与所述尾部部分连接。

5. 发明申请

WO2008096087A3 SECTION OF AIRCRAFT FUSELAGE AND AIRCRAFT INCLUDING ONE SUCH SECTION 审中-公开
标题翻译：飞机熔接和飞机部分，包括一个这样的部分
公开(公告)号：WO2008096087A3
公开(公告)日：2008-10-23
申请号：PCT/FR2008050006
申请日：2008-01-03
申请人： AIRBUS FRANCE , GALLANT GUILLAUME , AGUERA DAMIEN , BERNADET PHILIPPE
发明人： GALLANT GUILLAUME , AGUERA DAMIEN , BERNADET PHILIPPE
IPC分类号： B64C1/06 , B64C1/14
CPC分类号： B64C1/061 , B64C1/068 , B64C1/14
摘要： The invention relates to a section of fuselage for an aircraft, comprising frames and bays for receiving cabin windows (11). According to the invention, at least some of the frames include at least one frame segment that surrounds at least one bay, said frame segment comprising two branches (15, 16) that are disposed to the side of the bay. The ends of the branches are attached to each of the ends (17, 18) of the frame segment such as to form a Y.
摘要翻译：本发明涉及一种用于飞机的机身的一部分，包括用于接收舱窗（11）的框架和舱。根据本发明，至少一些框架包括围绕至少一个隔间的至少一个框架段，所述框架段包括设置在隔间侧面的两个分支（15,16）。分支的端部附接到框架段的每个端部（17,18），以形成Y.

6. 发明申请

WO2009156637A3 METHOD FOR THE ORBITAL ASSEMBLY OF AIRCRAFT SECTIONS MADE OF COMPOSITE MATERIAL 审中-公开
标题翻译：复合材料飞机部件的组装方法
公开(公告)号：WO2009156637A3
公开(公告)日：2010-02-18
申请号：PCT/FR2009050972
申请日：2009-05-26
申请人： ALRBUS OPERATIONS SOC PAR ACTI , GALLANT GUILLAUME , LACOMBE JEAN-CLAUDE
发明人： GALLANT GUILLAUME , LACOMBE JEAN-CLAUDE
IPC分类号： B29C65/00 , F16L47/00
CPC分类号： B64C1/069 , B29C65/56 , B29C66/5229 , B29C66/71 , B29C66/721 , B29C2793/0036 , B29K2023/06 , B29K2067/00 , B29K2105/06 , B29L2031/3082 , B64C2001/0072 , Y02T50/433 , Y10T29/4932 , Y10T29/49622 , Y10T29/49826 , B29K2023/04
摘要： The invention relates to a method for assembling two structural elements, at least one of the two being tube-shaped and including a skin made of a fiber-reinforced composite material. The ability of said element to adapt to the shape and perimeter of the junction interface is improved by providing longitudinal grooves (5) distributed on the circumference of the junction interface. The grooves (5) are of a sufficient length to provide the junction interface with the flexibility to accommodate, through the relative radial movement of each portion located between two grooves, the differences in shape and perimeter among the junction interfaces of the two structural elements.
摘要翻译：本发明涉及一种用于组装两个结构元件的方法，所述两个结构元件中的至少一个是管状并且包括由纤维增强复合材料制成的表皮。通过提供分布在接合界面的圆周上的纵向凹槽（5）来改善所述元件适应接合界面的形状和周长的能力。凹槽（5）具有足够的长度，以提供具有柔性的接合界面，以通过位于两个凹槽之间的每个部分的相对径向运动来容纳两个结构元件的连接界面之间的形状和周长的差异。

7. 发明申请

WO2008096088A2 AIRCRAFT CABIN WINDOW ASSEMBLY METHOD 审中-公开
标题翻译：飞机舱窗户组装方法
公开(公告)号：WO2008096088A2
公开(公告)日：2008-08-14
申请号：PCT/FR2008050008
申请日：2008-01-03
申请人： AIRBUS FRANCE , GALLANT GUILLAUME , AGUERA DAMIEN , BERNADET PHILIPPE
发明人： GALLANT GUILLAUME , AGUERA DAMIEN , BERNADET PHILIPPE
CPC分类号： B64C1/1492 , Y10T29/49826
摘要： The invention relates to a method for assembling a cabin window to a bay in a side wall (12) of an aircraft fuselage, said cabin window comprising an outer transparent element (10) and at least one inner transparent element (11). According to the invention, a non-through hole is made in a portion of the side wall (12) along the edge of the bay. Subsequently, the outer transparent element (10) is positioned in the bay from the exterior of the fuselage, said element including a first part (13) which has a diameter greater than that of the bay and which is shaped to co-operate with the above-mentioned portion such as to block the outer transparent element (10) in the bay both laterally and longitudinally. The outer transparent element (10) also includes a second part (16) having a groove (17) that projects into the fuselage. The outer transparent element (10) and the at least one inner transparent element (11) are welded to the fuselage using a strap (22) which presses a seal (21) against at least the fuselage and the inner wall of the groove (17).
摘要翻译：本发明涉及一种用于将舱窗组装到飞行器机身的侧壁（12）中的舱的方法，所述舱窗包括外部透明元件（10）和至少一个内部透明元件（11）。根据本发明，沿侧壁的边缘在侧壁（12）的一部分中形成非通孔。随后，外部透明元件（10）从机身的外部定位在隔间中，所述元件包括第一部分（13），该第一部分的直径大于海湾的直径，并且其形状与上述部分，例如横向和纵向地阻挡隔间中的外部透明元件（10）。外部透明元件（10）还包括具有突出到机身中的凹槽（17）的第二部分（16）。外部透明元件（10）和至少一个内部透明元件（11）使用将密封件（21）压在至少机身和凹槽（17）的内壁上的带子（22）而焊接到机身上）。

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